Class / Patent application number | Description | Number of patent applications / Date published |
244023000 | Fluid sustained | 75 |
20080302920 | Aerial Lifting and Propulsion Device (ALPD) - This invention, an Aerial Lifting and Propulsion Device, introduces an aircraft and aircraft wing design that has an outer and inner circumference, both of which are employed in the entirety of each to evacuate air, air space, and/or atmosphere from above the circular wing/craft, to the area beneath the circular wing/craft, through the use of a propeller inside the inner circumference of the circular wing, and impellers at the outer circumference of the circular wing. When the air, air space, and/or atmosphere forced from above the circular wing into the area beneath the circular wing and propeller attempts to escape to the top of the circular wing to fill the newly created low pressure area above the circular wing, it is intercepted at the lower edge of the outer circumference of the circular wing and forced to returned to the area beneath the circular wing, where the atmospheric pressure is further increased or decreased at will, depending on the pitch and speed of the aircraft propeller and impeller blades. The noted reduced atmospheric pressure at the top of the circular wing, and the higher controlled atmospheric pressure in the area beneath the circular wing and propeller, forces the circular wing upward from its stationary position, achieving lift as described in Bernoulli's Principle. Stabilization and directional control is maintained through adjustments in the pitch of the impeller and propeller and the effects of torque are neutralized by the rotation of the impeller and propeller assemblies in opposite directions. The Aerial Lifting and Propulsion Device maintains its upright configuration while airborne in part because its center of gravity is well below the points where lift is generated. | 12-11-2008 |
20090084907 | Ground Effect Vanes Arrangement - A vehicle, particularly a VTOL air vehicle, includes a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame; a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid therethrough from its inlet at the upper end of the duct through its exit at the lower end of the duct, and thereby to produce an upward lift force applied to the vehicle, and a plurality of spaced vanes mounted to and across the inlet and exit ends of the duct about axes substantially perpendicular to the longitudinal axis of the duct and selectively operational to produce a desired horizontal control force in addition to the lift force applied to the vehicle. | 04-02-2009 |
20100001143 | Discoidal flying craft - A flying craft has an aerodynamic aircraft fuselage structure preferably disc shaped. A pair of coaxial electrokinetic motor-generators are mounted concentrically, and preferably centered within the disc shaped structure of the craft. Each of the motors is toroidal in configuration, providing a ring-shaped stator and rotor portions. The rotor portions of the motors drive counter rotating fans which are electro-magnetically levitated. The structure is open to the fans so that air may be drawn into the structure and expelled downward providing vertical lift to the aircraft. By use of auxiliary air braking flaps and electrokinetic thrusters, the craft may be tilted so as to develop a desired horizontal thrust. By impulse breaking one of the fans through tracking solenoids at different points around the stator, the aircraft may be made to rotate about its own vertical axis for changing direction. By a series of sudden braking of the motors the craft may be made to move by inertial reaction. | 01-07-2010 |
20120068021 | CRAFT AND METHOD FOR ASSEMBLING CRAFT WITH CONTROLLED SPIN - This invention relates to a craft designed to move through or on a surface of a fluid. It is believed to be principally of use in relation to airborne craft and missiles but the theory behind the invention is equally applicable for example to submarines. | 03-22-2012 |
20140027581 | AIRCRAFT HAVING A ROTATING TURBINE ENGINE - The present invention describes an aircraft having a rotating engine. The aircraft comprises a means for rotating the engine 360° to allow directional control of the aircraft via rotation of the engine's thrust output. The aircraft can further comprise a plurality of flap members located on the wings of the aircraft and in communication with the rotating gas turbine engine to further control and stabilize flight of the aircraft. The gas turbine engine of the aircraft can comprise a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating more thrust from a single engine. | 01-30-2014 |
20150028161 | Hydraulic Passenger Lifting and Maneuvering Device - This invention relates to a fluid driven propulsion device comprising a body arranged in a manner to facilitate flight and lift for a person, passenger or object(s) with a production of thrust from a portable or fixed power unit. A power unit is designated to move an incompressible fluid via pump through a flexible pipe or transmission tube to two or more pairs of restrictive axially offset nozzles within the embodiment of the invention allowing the incompressible fluid's pressure to build and its mass to be ejected underneath the person, passenger or object(s). This fluid is expelled with such velocity to create a force, directed into multiple, generally symmetrical force vectors, sufficient to facilitate balanced, easy to master free-flight. The invention also allows for powered, active inward and outward adjustment of the axially offset pairs of nozzles, as well as powered, active aperture adjustment of each of the nozzle outlets. | 01-29-2015 |
20160144960 | PERSONAL FLUID-JET THRUST PACK WHICH PROVIDES ROTATION FOR A RIDER ABOUT THREE AXES - The present invention provides lightweight fluid-jet thrust pack which provides three rotational axes and reduced restriction of fluid flow to the output nozzles. A first rotational axis is provided by a first rotatable coupling that is concentric with a coupler for a hose supplying pressurized fluid. The top of the first coupling has a splitter which directs incoming fluid into two splayed stub supply pipes. A preformed, reinforced rubber hose connects each stub supply pipe to one of a pair of coaxial rotatable couplings at opposite ends of a tiltable cross arm assembly that is pivotally secured to tower support bracket that is secured to the first rotatable coupling. An outward rotatable portion of each of the coaxial rotatable couplings is equipped with one boot-mounting platform and a downward-projecting jet nozzle that is in communication with the stub receiver pipe of the same rotatable coupling. | 05-26-2016 |
20160152338 | AN AERODYNAMIC LIFTING DEVICE | 06-02-2016 |
20090236475 | LIFT CHAMBER - A lift device having a generally cylindrical chamber formed by a top wall, a bottom wall, an outer wall and an inner wall. A plurality of lift members are mounted to the interior of a chamber wall and at least one fan is mounted within the chamber and an engine operatively connected to at lease one fan. | 09-24-2009 |
20100025540 | Compact ultralight aircraft reduced dimensions, with vertical take-off and landing - A compact ultralight aircraft ( | 02-04-2010 |
20100051754 | Aircraft - An aircraft has a generally circular main body including an upper surface portion supported for rotation about a central passenger compartment to produce a gyroscopic effect on the aircraft. The rotatable upper surface portion includes viewable panes therein arranged to provide visibility therethrough from the central passenger compartment to an exterior of the main body. An engine communicates between a central inlet opening in the upper surface portion and an exhaust opening in the bottom of the main body to provide upward thrust to the aircraft. | 03-04-2010 |
20100102174 | Wingless Hovering Of Micro Air Vehicle - Embodiments of the subject invention relate to a Wingless Hovering Micro Air Vehicle (WHOMAV) and its Power Source Unit (PSU). Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments of the subject invention can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | 04-29-2010 |
20100187369 | DUCTED FAN UAV CONTROL ALTERNATIVES - A ducted fan air-vehicle having alternative methods of control is described. The ducted fan air-vehicle includes an air duct, a fan, a center body, a plurality of control vanes. Each control vanes includes a separate servo for independent control of each control vane, and is therefore able to operate the control vanes in a non-traditional manner to provide maximum control authority. | 07-29-2010 |
20100282918 | Saucer shaped gyroscopically stabilized vertical take-off and landing aircraft - An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating sine-wave ring is used to activate and move a plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere. | 11-11-2010 |
20100288889 | SPRING FLYING DEVICE - The Spring flying device ( | 11-18-2010 |
20130181095 | DEVICE TO GENERATE LIFT FORCE (OPTIONS) - The options of the invention relate to the aviation and can be used in order to create lifting vehicle as well as load lifting devices. In order to achieve technical result—the decrease of energy losses on the while creating and change of vector of moving, aerodynamic, composite force, including as a component a lift force,—in the device to generate lift force containing a tubiform frame, superchargers, the wings having in section an aerofoil profile oriented by the leading edge to the direction of working medium exhaust out of the super-charger, adjusting units for a wing, guiding devices, each of those is installed in front of leading edge of each wing, the system to maintain the required working temperature of medium, unit to connect outdoor environment, as per the invention in the first option of the device a tubiform frame is of the form of a tore, in the second option—the form of closed volumetric loop, in the third option—a cylindrical form. Meanwhile each option of the device is equipped with relevant distinguishing units, providing the achieving of a technical result. | 07-18-2013 |
20130306802 | METHODS AND APPARATUS FOR VERTICAL SHORT TAKEOFF AND LANDING - Methods and apparatus for vertical or short takeoff and landing. In one embodiment, the apparatus comprises two or more counter driven rings with one or more airfoils attached. In one variant, there is an upper ring and a lower ring, each with multiple airfoils attached. In one variant, lift is generated largely via ambient air currents, allowing for long term on-station operation of the device. | 11-21-2013 |
20130306803 | AIRCRAFT GENERATING A LIFT FROM AN INTERIOR THEREOF - The invention discloses an aircraft generating a larger lift from its interior. The fluid channel inside the aircraft communicates with the engine and the ports on the upper surface of the outer shell. With the powerful suction of the engine, the fluid on the upper surface of the outer shell is quickly sucked into the fluid channel via respective ports under conditions of long path, large area, high speed and low air pressure, which results in large lift from the interior of the aircraft. In the course of generating the lift, the fluid resistances of the fluid wall and the fluid hole are sucked into the fluid channel through the ports at the front and the surrounding area of the aircraft, then high-speed fluid is emitted from the rear port. This approach contributes greatly to the transformation of the existing aircraft. The unified big wing significantly improves the lift, the speed and the carrying capacity of the existing aircraft with lowered energy consumption. | 11-21-2013 |
20090039206 | BIRD VORTEX FLYING MACHINE - The present invention comprises, in one embodiment, an inexpensive, lightweight flying vehicle using fixed pitch helicopter blades powered by ramjet engines mounted to a power-ring which transfers torque to the lifting rotors. The use of fixed pitch blades eliminates the need for a tail boom and tail rotor, as well as for variable incidence control of blade pitch and/or cyclic and collective rotor-pitch controls. An optional ballistic parachute may be deployed for emergency landings. A radial shroud encloses the ramjet engines to act as a sound shield. Since the rotor has a fixed pitch, lift may be controlled by rotor speed, where increased speed results in ascent, and decreased speed, descent. | 02-12-2009 |
20100193643 | LIFT FAN SYSTEM - Embodiments of the present invention include a system, e.g., for a short takeoff and vertical landing (STOVL) aircraft. The system includes a power generator, such as a gas turbine engine; a lift fan powered by the power generator; and includes two or more nozzles in fluid communication with the lift fan. | 08-05-2010 |
20110204188 | ROTOCRAFT - An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle. | 08-25-2011 |
20140077039 | Heated Screen For Air Intake Of Aircraft Engines - An aircraft includes a fuselage and wings mounted on opposite sides of the fuselage for sustained forward flight. An engine is mounted in the fuselage or at least one of the wings and includes an air intake. At least a portion of the air intake generally faces the forward direction for receiving intake air during forward flight. A filter assembly is mounted adjacent the air intake and disposed to impinge air and block objects from passing therethrough. A heated screen includes a heater and is mounted adjacent the air intake and upstream of the engine such that ice entering the air intake contacts the heated screen before entering the engine. A power source is provided to supply power to the heater. | 03-20-2014 |
20190144108 | Aircraft having Hover Stability in Inclined Flight Attitudes | 05-16-2019 |
20080223993 | HOMEOSTATIC FLYING HOVERCRAFT - A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control. | 09-18-2008 |
20080283673 | Ducted Fan Vtol Vehicles - A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | 11-20-2008 |
20090020654 | Harness with mounted engine frame - A harness with mounted engine frame comprises a harness to be worn by a user. An engine support arm is mounted on the harness and a pair of lateral arms extend from the engine support arm. At least one engine is associated with each lateral arm. A connector attaches directly or indirectly to the harness for receiving the engine support arm, so that the engine support arm is movable relative to the harness in response to engine output and other flight conditions. | 01-22-2009 |
20090121087 | High speed vertical take-off and land aircraft with active fan balancing system - A high-speed vertical take-off and land aircraft includes a body with an engine supported by the body. A fan assembly is also carried by the body. The fan assembly includes a hub and a plurality of blades to provide vertical lift for the aircraft. A nozzle ring is provided on the fan assembly. The nozzle ring includes an annular nozzle array. Hot gases from the engine are fed to the nozzle array by a feed duct. A bearing mechanism supports the fan assembly on the body. The bearing mechanism is carried in a work space. A brush seal assembly thermally isolates the work space from the hot exhaust gases passing through the feed duct to the nozzle array. | 05-14-2009 |
20090159757 | Ducted Fan Vtol Vehicles - A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | 06-25-2009 |
20090250557 | Whirling Wheel Airborne Vehicles - A sliding-arm whirling wheel thruster includes first and second whirling wheels and a housing. The first whirling wheel is disposed about a first rotational axis, and the second whirling wheel about a second rotational axis parallel to the first rotational axis. The housing comprises an arc over an enclosed space into which the first and second whirling wheels fit. The air blown outward by each of the whirling wheels is amassed inside the housing so as to make a pressure difference between inside and outside of the housing. The relative position of the first rotational axis to the second rotational axis is configured to be controlled. The airborne vehicle is lifted by buoyant force caused by the pressure difference. | 10-08-2009 |
20100012790 | GYRO-STABILIZED AIR VEHICLE - A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage. | 01-21-2010 |
20100019098 | Ducted Fan Core for Use with an Unmanned Aerial Vehicle - A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame, attached to which are an engine, gearbox assembly, fan, and a plurality of control vanes. A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle. | 01-28-2010 |
20100051753 | WALL EFFECTS ON VTOL VEHICLES - ducted air flow vehicle that includes a fuselage having a longitudinal axis, supporting at least one air flow duct and a prime mover arranged to force surrounding air into the duct through an inlet at an upper end of the duct with normally symmetrical airflow streams, thereby creating a lift force directed substantially along a duct axis; a plurality of vanes extending across the inlet, substantially parallel to the longitudinal axis; and wherein one or more groups of the vanes are selectively pivotable to align with adjacent abnormal asymmetrical airflow streams. | 03-04-2010 |
20100078523 | Tandem powered power tilting tilt rotor aircraft - An aircraft with a long body | 04-01-2010 |
20100127131 | System and Method For a Fuel Bladder Assembly With Embossed Film - Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto. The fuel bladder may include an embossed pattern disposed to prevent a vacuum being formed by the collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV). | 05-27-2010 |
20100140415 | VERTICAL TAKE OFF AND LANDING UNMANNED AERIAL VEHICLE AIRFRAME STRUCTURE - An unmanned aerial vehicle selectively formed of high strength composite structural part portions and lightweight aerodynamic foam portions to provide a low-cost and lightweight UAV that comports with export, civil airspace, and safety regulations. To further to reduce an overall weight of the UAV, mechanical elements are designed to provide multiple functionalities. Structural elements may be manufactured in same or similar non-specialized processes, and non-structural elements manufactured in same or similar non-specialized processes, reducing overall manufacturing costs. Materials and bonding elements are selected to provide frangibility and yet maintain normal flight structural integrity. | 06-10-2010 |
20100140416 | Ducted Fans with Flow Control Synthetic Jet Actuators and Methods for Ducted Fan Force and Moment Control - The present invention relates to the field of aerodynamics. More particularly, the present invention relates to manipulating air flow over a surface, such as the surface of a duct of a ducted fan vehicle. By controlling air flow over, at, or around the surface of a duct, the flight of the vehicle can be controlled. One embodiment of the invention provides a vertical take-off and landing (VTOL) ducted-fan vehicle comprising means for producing steady or unsteady blowing at a surface of a duct for producing control forces and moments for controlling flight. The means for unsteady blowing can be provided by synthetic jets and the means for steady blowing can be provided by a pressurized air supply. The synthetic jets can be integrated into the ducted-fan vehicles in numerous ways, including at the surface of the leading and/or trailing edge of the ducts. The synthetic jets can be independently operated to control the flight of the vehicle. A novel use of these inventive flow control concepts is to apply the control asymmetrically to the duct in order to produce an imbalance in forces, thus resulting in a moment or torque, which can be used to control flight. | 06-10-2010 |
20100171000 | Tandem powered tilt rotor aircraft - An aircraft with a long body | 07-08-2010 |
20100320333 | Saucer-shaped gyroscopically stabilized vertical take-off and landing aircraft - An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating plate includes a groove that traces a sinusoidal pattern around an inside periphery of the plate. Tracking arms have a portion that fit within the groove and another portion that connects to a piston. The rotation of the plate causes the tracking arms to travel within the sinusoidal groove and impart movement on the plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere. | 12-23-2010 |
20110001017 | UAV DUCTED FAN SWEPT AND LEAN STATOR DESIGN - A ducted fan air-vehicle having an air duct and a fan is described. The air duct includes an outer rim and an inner rim, and the fan is located within the air duct and rotates in a direction. The fan also includes a hub, a plurality of struts extending from the hub and positioned adjacent the outer rim of the fan, a plurality of stators extending from the hub and positioned adjacent the inner rim of the fan, and a plurality of rotor blades extending from the hub and positioned between the plurality of struts and the plurality of stators. The stators are lean in a plane of fan rotation and swept in a plane normal to fan rotation to create the optimum amount of noise reduction in the ducted fan air-vehicle. | 01-06-2011 |
20110049306 | CONTROL FLOWS AND FORCES IN VTOL VEHICLES - The present application relates to VTOL vehicles with multi-function capabilities and, specifically to ducted fan arrangements that facilitate the control of forces and flows of air to control movement of the vehicle in six degrees of freedom in both primary and secondary modes of operation. Also disclosed are pitch control mechanisms for the lift propellers of VTOL vehicles: drive and transmission arrangements; a specially configured exhaust duct for directing exhaust gases from such vehicles along an upper surface of the vehicle; and shock absorbing components for the landing gear of such vehicles. | 03-03-2011 |
20110049307 | VTOL VEHICLE WITH OFFSET ENGINE - A ducted air flow vehicle includes a fuselage having a longitudinal axis, supporting forward and aft air flow ducts having respective lift fans arranged to force surrounding air into said ducts through inlets at upper ends of said ducts and out of said ducts through outlets at lower ends of said ducts, thereby creating a lift force. A single engine is located on one side of said longitudinal axis, and is operatively configured to power the lift fans. A payload bay is located in a central area of said fuselage, between the forward and aft ducts, spanning the longitudinal axis. | 03-03-2011 |
20110139939 | PERSONAL FLIGHT DEVICE INCORPORATING RADIATOR COOLING PASSAGE - A personal flight device which includes: a housing which is securable to a pilot; at least one pair of ducted fans, one fan of the pair mounted to one side of the housing, the other fan of the pair mounted to the other side of the housing; wherein each fan rotates about an axis of rotation so as to draw air through the corresponding duct from an entry end of the duct to an exit end of the duct; and wherein the axis of rotation of each fan is fixed relative to the housing; at least one engine mounted on the housing for driving the fans such that both fans rotate in the same direction for producing thrust; the or each engine being cooled by a radiator; the or each radiator being associated with at least one passage having an entry end in communication with one surface of the radiator and an exit end adjacent the entry end of one of said ducts. | 06-16-2011 |
20110147533 | MORPHING DUCTED FAN FOR VERTICAL TAKE-OFF AND LANDING VEHICLE - A morphing duct of a ducted fan for a vertical take-off and landing (VTOL) vehicle is configured to change shape as function of the flight mode of the vehicle to improve the thrust per unit energy input for the ducted fan. Additionally, the morphing duct may be configured to change shape to change the flight path of the VTOL vehicle. | 06-23-2011 |
20110155859 | AIRCRAFT VERTICAL LIFT DEVICE - A lift device is disclosed that can be used to provide vertical lift to an aircraft or other vehicle. The lift device can include a fan that produces an airflow and a vane box that can direct the airflow. In one form the fan can be oriented at an angle relative to a reference plane in the aircraft. In another form the vane box can be oriented at an angle. The vane box can be structured to provide a maximum flow area between an aft flow vector and a forward flow vector. | 06-30-2011 |
20110155860 | FLUID DYNAMIC DEVICE WITH THRUST CONTROL SHROUD - A fluid dynamic device ( | 06-30-2011 |
20110210212 | Tilt rotor aircraft with tilting tail rotor - TT - A vertical take-off aircraft comprising a main power plant | 09-01-2011 |
20110266397 | SOLAR THERMAL ROTORCRAFT - A vehicle includes a housing having a wall with a central port and radial port formed at a lower portion of the housing, a blower disposed within the housing to move air through the central port, a distributor coupled to the blower to distribute air inside the housing, a heat-absorbing body disposed within the housing to absorb thermal energy, and at least one arm coupled to the housing. | 11-03-2011 |
20120056040 | Electric VTOL Aircraft - An electric and hybrid Vertical-Take Off and Landing (“VTOL”) aircraft is disclosed comprising a plurality of small Electric Ducted Fans (“EDFs”) of various sizes and orientations. The thrust of each fixed EDF is individually controlled by modulation of motor power by one or more onboard microcomputers connected to a plurality of onboard laser distance measuring sensors, at least three onboard three-axis accelerometers and at least one GPS thereby allowing extremely precise and safe VTOL operation. The aircraft may be employed to allow robotic and passenger vehicles to transition extremely quickly between normal linear flight and VTOL and tb operate in extreme and gusty conditions. | 03-08-2012 |
20120080564 | DUCTED PLATFORMS - A ducted fan for a VTOL vehicle includes a substantially cylindrical duct having an inlet at an upper end and an outlet at a lower end, and an air mover unit located within the substantially cylindrical duct. The duct also includes inner and outer wall portions and a substantially annular upper lip connecting the inner and outer wall portions, thus defining the inlet. The substantially annular upper lip has opposed fore and aft portions and opposed side portions and is provided with at least first and second openings, respectively, at each of the opposed side portions. The first and second arrays of openings permit flow of air into at least first and second respective chambers formed within the duct, the first and second chambers connected by at least one passageway to thereby enable substantial equalization of surface pressure at the opposed side portions of the substantially annular upper lip. | 04-05-2012 |
20120091284 | UNMANNED AERIAL VEHICLE - The various embodiments of the present invention provide an unmanned aerial vehicle comprising a hemispherical body, a brushless type electrical, a propeller, a plurality of wingtip devices, a plurality of servomotors and each of the plurality of the servomotors is connected to each of the plurality of the wingtip devices respectively, a plurality of carbon rods, and a casing. The brushless type electrical motor provides a lifting force for a Vertical take-off and landing (VTOL) and the plurality of wing tip devices are classified into three types of wing tip devices and the three types of wing tip devices are controlled by the respective servomotors to control yaw, pitch and roll movements thereby stabilizing and controlling the movement of an aircraft. | 04-19-2012 |
20120126064 | UAV DUCTED FAN LIP SHAPING - A ducted fan air-vehicle having a duct lip shape is described. The duct lip has an internal duct lip portion and an external duct lip portion, both of which are substantially curvature continuous around the circumference of the air duct. The duct has a plurality of cross-sections along its circumference and at least some of the plurality of cross-sections have a different shape. Further, each cross-section around the circumference of the duct has an a/b ratio and the a/b ratio for each cross-section is substantially the same. | 05-24-2012 |
20120153087 | Modular Pods for Use with an Unmanned Aerial Vehicle - A pod for an unmanned aerial vehicle is provided that may be removed and re-attached to the vehicle. The pod comprises an outer shell, within which a variety of payloads may be carried. A first surface on the vehicle frame comprises a plurality of connects or electrical traces. The plurality of attachments are used to removably attach the pods to the first surface. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle. | 06-21-2012 |
20120234984 | Integrated Duct Design for an Unmanned Aerial Vehicle - A ducted fan air vehicle having increased storage capacity inside the duct for equipment and electronics provides improved airflow and fan efficiency over ducted fan air vehicles carrying cargo in external pods. The outside of the duct may extend outwardly to allow equipment and electronics to be stored inside the duct in storage areas located at intervals along the duct. The storage areas may form a square duct having a circular inside wall. Additionally, the storage areas may extend in the direction of the axis of rotation of the fan to provide additional storage above the lower lip of the duct. | 09-20-2012 |
20130068895 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 03-21-2013 |
20130105635 | QUAD TILT ROTOR VERTICAL TAKE OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV) WITH 45 DEGREE ROTORS | 05-02-2013 |
20130126680 | UNMANNED AIR VEHICLE FAULT TOLERANT FLIGHT CONTROL SYSTEM AND METHOD - Methods and apparatus are provided for controlling an unmanned air vehicle (UAV) that includes a plurality of independently controllable control vanes. Control vane position commands are supplied that will move each of the control vanes to a position that will cause the UAV to implement a commanded maneuver. Inoperability of one of the control vanes is sensed, and the position of the inoperable control vane is determined New control vane position commands are determined, based on the determined position of the inoperable control vane, which will also cause the UAV to implement the commanded maneuver. | 05-23-2013 |
20130134263 | WINGLESS HOVERING OF MICRO AIR VEHICLE - Embodiments of the subject invention relate to an air vehicle and a power source. Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | 05-30-2013 |
20130140404 | SYSTEM AND METHOD FOR IMPROVING TRANSITION LIFT-FAN PERFORMANCE - A system and method enabled to increase efficiency during a VTOL aircraft's transition. A VTOL aircraft enabled to operate multiple lift fans arranged into separately controllable groups, wherein the VTOL aircraft initially has vertical flight but transitions to horizontal flight. A first group of lift fans may be kept at full throttle, a second group of lift fans may be throttled to balance thrust and/or weight, and a third group of lift fans may be shut off. | 06-06-2013 |
20130206919 | SYSTEMS AND METHODS FOR CONTROLLING AN AERIAL UNIT - An aerial unit that includes a first propeller; a second propeller that is spaced apart from the first propeller and is below the first propeller; a propelling module that is configured to rotate the first propeller and the second propeller about a first axis; an apertured duct that comprises a first duct portion and a second duct portion. The first duct portion surrounds the first propeller. The second duct portion surrounds the second propeller. The apertured duct defines at least one aperture at an intermediate area that is positioned below the first propeller and is above the second propeller. The aggregate size of the at least one aperture is at least fifty percent of a size of the intermediate area; a frame; and at least one steering element; an interfacing module arranged to be connected to a connecting element that couples the aerial unit to a ground unit. The propelling module and the duct are connected to the frame. | 08-15-2013 |
20140048657 | CROSS FLOW FAN FLYING DEVICE - A cross flow fan flying device includes a first thrusting means having a first cross flow fan and a second thrusting means having a second cross flow fan, wherein the first flow fan and the second cross flow fan rotate in directions opposite with each other, and the cross flow fan flying device is driven and flies by airflow thrust generated by the first cross flow fan and the second cross flow fan. | 02-20-2014 |
20140158832 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 06-12-2014 |
20140263849 | PERSONAL PROPULSION DEVICES WITH IMPROVED BALANCE - A personal propulsion device, including a platform configured to support a passenger's body; and at least one fluid discharge nozzle coupled to the platform and angled with respect to the platform, where the angle defined between the nozzle and the platform is between approximately 95° and 120°; where the personal propulsion device is configured to receive pressurized fluid from a remote pressurized fluid source, and where the personal propulsion device is configured to achieve flight. | 09-18-2014 |
20140332634 | MULTI-PURPOSE PERSONAL PROPULSION SYSTEM - A personal propulsion system, including an assembly adapted to support a passenger and achieve flight through the discharge of pressurized fluid; and a pressurized fluid source in fluid communication with the assembly, where the pressurized fluid source does not achieve flight, and where the pressurized fluid source is constructed at least in part from one or more ballistic armor materials. | 11-13-2014 |
20140332635 | TANDEM PERSONAL PROPULSION DEVICE - A personal propulsion device, including a passenger assembly configured to support a plurality of passengers, the passenger assembly including one or more nozzles adapted to discharge pressurized fluid; and a pressurized fluid source in fluid communication with the passenger assembly, where the passenger assembly is capable of achieving flight by discharging pressurized fluid provided by the pressurized fluid source. The pressurized fluid source may be a personal watercraft, and the passenger assembly may be configured to support two passengers positioned side-by-side, one in front of the other, or facing different directions. | 11-13-2014 |
20150053826 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - There is provided a vertical take-off and landing aircraft including: a propulsion mechanism for generating lift and thrust; a power supply unit (e.g. an engine as a power source) for supplying power to the propulsion mechanism; a main frame for supporting the engine, a seat, and a landing undercarriage; a sub-frame for supporting the propulsion mechanism; a frame coupling unit for rotatably coupling the main frame and the sub-frame; and a control stick connected to the sub-frame, so that an occupant sitting on a seat operates a control stick thereby to move the sub-frame relative to the main frame so as to change the orientation of the propulsion mechanism. | 02-26-2015 |
20150108282 | FLOATING MOBILE OBJECT AND FLOATING MOBILE SYSTEM USING THE SAME - A holonomic floating mobile object is operated under gravity and includes a main body and six or more thrusters for generating thrust by changing the momentum of a fluid. The six or more thrusters are controlled independently of one another such that the thrust is set at a desired value. The six or more thrusters are arranged in a fuselage coordinate system defined on the main body, such that the range in which a total thrust vector obtained by combining vectors of the thrust generated by all of the thrusters can be generated spans a six-dimensional space with three directions of translation and three directions of rotation. Incoming and outgoing flows to and from one of the thrusters are spaced apart from incoming and outgoing flows to and from the other thrusters and even apart from every other fuselage structure aside from that one thruster. | 04-23-2015 |
20150360776 | VERTICAL TAKE-OFF AND LANDING AERIAL VEHICLE - A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The control system being able to control the orientation of the inner frame. The gimbal system connecting the inner frame to the outer frame with at least two rotation axis allowing rotation freedom between the outer frame to rotate independently from the inner frame. | 12-17-2015 |
20160101852 | Annular ducted lift fan VTOL aircraft - The invention is an annular ducted lift fan system for a VTOL type aircraft. In detail, the invention comprises an annular duct, a lift fan set, engines, a central fuselage, a peripheral wing, and means for pneumatic coupling or mechanic coupling of engines and the lift fan set. The lift fan set is mounted in the annular duct and powered by the engines through pneumatic coupling or mechanic coupling. The annular duct is opened with the lift fan set working to provide high lift efficiency in VTOL mode and transition mode and is closed off to reduce drag in cruise mode. | 04-14-2016 |
20160376002 | Aircraft with Rotating Outer Shell - An aircraft having a main body defining a passenger compartment therein, an upper shell portion above the main body and a lower shell portion below the main body, further includes a motor assembly operatively connected between the upper shell portion, the lower shell portion and the main body so as to be arranged to drive rotation of the upper and lower shell portions relative to the main body in opposing directions relative to one another. An engine assembly is supported on the main body in communication with a central thrust opening in the lower shell portion so as to be arranged to provide upward thrust to the main body. | 12-29-2016 |
20180022467 | SINGLE ENGINE, ASYMMETRICAL VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT | 01-25-2018 |
20090140102 | Ducted fan vehicles particularly useful as VTOL aircraft - A vehicle, including a vehicle frame, a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame, a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid therethrough from its inlet at the upper end of the duct through its exit at the lower end of the duct, and thereby to produce an upward lift force applied to the vehicle, and a plurality of parallel, spaced vanes pivotally mounted to and across the inlet end of the duct about pivotal axes perpendicular to the longitudinal axis of the duct and substantially parallel to the longitudinal axis of the vehicle frame, the vanes being selectively pivotal about their axes to produce a desired horizontal force component to the lift force applied to the vehicle. | 06-04-2009 |
20090140103 | Vehicle with vertical lift - An apparatus for producing vertical lift in a vehicle. In one embodiment, two sets of trans-flow fans discharge air through multi-directional vane assemblies that direct the discharged air outward and downward. Each one of the sets of fans is positioned on opposite sides of the vehicle. The multi-directional vane assemblies include vertical vanes that direct the discharged air fore and aft and horizontal vanes that direct the discharged air downward at various angles. In one embodiment, the vehicle includes a hovercraft skirt and a portion of the discharge air is directed into the skirt, causing the vehicle lift vertically on a cushion of air. In one such embodiment, a flow director controls the amount of discharged air flowing through the inlet to the volume defined by the skirt. | 06-04-2009 |
20110180671 | DIFFERENTIAL VANE VEHICLE CONTROL - A ducted fan air-vehicle capable of generating control moments. The ducted fan air-vehicle includes an air duct, a fan, a center body, a plurality of control vanes. The vanes are independently controlled and are deflected in the same direction but at different angles, thereby providing an increased control moments to the vehicle compared to the prior art. The increased pitching moment allows for additional control authority. Additional control authority is useful in forward flight and is especially desirable when the ducted fan air-vehicle is maneuvering in unsteady or turbulent winds or with various types of cargo that may effect the vehicle center of gravity location. | 07-28-2011 |
20140054423 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 02-27-2014 |
20140061390 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 03-06-2014 |
244023000 | Lifting thrusters | 47 |
20080302920 | Aerial Lifting and Propulsion Device (ALPD) - This invention, an Aerial Lifting and Propulsion Device, introduces an aircraft and aircraft wing design that has an outer and inner circumference, both of which are employed in the entirety of each to evacuate air, air space, and/or atmosphere from above the circular wing/craft, to the area beneath the circular wing/craft, through the use of a propeller inside the inner circumference of the circular wing, and impellers at the outer circumference of the circular wing. When the air, air space, and/or atmosphere forced from above the circular wing into the area beneath the circular wing and propeller attempts to escape to the top of the circular wing to fill the newly created low pressure area above the circular wing, it is intercepted at the lower edge of the outer circumference of the circular wing and forced to returned to the area beneath the circular wing, where the atmospheric pressure is further increased or decreased at will, depending on the pitch and speed of the aircraft propeller and impeller blades. The noted reduced atmospheric pressure at the top of the circular wing, and the higher controlled atmospheric pressure in the area beneath the circular wing and propeller, forces the circular wing upward from its stationary position, achieving lift as described in Bernoulli's Principle. Stabilization and directional control is maintained through adjustments in the pitch of the impeller and propeller and the effects of torque are neutralized by the rotation of the impeller and propeller assemblies in opposite directions. The Aerial Lifting and Propulsion Device maintains its upright configuration while airborne in part because its center of gravity is well below the points where lift is generated. | 12-11-2008 |
20090084907 | Ground Effect Vanes Arrangement - A vehicle, particularly a VTOL air vehicle, includes a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame; a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid therethrough from its inlet at the upper end of the duct through its exit at the lower end of the duct, and thereby to produce an upward lift force applied to the vehicle, and a plurality of spaced vanes mounted to and across the inlet and exit ends of the duct about axes substantially perpendicular to the longitudinal axis of the duct and selectively operational to produce a desired horizontal control force in addition to the lift force applied to the vehicle. | 04-02-2009 |
20100001143 | Discoidal flying craft - A flying craft has an aerodynamic aircraft fuselage structure preferably disc shaped. A pair of coaxial electrokinetic motor-generators are mounted concentrically, and preferably centered within the disc shaped structure of the craft. Each of the motors is toroidal in configuration, providing a ring-shaped stator and rotor portions. The rotor portions of the motors drive counter rotating fans which are electro-magnetically levitated. The structure is open to the fans so that air may be drawn into the structure and expelled downward providing vertical lift to the aircraft. By use of auxiliary air braking flaps and electrokinetic thrusters, the craft may be tilted so as to develop a desired horizontal thrust. By impulse breaking one of the fans through tracking solenoids at different points around the stator, the aircraft may be made to rotate about its own vertical axis for changing direction. By a series of sudden braking of the motors the craft may be made to move by inertial reaction. | 01-07-2010 |
20120068021 | CRAFT AND METHOD FOR ASSEMBLING CRAFT WITH CONTROLLED SPIN - This invention relates to a craft designed to move through or on a surface of a fluid. It is believed to be principally of use in relation to airborne craft and missiles but the theory behind the invention is equally applicable for example to submarines. | 03-22-2012 |
20140027581 | AIRCRAFT HAVING A ROTATING TURBINE ENGINE - The present invention describes an aircraft having a rotating engine. The aircraft comprises a means for rotating the engine 360° to allow directional control of the aircraft via rotation of the engine's thrust output. The aircraft can further comprise a plurality of flap members located on the wings of the aircraft and in communication with the rotating gas turbine engine to further control and stabilize flight of the aircraft. The gas turbine engine of the aircraft can comprise a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating more thrust from a single engine. | 01-30-2014 |
20150028161 | Hydraulic Passenger Lifting and Maneuvering Device - This invention relates to a fluid driven propulsion device comprising a body arranged in a manner to facilitate flight and lift for a person, passenger or object(s) with a production of thrust from a portable or fixed power unit. A power unit is designated to move an incompressible fluid via pump through a flexible pipe or transmission tube to two or more pairs of restrictive axially offset nozzles within the embodiment of the invention allowing the incompressible fluid's pressure to build and its mass to be ejected underneath the person, passenger or object(s). This fluid is expelled with such velocity to create a force, directed into multiple, generally symmetrical force vectors, sufficient to facilitate balanced, easy to master free-flight. The invention also allows for powered, active inward and outward adjustment of the axially offset pairs of nozzles, as well as powered, active aperture adjustment of each of the nozzle outlets. | 01-29-2015 |
20160144960 | PERSONAL FLUID-JET THRUST PACK WHICH PROVIDES ROTATION FOR A RIDER ABOUT THREE AXES - The present invention provides lightweight fluid-jet thrust pack which provides three rotational axes and reduced restriction of fluid flow to the output nozzles. A first rotational axis is provided by a first rotatable coupling that is concentric with a coupler for a hose supplying pressurized fluid. The top of the first coupling has a splitter which directs incoming fluid into two splayed stub supply pipes. A preformed, reinforced rubber hose connects each stub supply pipe to one of a pair of coaxial rotatable couplings at opposite ends of a tiltable cross arm assembly that is pivotally secured to tower support bracket that is secured to the first rotatable coupling. An outward rotatable portion of each of the coaxial rotatable couplings is equipped with one boot-mounting platform and a downward-projecting jet nozzle that is in communication with the stub receiver pipe of the same rotatable coupling. | 05-26-2016 |
20160152338 | AN AERODYNAMIC LIFTING DEVICE | 06-02-2016 |
20090236475 | LIFT CHAMBER - A lift device having a generally cylindrical chamber formed by a top wall, a bottom wall, an outer wall and an inner wall. A plurality of lift members are mounted to the interior of a chamber wall and at least one fan is mounted within the chamber and an engine operatively connected to at lease one fan. | 09-24-2009 |
20100025540 | Compact ultralight aircraft reduced dimensions, with vertical take-off and landing - A compact ultralight aircraft ( | 02-04-2010 |
20100051754 | Aircraft - An aircraft has a generally circular main body including an upper surface portion supported for rotation about a central passenger compartment to produce a gyroscopic effect on the aircraft. The rotatable upper surface portion includes viewable panes therein arranged to provide visibility therethrough from the central passenger compartment to an exterior of the main body. An engine communicates between a central inlet opening in the upper surface portion and an exhaust opening in the bottom of the main body to provide upward thrust to the aircraft. | 03-04-2010 |
20100102174 | Wingless Hovering Of Micro Air Vehicle - Embodiments of the subject invention relate to a Wingless Hovering Micro Air Vehicle (WHOMAV) and its Power Source Unit (PSU). Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments of the subject invention can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | 04-29-2010 |
20100187369 | DUCTED FAN UAV CONTROL ALTERNATIVES - A ducted fan air-vehicle having alternative methods of control is described. The ducted fan air-vehicle includes an air duct, a fan, a center body, a plurality of control vanes. Each control vanes includes a separate servo for independent control of each control vane, and is therefore able to operate the control vanes in a non-traditional manner to provide maximum control authority. | 07-29-2010 |
20100282918 | Saucer shaped gyroscopically stabilized vertical take-off and landing aircraft - An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating sine-wave ring is used to activate and move a plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere. | 11-11-2010 |
20100288889 | SPRING FLYING DEVICE - The Spring flying device ( | 11-18-2010 |
20130181095 | DEVICE TO GENERATE LIFT FORCE (OPTIONS) - The options of the invention relate to the aviation and can be used in order to create lifting vehicle as well as load lifting devices. In order to achieve technical result—the decrease of energy losses on the while creating and change of vector of moving, aerodynamic, composite force, including as a component a lift force,—in the device to generate lift force containing a tubiform frame, superchargers, the wings having in section an aerofoil profile oriented by the leading edge to the direction of working medium exhaust out of the super-charger, adjusting units for a wing, guiding devices, each of those is installed in front of leading edge of each wing, the system to maintain the required working temperature of medium, unit to connect outdoor environment, as per the invention in the first option of the device a tubiform frame is of the form of a tore, in the second option—the form of closed volumetric loop, in the third option—a cylindrical form. Meanwhile each option of the device is equipped with relevant distinguishing units, providing the achieving of a technical result. | 07-18-2013 |
20130306802 | METHODS AND APPARATUS FOR VERTICAL SHORT TAKEOFF AND LANDING - Methods and apparatus for vertical or short takeoff and landing. In one embodiment, the apparatus comprises two or more counter driven rings with one or more airfoils attached. In one variant, there is an upper ring and a lower ring, each with multiple airfoils attached. In one variant, lift is generated largely via ambient air currents, allowing for long term on-station operation of the device. | 11-21-2013 |
20130306803 | AIRCRAFT GENERATING A LIFT FROM AN INTERIOR THEREOF - The invention discloses an aircraft generating a larger lift from its interior. The fluid channel inside the aircraft communicates with the engine and the ports on the upper surface of the outer shell. With the powerful suction of the engine, the fluid on the upper surface of the outer shell is quickly sucked into the fluid channel via respective ports under conditions of long path, large area, high speed and low air pressure, which results in large lift from the interior of the aircraft. In the course of generating the lift, the fluid resistances of the fluid wall and the fluid hole are sucked into the fluid channel through the ports at the front and the surrounding area of the aircraft, then high-speed fluid is emitted from the rear port. This approach contributes greatly to the transformation of the existing aircraft. The unified big wing significantly improves the lift, the speed and the carrying capacity of the existing aircraft with lowered energy consumption. | 11-21-2013 |
20090039206 | BIRD VORTEX FLYING MACHINE - The present invention comprises, in one embodiment, an inexpensive, lightweight flying vehicle using fixed pitch helicopter blades powered by ramjet engines mounted to a power-ring which transfers torque to the lifting rotors. The use of fixed pitch blades eliminates the need for a tail boom and tail rotor, as well as for variable incidence control of blade pitch and/or cyclic and collective rotor-pitch controls. An optional ballistic parachute may be deployed for emergency landings. A radial shroud encloses the ramjet engines to act as a sound shield. Since the rotor has a fixed pitch, lift may be controlled by rotor speed, where increased speed results in ascent, and decreased speed, descent. | 02-12-2009 |
20100193643 | LIFT FAN SYSTEM - Embodiments of the present invention include a system, e.g., for a short takeoff and vertical landing (STOVL) aircraft. The system includes a power generator, such as a gas turbine engine; a lift fan powered by the power generator; and includes two or more nozzles in fluid communication with the lift fan. | 08-05-2010 |
20110204188 | ROTOCRAFT - An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle. | 08-25-2011 |
20140077039 | Heated Screen For Air Intake Of Aircraft Engines - An aircraft includes a fuselage and wings mounted on opposite sides of the fuselage for sustained forward flight. An engine is mounted in the fuselage or at least one of the wings and includes an air intake. At least a portion of the air intake generally faces the forward direction for receiving intake air during forward flight. A filter assembly is mounted adjacent the air intake and disposed to impinge air and block objects from passing therethrough. A heated screen includes a heater and is mounted adjacent the air intake and upstream of the engine such that ice entering the air intake contacts the heated screen before entering the engine. A power source is provided to supply power to the heater. | 03-20-2014 |
20190144108 | Aircraft having Hover Stability in Inclined Flight Attitudes | 05-16-2019 |
20080223993 | HOMEOSTATIC FLYING HOVERCRAFT - A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control. | 09-18-2008 |
20080283673 | Ducted Fan Vtol Vehicles - A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | 11-20-2008 |
20090020654 | Harness with mounted engine frame - A harness with mounted engine frame comprises a harness to be worn by a user. An engine support arm is mounted on the harness and a pair of lateral arms extend from the engine support arm. At least one engine is associated with each lateral arm. A connector attaches directly or indirectly to the harness for receiving the engine support arm, so that the engine support arm is movable relative to the harness in response to engine output and other flight conditions. | 01-22-2009 |
20090121087 | High speed vertical take-off and land aircraft with active fan balancing system - A high-speed vertical take-off and land aircraft includes a body with an engine supported by the body. A fan assembly is also carried by the body. The fan assembly includes a hub and a plurality of blades to provide vertical lift for the aircraft. A nozzle ring is provided on the fan assembly. The nozzle ring includes an annular nozzle array. Hot gases from the engine are fed to the nozzle array by a feed duct. A bearing mechanism supports the fan assembly on the body. The bearing mechanism is carried in a work space. A brush seal assembly thermally isolates the work space from the hot exhaust gases passing through the feed duct to the nozzle array. | 05-14-2009 |
20090159757 | Ducted Fan Vtol Vehicles - A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | 06-25-2009 |
20090250557 | Whirling Wheel Airborne Vehicles - A sliding-arm whirling wheel thruster includes first and second whirling wheels and a housing. The first whirling wheel is disposed about a first rotational axis, and the second whirling wheel about a second rotational axis parallel to the first rotational axis. The housing comprises an arc over an enclosed space into which the first and second whirling wheels fit. The air blown outward by each of the whirling wheels is amassed inside the housing so as to make a pressure difference between inside and outside of the housing. The relative position of the first rotational axis to the second rotational axis is configured to be controlled. The airborne vehicle is lifted by buoyant force caused by the pressure difference. | 10-08-2009 |
20100012790 | GYRO-STABILIZED AIR VEHICLE - A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage. | 01-21-2010 |
20100019098 | Ducted Fan Core for Use with an Unmanned Aerial Vehicle - A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame, attached to which are an engine, gearbox assembly, fan, and a plurality of control vanes. A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle. | 01-28-2010 |
20100051753 | WALL EFFECTS ON VTOL VEHICLES - ducted air flow vehicle that includes a fuselage having a longitudinal axis, supporting at least one air flow duct and a prime mover arranged to force surrounding air into the duct through an inlet at an upper end of the duct with normally symmetrical airflow streams, thereby creating a lift force directed substantially along a duct axis; a plurality of vanes extending across the inlet, substantially parallel to the longitudinal axis; and wherein one or more groups of the vanes are selectively pivotable to align with adjacent abnormal asymmetrical airflow streams. | 03-04-2010 |
20100078523 | Tandem powered power tilting tilt rotor aircraft - An aircraft with a long body | 04-01-2010 |
20100127131 | System and Method For a Fuel Bladder Assembly With Embossed Film - Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto. The fuel bladder may include an embossed pattern disposed to prevent a vacuum being formed by the collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV). | 05-27-2010 |
20100140415 | VERTICAL TAKE OFF AND LANDING UNMANNED AERIAL VEHICLE AIRFRAME STRUCTURE - An unmanned aerial vehicle selectively formed of high strength composite structural part portions and lightweight aerodynamic foam portions to provide a low-cost and lightweight UAV that comports with export, civil airspace, and safety regulations. To further to reduce an overall weight of the UAV, mechanical elements are designed to provide multiple functionalities. Structural elements may be manufactured in same or similar non-specialized processes, and non-structural elements manufactured in same or similar non-specialized processes, reducing overall manufacturing costs. Materials and bonding elements are selected to provide frangibility and yet maintain normal flight structural integrity. | 06-10-2010 |
20100140416 | Ducted Fans with Flow Control Synthetic Jet Actuators and Methods for Ducted Fan Force and Moment Control - The present invention relates to the field of aerodynamics. More particularly, the present invention relates to manipulating air flow over a surface, such as the surface of a duct of a ducted fan vehicle. By controlling air flow over, at, or around the surface of a duct, the flight of the vehicle can be controlled. One embodiment of the invention provides a vertical take-off and landing (VTOL) ducted-fan vehicle comprising means for producing steady or unsteady blowing at a surface of a duct for producing control forces and moments for controlling flight. The means for unsteady blowing can be provided by synthetic jets and the means for steady blowing can be provided by a pressurized air supply. The synthetic jets can be integrated into the ducted-fan vehicles in numerous ways, including at the surface of the leading and/or trailing edge of the ducts. The synthetic jets can be independently operated to control the flight of the vehicle. A novel use of these inventive flow control concepts is to apply the control asymmetrically to the duct in order to produce an imbalance in forces, thus resulting in a moment or torque, which can be used to control flight. | 06-10-2010 |
20100171000 | Tandem powered tilt rotor aircraft - An aircraft with a long body | 07-08-2010 |
20100320333 | Saucer-shaped gyroscopically stabilized vertical take-off and landing aircraft - An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating plate includes a groove that traces a sinusoidal pattern around an inside periphery of the plate. Tracking arms have a portion that fit within the groove and another portion that connects to a piston. The rotation of the plate causes the tracking arms to travel within the sinusoidal groove and impart movement on the plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere. | 12-23-2010 |
20110001017 | UAV DUCTED FAN SWEPT AND LEAN STATOR DESIGN - A ducted fan air-vehicle having an air duct and a fan is described. The air duct includes an outer rim and an inner rim, and the fan is located within the air duct and rotates in a direction. The fan also includes a hub, a plurality of struts extending from the hub and positioned adjacent the outer rim of the fan, a plurality of stators extending from the hub and positioned adjacent the inner rim of the fan, and a plurality of rotor blades extending from the hub and positioned between the plurality of struts and the plurality of stators. The stators are lean in a plane of fan rotation and swept in a plane normal to fan rotation to create the optimum amount of noise reduction in the ducted fan air-vehicle. | 01-06-2011 |
20110049306 | CONTROL FLOWS AND FORCES IN VTOL VEHICLES - The present application relates to VTOL vehicles with multi-function capabilities and, specifically to ducted fan arrangements that facilitate the control of forces and flows of air to control movement of the vehicle in six degrees of freedom in both primary and secondary modes of operation. Also disclosed are pitch control mechanisms for the lift propellers of VTOL vehicles: drive and transmission arrangements; a specially configured exhaust duct for directing exhaust gases from such vehicles along an upper surface of the vehicle; and shock absorbing components for the landing gear of such vehicles. | 03-03-2011 |
20110049307 | VTOL VEHICLE WITH OFFSET ENGINE - A ducted air flow vehicle includes a fuselage having a longitudinal axis, supporting forward and aft air flow ducts having respective lift fans arranged to force surrounding air into said ducts through inlets at upper ends of said ducts and out of said ducts through outlets at lower ends of said ducts, thereby creating a lift force. A single engine is located on one side of said longitudinal axis, and is operatively configured to power the lift fans. A payload bay is located in a central area of said fuselage, between the forward and aft ducts, spanning the longitudinal axis. | 03-03-2011 |
20110139939 | PERSONAL FLIGHT DEVICE INCORPORATING RADIATOR COOLING PASSAGE - A personal flight device which includes: a housing which is securable to a pilot; at least one pair of ducted fans, one fan of the pair mounted to one side of the housing, the other fan of the pair mounted to the other side of the housing; wherein each fan rotates about an axis of rotation so as to draw air through the corresponding duct from an entry end of the duct to an exit end of the duct; and wherein the axis of rotation of each fan is fixed relative to the housing; at least one engine mounted on the housing for driving the fans such that both fans rotate in the same direction for producing thrust; the or each engine being cooled by a radiator; the or each radiator being associated with at least one passage having an entry end in communication with one surface of the radiator and an exit end adjacent the entry end of one of said ducts. | 06-16-2011 |
20110147533 | MORPHING DUCTED FAN FOR VERTICAL TAKE-OFF AND LANDING VEHICLE - A morphing duct of a ducted fan for a vertical take-off and landing (VTOL) vehicle is configured to change shape as function of the flight mode of the vehicle to improve the thrust per unit energy input for the ducted fan. Additionally, the morphing duct may be configured to change shape to change the flight path of the VTOL vehicle. | 06-23-2011 |
20110155859 | AIRCRAFT VERTICAL LIFT DEVICE - A lift device is disclosed that can be used to provide vertical lift to an aircraft or other vehicle. The lift device can include a fan that produces an airflow and a vane box that can direct the airflow. In one form the fan can be oriented at an angle relative to a reference plane in the aircraft. In another form the vane box can be oriented at an angle. The vane box can be structured to provide a maximum flow area between an aft flow vector and a forward flow vector. | 06-30-2011 |
20110155860 | FLUID DYNAMIC DEVICE WITH THRUST CONTROL SHROUD - A fluid dynamic device ( | 06-30-2011 |
20110210212 | Tilt rotor aircraft with tilting tail rotor - TT - A vertical take-off aircraft comprising a main power plant | 09-01-2011 |
20110266397 | SOLAR THERMAL ROTORCRAFT - A vehicle includes a housing having a wall with a central port and radial port formed at a lower portion of the housing, a blower disposed within the housing to move air through the central port, a distributor coupled to the blower to distribute air inside the housing, a heat-absorbing body disposed within the housing to absorb thermal energy, and at least one arm coupled to the housing. | 11-03-2011 |
20120056040 | Electric VTOL Aircraft - An electric and hybrid Vertical-Take Off and Landing (“VTOL”) aircraft is disclosed comprising a plurality of small Electric Ducted Fans (“EDFs”) of various sizes and orientations. The thrust of each fixed EDF is individually controlled by modulation of motor power by one or more onboard microcomputers connected to a plurality of onboard laser distance measuring sensors, at least three onboard three-axis accelerometers and at least one GPS thereby allowing extremely precise and safe VTOL operation. The aircraft may be employed to allow robotic and passenger vehicles to transition extremely quickly between normal linear flight and VTOL and tb operate in extreme and gusty conditions. | 03-08-2012 |
20120080564 | DUCTED PLATFORMS - A ducted fan for a VTOL vehicle includes a substantially cylindrical duct having an inlet at an upper end and an outlet at a lower end, and an air mover unit located within the substantially cylindrical duct. The duct also includes inner and outer wall portions and a substantially annular upper lip connecting the inner and outer wall portions, thus defining the inlet. The substantially annular upper lip has opposed fore and aft portions and opposed side portions and is provided with at least first and second openings, respectively, at each of the opposed side portions. The first and second arrays of openings permit flow of air into at least first and second respective chambers formed within the duct, the first and second chambers connected by at least one passageway to thereby enable substantial equalization of surface pressure at the opposed side portions of the substantially annular upper lip. | 04-05-2012 |
20120091284 | UNMANNED AERIAL VEHICLE - The various embodiments of the present invention provide an unmanned aerial vehicle comprising a hemispherical body, a brushless type electrical, a propeller, a plurality of wingtip devices, a plurality of servomotors and each of the plurality of the servomotors is connected to each of the plurality of the wingtip devices respectively, a plurality of carbon rods, and a casing. The brushless type electrical motor provides a lifting force for a Vertical take-off and landing (VTOL) and the plurality of wing tip devices are classified into three types of wing tip devices and the three types of wing tip devices are controlled by the respective servomotors to control yaw, pitch and roll movements thereby stabilizing and controlling the movement of an aircraft. | 04-19-2012 |
20120126064 | UAV DUCTED FAN LIP SHAPING - A ducted fan air-vehicle having a duct lip shape is described. The duct lip has an internal duct lip portion and an external duct lip portion, both of which are substantially curvature continuous around the circumference of the air duct. The duct has a plurality of cross-sections along its circumference and at least some of the plurality of cross-sections have a different shape. Further, each cross-section around the circumference of the duct has an a/b ratio and the a/b ratio for each cross-section is substantially the same. | 05-24-2012 |
20120153087 | Modular Pods for Use with an Unmanned Aerial Vehicle - A pod for an unmanned aerial vehicle is provided that may be removed and re-attached to the vehicle. The pod comprises an outer shell, within which a variety of payloads may be carried. A first surface on the vehicle frame comprises a plurality of connects or electrical traces. The plurality of attachments are used to removably attach the pods to the first surface. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle. | 06-21-2012 |
20120234984 | Integrated Duct Design for an Unmanned Aerial Vehicle - A ducted fan air vehicle having increased storage capacity inside the duct for equipment and electronics provides improved airflow and fan efficiency over ducted fan air vehicles carrying cargo in external pods. The outside of the duct may extend outwardly to allow equipment and electronics to be stored inside the duct in storage areas located at intervals along the duct. The storage areas may form a square duct having a circular inside wall. Additionally, the storage areas may extend in the direction of the axis of rotation of the fan to provide additional storage above the lower lip of the duct. | 09-20-2012 |
20130068895 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 03-21-2013 |
20130105635 | QUAD TILT ROTOR VERTICAL TAKE OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV) WITH 45 DEGREE ROTORS | 05-02-2013 |
20130126680 | UNMANNED AIR VEHICLE FAULT TOLERANT FLIGHT CONTROL SYSTEM AND METHOD - Methods and apparatus are provided for controlling an unmanned air vehicle (UAV) that includes a plurality of independently controllable control vanes. Control vane position commands are supplied that will move each of the control vanes to a position that will cause the UAV to implement a commanded maneuver. Inoperability of one of the control vanes is sensed, and the position of the inoperable control vane is determined New control vane position commands are determined, based on the determined position of the inoperable control vane, which will also cause the UAV to implement the commanded maneuver. | 05-23-2013 |
20130134263 | WINGLESS HOVERING OF MICRO AIR VEHICLE - Embodiments of the subject invention relate to an air vehicle and a power source. Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | 05-30-2013 |
20130140404 | SYSTEM AND METHOD FOR IMPROVING TRANSITION LIFT-FAN PERFORMANCE - A system and method enabled to increase efficiency during a VTOL aircraft's transition. A VTOL aircraft enabled to operate multiple lift fans arranged into separately controllable groups, wherein the VTOL aircraft initially has vertical flight but transitions to horizontal flight. A first group of lift fans may be kept at full throttle, a second group of lift fans may be throttled to balance thrust and/or weight, and a third group of lift fans may be shut off. | 06-06-2013 |
20130206919 | SYSTEMS AND METHODS FOR CONTROLLING AN AERIAL UNIT - An aerial unit that includes a first propeller; a second propeller that is spaced apart from the first propeller and is below the first propeller; a propelling module that is configured to rotate the first propeller and the second propeller about a first axis; an apertured duct that comprises a first duct portion and a second duct portion. The first duct portion surrounds the first propeller. The second duct portion surrounds the second propeller. The apertured duct defines at least one aperture at an intermediate area that is positioned below the first propeller and is above the second propeller. The aggregate size of the at least one aperture is at least fifty percent of a size of the intermediate area; a frame; and at least one steering element; an interfacing module arranged to be connected to a connecting element that couples the aerial unit to a ground unit. The propelling module and the duct are connected to the frame. | 08-15-2013 |
20140048657 | CROSS FLOW FAN FLYING DEVICE - A cross flow fan flying device includes a first thrusting means having a first cross flow fan and a second thrusting means having a second cross flow fan, wherein the first flow fan and the second cross flow fan rotate in directions opposite with each other, and the cross flow fan flying device is driven and flies by airflow thrust generated by the first cross flow fan and the second cross flow fan. | 02-20-2014 |
20140158832 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 06-12-2014 |
20140263849 | PERSONAL PROPULSION DEVICES WITH IMPROVED BALANCE - A personal propulsion device, including a platform configured to support a passenger's body; and at least one fluid discharge nozzle coupled to the platform and angled with respect to the platform, where the angle defined between the nozzle and the platform is between approximately 95° and 120°; where the personal propulsion device is configured to receive pressurized fluid from a remote pressurized fluid source, and where the personal propulsion device is configured to achieve flight. | 09-18-2014 |
20140332634 | MULTI-PURPOSE PERSONAL PROPULSION SYSTEM - A personal propulsion system, including an assembly adapted to support a passenger and achieve flight through the discharge of pressurized fluid; and a pressurized fluid source in fluid communication with the assembly, where the pressurized fluid source does not achieve flight, and where the pressurized fluid source is constructed at least in part from one or more ballistic armor materials. | 11-13-2014 |
20140332635 | TANDEM PERSONAL PROPULSION DEVICE - A personal propulsion device, including a passenger assembly configured to support a plurality of passengers, the passenger assembly including one or more nozzles adapted to discharge pressurized fluid; and a pressurized fluid source in fluid communication with the passenger assembly, where the passenger assembly is capable of achieving flight by discharging pressurized fluid provided by the pressurized fluid source. The pressurized fluid source may be a personal watercraft, and the passenger assembly may be configured to support two passengers positioned side-by-side, one in front of the other, or facing different directions. | 11-13-2014 |
20150053826 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - There is provided a vertical take-off and landing aircraft including: a propulsion mechanism for generating lift and thrust; a power supply unit (e.g. an engine as a power source) for supplying power to the propulsion mechanism; a main frame for supporting the engine, a seat, and a landing undercarriage; a sub-frame for supporting the propulsion mechanism; a frame coupling unit for rotatably coupling the main frame and the sub-frame; and a control stick connected to the sub-frame, so that an occupant sitting on a seat operates a control stick thereby to move the sub-frame relative to the main frame so as to change the orientation of the propulsion mechanism. | 02-26-2015 |
20150108282 | FLOATING MOBILE OBJECT AND FLOATING MOBILE SYSTEM USING THE SAME - A holonomic floating mobile object is operated under gravity and includes a main body and six or more thrusters for generating thrust by changing the momentum of a fluid. The six or more thrusters are controlled independently of one another such that the thrust is set at a desired value. The six or more thrusters are arranged in a fuselage coordinate system defined on the main body, such that the range in which a total thrust vector obtained by combining vectors of the thrust generated by all of the thrusters can be generated spans a six-dimensional space with three directions of translation and three directions of rotation. Incoming and outgoing flows to and from one of the thrusters are spaced apart from incoming and outgoing flows to and from the other thrusters and even apart from every other fuselage structure aside from that one thruster. | 04-23-2015 |
20150360776 | VERTICAL TAKE-OFF AND LANDING AERIAL VEHICLE - A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The control system being able to control the orientation of the inner frame. The gimbal system connecting the inner frame to the outer frame with at least two rotation axis allowing rotation freedom between the outer frame to rotate independently from the inner frame. | 12-17-2015 |
20160101852 | Annular ducted lift fan VTOL aircraft - The invention is an annular ducted lift fan system for a VTOL type aircraft. In detail, the invention comprises an annular duct, a lift fan set, engines, a central fuselage, a peripheral wing, and means for pneumatic coupling or mechanic coupling of engines and the lift fan set. The lift fan set is mounted in the annular duct and powered by the engines through pneumatic coupling or mechanic coupling. The annular duct is opened with the lift fan set working to provide high lift efficiency in VTOL mode and transition mode and is closed off to reduce drag in cruise mode. | 04-14-2016 |
20160376002 | Aircraft with Rotating Outer Shell - An aircraft having a main body defining a passenger compartment therein, an upper shell portion above the main body and a lower shell portion below the main body, further includes a motor assembly operatively connected between the upper shell portion, the lower shell portion and the main body so as to be arranged to drive rotation of the upper and lower shell portions relative to the main body in opposing directions relative to one another. An engine assembly is supported on the main body in communication with a central thrust opening in the lower shell portion so as to be arranged to provide upward thrust to the main body. | 12-29-2016 |
20180022467 | SINGLE ENGINE, ASYMMETRICAL VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT | 01-25-2018 |
20090140102 | Ducted fan vehicles particularly useful as VTOL aircraft - A vehicle, including a vehicle frame, a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame, a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid therethrough from its inlet at the upper end of the duct through its exit at the lower end of the duct, and thereby to produce an upward lift force applied to the vehicle, and a plurality of parallel, spaced vanes pivotally mounted to and across the inlet end of the duct about pivotal axes perpendicular to the longitudinal axis of the duct and substantially parallel to the longitudinal axis of the vehicle frame, the vanes being selectively pivotal about their axes to produce a desired horizontal force component to the lift force applied to the vehicle. | 06-04-2009 |
20090140103 | Vehicle with vertical lift - An apparatus for producing vertical lift in a vehicle. In one embodiment, two sets of trans-flow fans discharge air through multi-directional vane assemblies that direct the discharged air outward and downward. Each one of the sets of fans is positioned on opposite sides of the vehicle. The multi-directional vane assemblies include vertical vanes that direct the discharged air fore and aft and horizontal vanes that direct the discharged air downward at various angles. In one embodiment, the vehicle includes a hovercraft skirt and a portion of the discharge air is directed into the skirt, causing the vehicle lift vertically on a cushion of air. In one such embodiment, a flow director controls the amount of discharged air flowing through the inlet to the volume defined by the skirt. | 06-04-2009 |
20110180671 | DIFFERENTIAL VANE VEHICLE CONTROL - A ducted fan air-vehicle capable of generating control moments. The ducted fan air-vehicle includes an air duct, a fan, a center body, a plurality of control vanes. The vanes are independently controlled and are deflected in the same direction but at different angles, thereby providing an increased control moments to the vehicle compared to the prior art. The increased pitching moment allows for additional control authority. Additional control authority is useful in forward flight and is especially desirable when the ducted fan air-vehicle is maneuvering in unsteady or turbulent winds or with various types of cargo that may effect the vehicle center of gravity location. | 07-28-2011 |
20140054423 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 02-27-2014 |
20140061390 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 03-06-2014 |
244023000 | Dual propulsion means, horizontal and vertical | 5 |
20080302920 | Aerial Lifting and Propulsion Device (ALPD) - This invention, an Aerial Lifting and Propulsion Device, introduces an aircraft and aircraft wing design that has an outer and inner circumference, both of which are employed in the entirety of each to evacuate air, air space, and/or atmosphere from above the circular wing/craft, to the area beneath the circular wing/craft, through the use of a propeller inside the inner circumference of the circular wing, and impellers at the outer circumference of the circular wing. When the air, air space, and/or atmosphere forced from above the circular wing into the area beneath the circular wing and propeller attempts to escape to the top of the circular wing to fill the newly created low pressure area above the circular wing, it is intercepted at the lower edge of the outer circumference of the circular wing and forced to returned to the area beneath the circular wing, where the atmospheric pressure is further increased or decreased at will, depending on the pitch and speed of the aircraft propeller and impeller blades. The noted reduced atmospheric pressure at the top of the circular wing, and the higher controlled atmospheric pressure in the area beneath the circular wing and propeller, forces the circular wing upward from its stationary position, achieving lift as described in Bernoulli's Principle. Stabilization and directional control is maintained through adjustments in the pitch of the impeller and propeller and the effects of torque are neutralized by the rotation of the impeller and propeller assemblies in opposite directions. The Aerial Lifting and Propulsion Device maintains its upright configuration while airborne in part because its center of gravity is well below the points where lift is generated. | 12-11-2008 |
20090084907 | Ground Effect Vanes Arrangement - A vehicle, particularly a VTOL air vehicle, includes a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame; a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid therethrough from its inlet at the upper end of the duct through its exit at the lower end of the duct, and thereby to produce an upward lift force applied to the vehicle, and a plurality of spaced vanes mounted to and across the inlet and exit ends of the duct about axes substantially perpendicular to the longitudinal axis of the duct and selectively operational to produce a desired horizontal control force in addition to the lift force applied to the vehicle. | 04-02-2009 |
20100001143 | Discoidal flying craft - A flying craft has an aerodynamic aircraft fuselage structure preferably disc shaped. A pair of coaxial electrokinetic motor-generators are mounted concentrically, and preferably centered within the disc shaped structure of the craft. Each of the motors is toroidal in configuration, providing a ring-shaped stator and rotor portions. The rotor portions of the motors drive counter rotating fans which are electro-magnetically levitated. The structure is open to the fans so that air may be drawn into the structure and expelled downward providing vertical lift to the aircraft. By use of auxiliary air braking flaps and electrokinetic thrusters, the craft may be tilted so as to develop a desired horizontal thrust. By impulse breaking one of the fans through tracking solenoids at different points around the stator, the aircraft may be made to rotate about its own vertical axis for changing direction. By a series of sudden braking of the motors the craft may be made to move by inertial reaction. | 01-07-2010 |
20120068021 | CRAFT AND METHOD FOR ASSEMBLING CRAFT WITH CONTROLLED SPIN - This invention relates to a craft designed to move through or on a surface of a fluid. It is believed to be principally of use in relation to airborne craft and missiles but the theory behind the invention is equally applicable for example to submarines. | 03-22-2012 |
20140027581 | AIRCRAFT HAVING A ROTATING TURBINE ENGINE - The present invention describes an aircraft having a rotating engine. The aircraft comprises a means for rotating the engine 360° to allow directional control of the aircraft via rotation of the engine's thrust output. The aircraft can further comprise a plurality of flap members located on the wings of the aircraft and in communication with the rotating gas turbine engine to further control and stabilize flight of the aircraft. The gas turbine engine of the aircraft can comprise a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating more thrust from a single engine. | 01-30-2014 |
20150028161 | Hydraulic Passenger Lifting and Maneuvering Device - This invention relates to a fluid driven propulsion device comprising a body arranged in a manner to facilitate flight and lift for a person, passenger or object(s) with a production of thrust from a portable or fixed power unit. A power unit is designated to move an incompressible fluid via pump through a flexible pipe or transmission tube to two or more pairs of restrictive axially offset nozzles within the embodiment of the invention allowing the incompressible fluid's pressure to build and its mass to be ejected underneath the person, passenger or object(s). This fluid is expelled with such velocity to create a force, directed into multiple, generally symmetrical force vectors, sufficient to facilitate balanced, easy to master free-flight. The invention also allows for powered, active inward and outward adjustment of the axially offset pairs of nozzles, as well as powered, active aperture adjustment of each of the nozzle outlets. | 01-29-2015 |
20160144960 | PERSONAL FLUID-JET THRUST PACK WHICH PROVIDES ROTATION FOR A RIDER ABOUT THREE AXES - The present invention provides lightweight fluid-jet thrust pack which provides three rotational axes and reduced restriction of fluid flow to the output nozzles. A first rotational axis is provided by a first rotatable coupling that is concentric with a coupler for a hose supplying pressurized fluid. The top of the first coupling has a splitter which directs incoming fluid into two splayed stub supply pipes. A preformed, reinforced rubber hose connects each stub supply pipe to one of a pair of coaxial rotatable couplings at opposite ends of a tiltable cross arm assembly that is pivotally secured to tower support bracket that is secured to the first rotatable coupling. An outward rotatable portion of each of the coaxial rotatable couplings is equipped with one boot-mounting platform and a downward-projecting jet nozzle that is in communication with the stub receiver pipe of the same rotatable coupling. | 05-26-2016 |
20160152338 | AN AERODYNAMIC LIFTING DEVICE | 06-02-2016 |
20090236475 | LIFT CHAMBER - A lift device having a generally cylindrical chamber formed by a top wall, a bottom wall, an outer wall and an inner wall. A plurality of lift members are mounted to the interior of a chamber wall and at least one fan is mounted within the chamber and an engine operatively connected to at lease one fan. | 09-24-2009 |
20100025540 | Compact ultralight aircraft reduced dimensions, with vertical take-off and landing - A compact ultralight aircraft ( | 02-04-2010 |
20100051754 | Aircraft - An aircraft has a generally circular main body including an upper surface portion supported for rotation about a central passenger compartment to produce a gyroscopic effect on the aircraft. The rotatable upper surface portion includes viewable panes therein arranged to provide visibility therethrough from the central passenger compartment to an exterior of the main body. An engine communicates between a central inlet opening in the upper surface portion and an exhaust opening in the bottom of the main body to provide upward thrust to the aircraft. | 03-04-2010 |
20100102174 | Wingless Hovering Of Micro Air Vehicle - Embodiments of the subject invention relate to a Wingless Hovering Micro Air Vehicle (WHOMAV) and its Power Source Unit (PSU). Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments of the subject invention can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | 04-29-2010 |
20100187369 | DUCTED FAN UAV CONTROL ALTERNATIVES - A ducted fan air-vehicle having alternative methods of control is described. The ducted fan air-vehicle includes an air duct, a fan, a center body, a plurality of control vanes. Each control vanes includes a separate servo for independent control of each control vane, and is therefore able to operate the control vanes in a non-traditional manner to provide maximum control authority. | 07-29-2010 |
20100282918 | Saucer shaped gyroscopically stabilized vertical take-off and landing aircraft - An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating sine-wave ring is used to activate and move a plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere. | 11-11-2010 |
20100288889 | SPRING FLYING DEVICE - The Spring flying device ( | 11-18-2010 |
20130181095 | DEVICE TO GENERATE LIFT FORCE (OPTIONS) - The options of the invention relate to the aviation and can be used in order to create lifting vehicle as well as load lifting devices. In order to achieve technical result—the decrease of energy losses on the while creating and change of vector of moving, aerodynamic, composite force, including as a component a lift force,—in the device to generate lift force containing a tubiform frame, superchargers, the wings having in section an aerofoil profile oriented by the leading edge to the direction of working medium exhaust out of the super-charger, adjusting units for a wing, guiding devices, each of those is installed in front of leading edge of each wing, the system to maintain the required working temperature of medium, unit to connect outdoor environment, as per the invention in the first option of the device a tubiform frame is of the form of a tore, in the second option—the form of closed volumetric loop, in the third option—a cylindrical form. Meanwhile each option of the device is equipped with relevant distinguishing units, providing the achieving of a technical result. | 07-18-2013 |
20130306802 | METHODS AND APPARATUS FOR VERTICAL SHORT TAKEOFF AND LANDING - Methods and apparatus for vertical or short takeoff and landing. In one embodiment, the apparatus comprises two or more counter driven rings with one or more airfoils attached. In one variant, there is an upper ring and a lower ring, each with multiple airfoils attached. In one variant, lift is generated largely via ambient air currents, allowing for long term on-station operation of the device. | 11-21-2013 |
20130306803 | AIRCRAFT GENERATING A LIFT FROM AN INTERIOR THEREOF - The invention discloses an aircraft generating a larger lift from its interior. The fluid channel inside the aircraft communicates with the engine and the ports on the upper surface of the outer shell. With the powerful suction of the engine, the fluid on the upper surface of the outer shell is quickly sucked into the fluid channel via respective ports under conditions of long path, large area, high speed and low air pressure, which results in large lift from the interior of the aircraft. In the course of generating the lift, the fluid resistances of the fluid wall and the fluid hole are sucked into the fluid channel through the ports at the front and the surrounding area of the aircraft, then high-speed fluid is emitted from the rear port. This approach contributes greatly to the transformation of the existing aircraft. The unified big wing significantly improves the lift, the speed and the carrying capacity of the existing aircraft with lowered energy consumption. | 11-21-2013 |
20090039206 | BIRD VORTEX FLYING MACHINE - The present invention comprises, in one embodiment, an inexpensive, lightweight flying vehicle using fixed pitch helicopter blades powered by ramjet engines mounted to a power-ring which transfers torque to the lifting rotors. The use of fixed pitch blades eliminates the need for a tail boom and tail rotor, as well as for variable incidence control of blade pitch and/or cyclic and collective rotor-pitch controls. An optional ballistic parachute may be deployed for emergency landings. A radial shroud encloses the ramjet engines to act as a sound shield. Since the rotor has a fixed pitch, lift may be controlled by rotor speed, where increased speed results in ascent, and decreased speed, descent. | 02-12-2009 |
20100193643 | LIFT FAN SYSTEM - Embodiments of the present invention include a system, e.g., for a short takeoff and vertical landing (STOVL) aircraft. The system includes a power generator, such as a gas turbine engine; a lift fan powered by the power generator; and includes two or more nozzles in fluid communication with the lift fan. | 08-05-2010 |
20110204188 | ROTOCRAFT - An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle. | 08-25-2011 |
20140077039 | Heated Screen For Air Intake Of Aircraft Engines - An aircraft includes a fuselage and wings mounted on opposite sides of the fuselage for sustained forward flight. An engine is mounted in the fuselage or at least one of the wings and includes an air intake. At least a portion of the air intake generally faces the forward direction for receiving intake air during forward flight. A filter assembly is mounted adjacent the air intake and disposed to impinge air and block objects from passing therethrough. A heated screen includes a heater and is mounted adjacent the air intake and upstream of the engine such that ice entering the air intake contacts the heated screen before entering the engine. A power source is provided to supply power to the heater. | 03-20-2014 |
20190144108 | Aircraft having Hover Stability in Inclined Flight Attitudes | 05-16-2019 |
20080223993 | HOMEOSTATIC FLYING HOVERCRAFT - A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control. | 09-18-2008 |
20080283673 | Ducted Fan Vtol Vehicles - A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | 11-20-2008 |
20090020654 | Harness with mounted engine frame - A harness with mounted engine frame comprises a harness to be worn by a user. An engine support arm is mounted on the harness and a pair of lateral arms extend from the engine support arm. At least one engine is associated with each lateral arm. A connector attaches directly or indirectly to the harness for receiving the engine support arm, so that the engine support arm is movable relative to the harness in response to engine output and other flight conditions. | 01-22-2009 |
20090121087 | High speed vertical take-off and land aircraft with active fan balancing system - A high-speed vertical take-off and land aircraft includes a body with an engine supported by the body. A fan assembly is also carried by the body. The fan assembly includes a hub and a plurality of blades to provide vertical lift for the aircraft. A nozzle ring is provided on the fan assembly. The nozzle ring includes an annular nozzle array. Hot gases from the engine are fed to the nozzle array by a feed duct. A bearing mechanism supports the fan assembly on the body. The bearing mechanism is carried in a work space. A brush seal assembly thermally isolates the work space from the hot exhaust gases passing through the feed duct to the nozzle array. | 05-14-2009 |
20090159757 | Ducted Fan Vtol Vehicles - A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | 06-25-2009 |
20090250557 | Whirling Wheel Airborne Vehicles - A sliding-arm whirling wheel thruster includes first and second whirling wheels and a housing. The first whirling wheel is disposed about a first rotational axis, and the second whirling wheel about a second rotational axis parallel to the first rotational axis. The housing comprises an arc over an enclosed space into which the first and second whirling wheels fit. The air blown outward by each of the whirling wheels is amassed inside the housing so as to make a pressure difference between inside and outside of the housing. The relative position of the first rotational axis to the second rotational axis is configured to be controlled. The airborne vehicle is lifted by buoyant force caused by the pressure difference. | 10-08-2009 |
20100012790 | GYRO-STABILIZED AIR VEHICLE - A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage. | 01-21-2010 |
20100019098 | Ducted Fan Core for Use with an Unmanned Aerial Vehicle - A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame, attached to which are an engine, gearbox assembly, fan, and a plurality of control vanes. A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle. | 01-28-2010 |
20100051753 | WALL EFFECTS ON VTOL VEHICLES - ducted air flow vehicle that includes a fuselage having a longitudinal axis, supporting at least one air flow duct and a prime mover arranged to force surrounding air into the duct through an inlet at an upper end of the duct with normally symmetrical airflow streams, thereby creating a lift force directed substantially along a duct axis; a plurality of vanes extending across the inlet, substantially parallel to the longitudinal axis; and wherein one or more groups of the vanes are selectively pivotable to align with adjacent abnormal asymmetrical airflow streams. | 03-04-2010 |
20100078523 | Tandem powered power tilting tilt rotor aircraft - An aircraft with a long body | 04-01-2010 |
20100127131 | System and Method For a Fuel Bladder Assembly With Embossed Film - Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto. The fuel bladder may include an embossed pattern disposed to prevent a vacuum being formed by the collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV). | 05-27-2010 |
20100140415 | VERTICAL TAKE OFF AND LANDING UNMANNED AERIAL VEHICLE AIRFRAME STRUCTURE - An unmanned aerial vehicle selectively formed of high strength composite structural part portions and lightweight aerodynamic foam portions to provide a low-cost and lightweight UAV that comports with export, civil airspace, and safety regulations. To further to reduce an overall weight of the UAV, mechanical elements are designed to provide multiple functionalities. Structural elements may be manufactured in same or similar non-specialized processes, and non-structural elements manufactured in same or similar non-specialized processes, reducing overall manufacturing costs. Materials and bonding elements are selected to provide frangibility and yet maintain normal flight structural integrity. | 06-10-2010 |
20100140416 | Ducted Fans with Flow Control Synthetic Jet Actuators and Methods for Ducted Fan Force and Moment Control - The present invention relates to the field of aerodynamics. More particularly, the present invention relates to manipulating air flow over a surface, such as the surface of a duct of a ducted fan vehicle. By controlling air flow over, at, or around the surface of a duct, the flight of the vehicle can be controlled. One embodiment of the invention provides a vertical take-off and landing (VTOL) ducted-fan vehicle comprising means for producing steady or unsteady blowing at a surface of a duct for producing control forces and moments for controlling flight. The means for unsteady blowing can be provided by synthetic jets and the means for steady blowing can be provided by a pressurized air supply. The synthetic jets can be integrated into the ducted-fan vehicles in numerous ways, including at the surface of the leading and/or trailing edge of the ducts. The synthetic jets can be independently operated to control the flight of the vehicle. A novel use of these inventive flow control concepts is to apply the control asymmetrically to the duct in order to produce an imbalance in forces, thus resulting in a moment or torque, which can be used to control flight. | 06-10-2010 |
20100171000 | Tandem powered tilt rotor aircraft - An aircraft with a long body | 07-08-2010 |
20100320333 | Saucer-shaped gyroscopically stabilized vertical take-off and landing aircraft - An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating plate includes a groove that traces a sinusoidal pattern around an inside periphery of the plate. Tracking arms have a portion that fit within the groove and another portion that connects to a piston. The rotation of the plate causes the tracking arms to travel within the sinusoidal groove and impart movement on the plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere. | 12-23-2010 |
20110001017 | UAV DUCTED FAN SWEPT AND LEAN STATOR DESIGN - A ducted fan air-vehicle having an air duct and a fan is described. The air duct includes an outer rim and an inner rim, and the fan is located within the air duct and rotates in a direction. The fan also includes a hub, a plurality of struts extending from the hub and positioned adjacent the outer rim of the fan, a plurality of stators extending from the hub and positioned adjacent the inner rim of the fan, and a plurality of rotor blades extending from the hub and positioned between the plurality of struts and the plurality of stators. The stators are lean in a plane of fan rotation and swept in a plane normal to fan rotation to create the optimum amount of noise reduction in the ducted fan air-vehicle. | 01-06-2011 |
20110049306 | CONTROL FLOWS AND FORCES IN VTOL VEHICLES - The present application relates to VTOL vehicles with multi-function capabilities and, specifically to ducted fan arrangements that facilitate the control of forces and flows of air to control movement of the vehicle in six degrees of freedom in both primary and secondary modes of operation. Also disclosed are pitch control mechanisms for the lift propellers of VTOL vehicles: drive and transmission arrangements; a specially configured exhaust duct for directing exhaust gases from such vehicles along an upper surface of the vehicle; and shock absorbing components for the landing gear of such vehicles. | 03-03-2011 |
20110049307 | VTOL VEHICLE WITH OFFSET ENGINE - A ducted air flow vehicle includes a fuselage having a longitudinal axis, supporting forward and aft air flow ducts having respective lift fans arranged to force surrounding air into said ducts through inlets at upper ends of said ducts and out of said ducts through outlets at lower ends of said ducts, thereby creating a lift force. A single engine is located on one side of said longitudinal axis, and is operatively configured to power the lift fans. A payload bay is located in a central area of said fuselage, between the forward and aft ducts, spanning the longitudinal axis. | 03-03-2011 |
20110139939 | PERSONAL FLIGHT DEVICE INCORPORATING RADIATOR COOLING PASSAGE - A personal flight device which includes: a housing which is securable to a pilot; at least one pair of ducted fans, one fan of the pair mounted to one side of the housing, the other fan of the pair mounted to the other side of the housing; wherein each fan rotates about an axis of rotation so as to draw air through the corresponding duct from an entry end of the duct to an exit end of the duct; and wherein the axis of rotation of each fan is fixed relative to the housing; at least one engine mounted on the housing for driving the fans such that both fans rotate in the same direction for producing thrust; the or each engine being cooled by a radiator; the or each radiator being associated with at least one passage having an entry end in communication with one surface of the radiator and an exit end adjacent the entry end of one of said ducts. | 06-16-2011 |
20110147533 | MORPHING DUCTED FAN FOR VERTICAL TAKE-OFF AND LANDING VEHICLE - A morphing duct of a ducted fan for a vertical take-off and landing (VTOL) vehicle is configured to change shape as function of the flight mode of the vehicle to improve the thrust per unit energy input for the ducted fan. Additionally, the morphing duct may be configured to change shape to change the flight path of the VTOL vehicle. | 06-23-2011 |
20110155859 | AIRCRAFT VERTICAL LIFT DEVICE - A lift device is disclosed that can be used to provide vertical lift to an aircraft or other vehicle. The lift device can include a fan that produces an airflow and a vane box that can direct the airflow. In one form the fan can be oriented at an angle relative to a reference plane in the aircraft. In another form the vane box can be oriented at an angle. The vane box can be structured to provide a maximum flow area between an aft flow vector and a forward flow vector. | 06-30-2011 |
20110155860 | FLUID DYNAMIC DEVICE WITH THRUST CONTROL SHROUD - A fluid dynamic device ( | 06-30-2011 |
20110210212 | Tilt rotor aircraft with tilting tail rotor - TT - A vertical take-off aircraft comprising a main power plant | 09-01-2011 |
20110266397 | SOLAR THERMAL ROTORCRAFT - A vehicle includes a housing having a wall with a central port and radial port formed at a lower portion of the housing, a blower disposed within the housing to move air through the central port, a distributor coupled to the blower to distribute air inside the housing, a heat-absorbing body disposed within the housing to absorb thermal energy, and at least one arm coupled to the housing. | 11-03-2011 |
20120056040 | Electric VTOL Aircraft - An electric and hybrid Vertical-Take Off and Landing (“VTOL”) aircraft is disclosed comprising a plurality of small Electric Ducted Fans (“EDFs”) of various sizes and orientations. The thrust of each fixed EDF is individually controlled by modulation of motor power by one or more onboard microcomputers connected to a plurality of onboard laser distance measuring sensors, at least three onboard three-axis accelerometers and at least one GPS thereby allowing extremely precise and safe VTOL operation. The aircraft may be employed to allow robotic and passenger vehicles to transition extremely quickly between normal linear flight and VTOL and tb operate in extreme and gusty conditions. | 03-08-2012 |
20120080564 | DUCTED PLATFORMS - A ducted fan for a VTOL vehicle includes a substantially cylindrical duct having an inlet at an upper end and an outlet at a lower end, and an air mover unit located within the substantially cylindrical duct. The duct also includes inner and outer wall portions and a substantially annular upper lip connecting the inner and outer wall portions, thus defining the inlet. The substantially annular upper lip has opposed fore and aft portions and opposed side portions and is provided with at least first and second openings, respectively, at each of the opposed side portions. The first and second arrays of openings permit flow of air into at least first and second respective chambers formed within the duct, the first and second chambers connected by at least one passageway to thereby enable substantial equalization of surface pressure at the opposed side portions of the substantially annular upper lip. | 04-05-2012 |
20120091284 | UNMANNED AERIAL VEHICLE - The various embodiments of the present invention provide an unmanned aerial vehicle comprising a hemispherical body, a brushless type electrical, a propeller, a plurality of wingtip devices, a plurality of servomotors and each of the plurality of the servomotors is connected to each of the plurality of the wingtip devices respectively, a plurality of carbon rods, and a casing. The brushless type electrical motor provides a lifting force for a Vertical take-off and landing (VTOL) and the plurality of wing tip devices are classified into three types of wing tip devices and the three types of wing tip devices are controlled by the respective servomotors to control yaw, pitch and roll movements thereby stabilizing and controlling the movement of an aircraft. | 04-19-2012 |
20120126064 | UAV DUCTED FAN LIP SHAPING - A ducted fan air-vehicle having a duct lip shape is described. The duct lip has an internal duct lip portion and an external duct lip portion, both of which are substantially curvature continuous around the circumference of the air duct. The duct has a plurality of cross-sections along its circumference and at least some of the plurality of cross-sections have a different shape. Further, each cross-section around the circumference of the duct has an a/b ratio and the a/b ratio for each cross-section is substantially the same. | 05-24-2012 |
20120153087 | Modular Pods for Use with an Unmanned Aerial Vehicle - A pod for an unmanned aerial vehicle is provided that may be removed and re-attached to the vehicle. The pod comprises an outer shell, within which a variety of payloads may be carried. A first surface on the vehicle frame comprises a plurality of connects or electrical traces. The plurality of attachments are used to removably attach the pods to the first surface. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle. | 06-21-2012 |
20120234984 | Integrated Duct Design for an Unmanned Aerial Vehicle - A ducted fan air vehicle having increased storage capacity inside the duct for equipment and electronics provides improved airflow and fan efficiency over ducted fan air vehicles carrying cargo in external pods. The outside of the duct may extend outwardly to allow equipment and electronics to be stored inside the duct in storage areas located at intervals along the duct. The storage areas may form a square duct having a circular inside wall. Additionally, the storage areas may extend in the direction of the axis of rotation of the fan to provide additional storage above the lower lip of the duct. | 09-20-2012 |
20130068895 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 03-21-2013 |
20130105635 | QUAD TILT ROTOR VERTICAL TAKE OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV) WITH 45 DEGREE ROTORS | 05-02-2013 |
20130126680 | UNMANNED AIR VEHICLE FAULT TOLERANT FLIGHT CONTROL SYSTEM AND METHOD - Methods and apparatus are provided for controlling an unmanned air vehicle (UAV) that includes a plurality of independently controllable control vanes. Control vane position commands are supplied that will move each of the control vanes to a position that will cause the UAV to implement a commanded maneuver. Inoperability of one of the control vanes is sensed, and the position of the inoperable control vane is determined New control vane position commands are determined, based on the determined position of the inoperable control vane, which will also cause the UAV to implement the commanded maneuver. | 05-23-2013 |
20130134263 | WINGLESS HOVERING OF MICRO AIR VEHICLE - Embodiments of the subject invention relate to an air vehicle and a power source. Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | 05-30-2013 |
20130140404 | SYSTEM AND METHOD FOR IMPROVING TRANSITION LIFT-FAN PERFORMANCE - A system and method enabled to increase efficiency during a VTOL aircraft's transition. A VTOL aircraft enabled to operate multiple lift fans arranged into separately controllable groups, wherein the VTOL aircraft initially has vertical flight but transitions to horizontal flight. A first group of lift fans may be kept at full throttle, a second group of lift fans may be throttled to balance thrust and/or weight, and a third group of lift fans may be shut off. | 06-06-2013 |
20130206919 | SYSTEMS AND METHODS FOR CONTROLLING AN AERIAL UNIT - An aerial unit that includes a first propeller; a second propeller that is spaced apart from the first propeller and is below the first propeller; a propelling module that is configured to rotate the first propeller and the second propeller about a first axis; an apertured duct that comprises a first duct portion and a second duct portion. The first duct portion surrounds the first propeller. The second duct portion surrounds the second propeller. The apertured duct defines at least one aperture at an intermediate area that is positioned below the first propeller and is above the second propeller. The aggregate size of the at least one aperture is at least fifty percent of a size of the intermediate area; a frame; and at least one steering element; an interfacing module arranged to be connected to a connecting element that couples the aerial unit to a ground unit. The propelling module and the duct are connected to the frame. | 08-15-2013 |
20140048657 | CROSS FLOW FAN FLYING DEVICE - A cross flow fan flying device includes a first thrusting means having a first cross flow fan and a second thrusting means having a second cross flow fan, wherein the first flow fan and the second cross flow fan rotate in directions opposite with each other, and the cross flow fan flying device is driven and flies by airflow thrust generated by the first cross flow fan and the second cross flow fan. | 02-20-2014 |
20140158832 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 06-12-2014 |
20140263849 | PERSONAL PROPULSION DEVICES WITH IMPROVED BALANCE - A personal propulsion device, including a platform configured to support a passenger's body; and at least one fluid discharge nozzle coupled to the platform and angled with respect to the platform, where the angle defined between the nozzle and the platform is between approximately 95° and 120°; where the personal propulsion device is configured to receive pressurized fluid from a remote pressurized fluid source, and where the personal propulsion device is configured to achieve flight. | 09-18-2014 |
20140332634 | MULTI-PURPOSE PERSONAL PROPULSION SYSTEM - A personal propulsion system, including an assembly adapted to support a passenger and achieve flight through the discharge of pressurized fluid; and a pressurized fluid source in fluid communication with the assembly, where the pressurized fluid source does not achieve flight, and where the pressurized fluid source is constructed at least in part from one or more ballistic armor materials. | 11-13-2014 |
20140332635 | TANDEM PERSONAL PROPULSION DEVICE - A personal propulsion device, including a passenger assembly configured to support a plurality of passengers, the passenger assembly including one or more nozzles adapted to discharge pressurized fluid; and a pressurized fluid source in fluid communication with the passenger assembly, where the passenger assembly is capable of achieving flight by discharging pressurized fluid provided by the pressurized fluid source. The pressurized fluid source may be a personal watercraft, and the passenger assembly may be configured to support two passengers positioned side-by-side, one in front of the other, or facing different directions. | 11-13-2014 |
20150053826 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - There is provided a vertical take-off and landing aircraft including: a propulsion mechanism for generating lift and thrust; a power supply unit (e.g. an engine as a power source) for supplying power to the propulsion mechanism; a main frame for supporting the engine, a seat, and a landing undercarriage; a sub-frame for supporting the propulsion mechanism; a frame coupling unit for rotatably coupling the main frame and the sub-frame; and a control stick connected to the sub-frame, so that an occupant sitting on a seat operates a control stick thereby to move the sub-frame relative to the main frame so as to change the orientation of the propulsion mechanism. | 02-26-2015 |
20150108282 | FLOATING MOBILE OBJECT AND FLOATING MOBILE SYSTEM USING THE SAME - A holonomic floating mobile object is operated under gravity and includes a main body and six or more thrusters for generating thrust by changing the momentum of a fluid. The six or more thrusters are controlled independently of one another such that the thrust is set at a desired value. The six or more thrusters are arranged in a fuselage coordinate system defined on the main body, such that the range in which a total thrust vector obtained by combining vectors of the thrust generated by all of the thrusters can be generated spans a six-dimensional space with three directions of translation and three directions of rotation. Incoming and outgoing flows to and from one of the thrusters are spaced apart from incoming and outgoing flows to and from the other thrusters and even apart from every other fuselage structure aside from that one thruster. | 04-23-2015 |
20150360776 | VERTICAL TAKE-OFF AND LANDING AERIAL VEHICLE - A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The control system being able to control the orientation of the inner frame. The gimbal system connecting the inner frame to the outer frame with at least two rotation axis allowing rotation freedom between the outer frame to rotate independently from the inner frame. | 12-17-2015 |
20160101852 | Annular ducted lift fan VTOL aircraft - The invention is an annular ducted lift fan system for a VTOL type aircraft. In detail, the invention comprises an annular duct, a lift fan set, engines, a central fuselage, a peripheral wing, and means for pneumatic coupling or mechanic coupling of engines and the lift fan set. The lift fan set is mounted in the annular duct and powered by the engines through pneumatic coupling or mechanic coupling. The annular duct is opened with the lift fan set working to provide high lift efficiency in VTOL mode and transition mode and is closed off to reduce drag in cruise mode. | 04-14-2016 |
20160376002 | Aircraft with Rotating Outer Shell - An aircraft having a main body defining a passenger compartment therein, an upper shell portion above the main body and a lower shell portion below the main body, further includes a motor assembly operatively connected between the upper shell portion, the lower shell portion and the main body so as to be arranged to drive rotation of the upper and lower shell portions relative to the main body in opposing directions relative to one another. An engine assembly is supported on the main body in communication with a central thrust opening in the lower shell portion so as to be arranged to provide upward thrust to the main body. | 12-29-2016 |
20180022467 | SINGLE ENGINE, ASYMMETRICAL VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT | 01-25-2018 |
20090140102 | Ducted fan vehicles particularly useful as VTOL aircraft - A vehicle, including a vehicle frame, a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame, a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid therethrough from its inlet at the upper end of the duct through its exit at the lower end of the duct, and thereby to produce an upward lift force applied to the vehicle, and a plurality of parallel, spaced vanes pivotally mounted to and across the inlet end of the duct about pivotal axes perpendicular to the longitudinal axis of the duct and substantially parallel to the longitudinal axis of the vehicle frame, the vanes being selectively pivotal about their axes to produce a desired horizontal force component to the lift force applied to the vehicle. | 06-04-2009 |
20090140103 | Vehicle with vertical lift - An apparatus for producing vertical lift in a vehicle. In one embodiment, two sets of trans-flow fans discharge air through multi-directional vane assemblies that direct the discharged air outward and downward. Each one of the sets of fans is positioned on opposite sides of the vehicle. The multi-directional vane assemblies include vertical vanes that direct the discharged air fore and aft and horizontal vanes that direct the discharged air downward at various angles. In one embodiment, the vehicle includes a hovercraft skirt and a portion of the discharge air is directed into the skirt, causing the vehicle lift vertically on a cushion of air. In one such embodiment, a flow director controls the amount of discharged air flowing through the inlet to the volume defined by the skirt. | 06-04-2009 |
20110180671 | DIFFERENTIAL VANE VEHICLE CONTROL - A ducted fan air-vehicle capable of generating control moments. The ducted fan air-vehicle includes an air duct, a fan, a center body, a plurality of control vanes. The vanes are independently controlled and are deflected in the same direction but at different angles, thereby providing an increased control moments to the vehicle compared to the prior art. The increased pitching moment allows for additional control authority. Additional control authority is useful in forward flight and is especially desirable when the ducted fan air-vehicle is maneuvering in unsteady or turbulent winds or with various types of cargo that may effect the vehicle center of gravity location. | 07-28-2011 |
20140054423 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 02-27-2014 |
20140061390 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 03-06-2014 |
244023000 | Circular configuration | 10 |
20080302920 | Aerial Lifting and Propulsion Device (ALPD) - This invention, an Aerial Lifting and Propulsion Device, introduces an aircraft and aircraft wing design that has an outer and inner circumference, both of which are employed in the entirety of each to evacuate air, air space, and/or atmosphere from above the circular wing/craft, to the area beneath the circular wing/craft, through the use of a propeller inside the inner circumference of the circular wing, and impellers at the outer circumference of the circular wing. When the air, air space, and/or atmosphere forced from above the circular wing into the area beneath the circular wing and propeller attempts to escape to the top of the circular wing to fill the newly created low pressure area above the circular wing, it is intercepted at the lower edge of the outer circumference of the circular wing and forced to returned to the area beneath the circular wing, where the atmospheric pressure is further increased or decreased at will, depending on the pitch and speed of the aircraft propeller and impeller blades. The noted reduced atmospheric pressure at the top of the circular wing, and the higher controlled atmospheric pressure in the area beneath the circular wing and propeller, forces the circular wing upward from its stationary position, achieving lift as described in Bernoulli's Principle. Stabilization and directional control is maintained through adjustments in the pitch of the impeller and propeller and the effects of torque are neutralized by the rotation of the impeller and propeller assemblies in opposite directions. The Aerial Lifting and Propulsion Device maintains its upright configuration while airborne in part because its center of gravity is well below the points where lift is generated. | 12-11-2008 |
20090084907 | Ground Effect Vanes Arrangement - A vehicle, particularly a VTOL air vehicle, includes a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame; a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid therethrough from its inlet at the upper end of the duct through its exit at the lower end of the duct, and thereby to produce an upward lift force applied to the vehicle, and a plurality of spaced vanes mounted to and across the inlet and exit ends of the duct about axes substantially perpendicular to the longitudinal axis of the duct and selectively operational to produce a desired horizontal control force in addition to the lift force applied to the vehicle. | 04-02-2009 |
20100001143 | Discoidal flying craft - A flying craft has an aerodynamic aircraft fuselage structure preferably disc shaped. A pair of coaxial electrokinetic motor-generators are mounted concentrically, and preferably centered within the disc shaped structure of the craft. Each of the motors is toroidal in configuration, providing a ring-shaped stator and rotor portions. The rotor portions of the motors drive counter rotating fans which are electro-magnetically levitated. The structure is open to the fans so that air may be drawn into the structure and expelled downward providing vertical lift to the aircraft. By use of auxiliary air braking flaps and electrokinetic thrusters, the craft may be tilted so as to develop a desired horizontal thrust. By impulse breaking one of the fans through tracking solenoids at different points around the stator, the aircraft may be made to rotate about its own vertical axis for changing direction. By a series of sudden braking of the motors the craft may be made to move by inertial reaction. | 01-07-2010 |
20120068021 | CRAFT AND METHOD FOR ASSEMBLING CRAFT WITH CONTROLLED SPIN - This invention relates to a craft designed to move through or on a surface of a fluid. It is believed to be principally of use in relation to airborne craft and missiles but the theory behind the invention is equally applicable for example to submarines. | 03-22-2012 |
20140027581 | AIRCRAFT HAVING A ROTATING TURBINE ENGINE - The present invention describes an aircraft having a rotating engine. The aircraft comprises a means for rotating the engine 360° to allow directional control of the aircraft via rotation of the engine's thrust output. The aircraft can further comprise a plurality of flap members located on the wings of the aircraft and in communication with the rotating gas turbine engine to further control and stabilize flight of the aircraft. The gas turbine engine of the aircraft can comprise a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating more thrust from a single engine. | 01-30-2014 |
20150028161 | Hydraulic Passenger Lifting and Maneuvering Device - This invention relates to a fluid driven propulsion device comprising a body arranged in a manner to facilitate flight and lift for a person, passenger or object(s) with a production of thrust from a portable or fixed power unit. A power unit is designated to move an incompressible fluid via pump through a flexible pipe or transmission tube to two or more pairs of restrictive axially offset nozzles within the embodiment of the invention allowing the incompressible fluid's pressure to build and its mass to be ejected underneath the person, passenger or object(s). This fluid is expelled with such velocity to create a force, directed into multiple, generally symmetrical force vectors, sufficient to facilitate balanced, easy to master free-flight. The invention also allows for powered, active inward and outward adjustment of the axially offset pairs of nozzles, as well as powered, active aperture adjustment of each of the nozzle outlets. | 01-29-2015 |
20160144960 | PERSONAL FLUID-JET THRUST PACK WHICH PROVIDES ROTATION FOR A RIDER ABOUT THREE AXES - The present invention provides lightweight fluid-jet thrust pack which provides three rotational axes and reduced restriction of fluid flow to the output nozzles. A first rotational axis is provided by a first rotatable coupling that is concentric with a coupler for a hose supplying pressurized fluid. The top of the first coupling has a splitter which directs incoming fluid into two splayed stub supply pipes. A preformed, reinforced rubber hose connects each stub supply pipe to one of a pair of coaxial rotatable couplings at opposite ends of a tiltable cross arm assembly that is pivotally secured to tower support bracket that is secured to the first rotatable coupling. An outward rotatable portion of each of the coaxial rotatable couplings is equipped with one boot-mounting platform and a downward-projecting jet nozzle that is in communication with the stub receiver pipe of the same rotatable coupling. | 05-26-2016 |
20160152338 | AN AERODYNAMIC LIFTING DEVICE | 06-02-2016 |
20090236475 | LIFT CHAMBER - A lift device having a generally cylindrical chamber formed by a top wall, a bottom wall, an outer wall and an inner wall. A plurality of lift members are mounted to the interior of a chamber wall and at least one fan is mounted within the chamber and an engine operatively connected to at lease one fan. | 09-24-2009 |
20100025540 | Compact ultralight aircraft reduced dimensions, with vertical take-off and landing - A compact ultralight aircraft ( | 02-04-2010 |
20100051754 | Aircraft - An aircraft has a generally circular main body including an upper surface portion supported for rotation about a central passenger compartment to produce a gyroscopic effect on the aircraft. The rotatable upper surface portion includes viewable panes therein arranged to provide visibility therethrough from the central passenger compartment to an exterior of the main body. An engine communicates between a central inlet opening in the upper surface portion and an exhaust opening in the bottom of the main body to provide upward thrust to the aircraft. | 03-04-2010 |
20100102174 | Wingless Hovering Of Micro Air Vehicle - Embodiments of the subject invention relate to a Wingless Hovering Micro Air Vehicle (WHOMAV) and its Power Source Unit (PSU). Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments of the subject invention can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | 04-29-2010 |
20100187369 | DUCTED FAN UAV CONTROL ALTERNATIVES - A ducted fan air-vehicle having alternative methods of control is described. The ducted fan air-vehicle includes an air duct, a fan, a center body, a plurality of control vanes. Each control vanes includes a separate servo for independent control of each control vane, and is therefore able to operate the control vanes in a non-traditional manner to provide maximum control authority. | 07-29-2010 |
20100282918 | Saucer shaped gyroscopically stabilized vertical take-off and landing aircraft - An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating sine-wave ring is used to activate and move a plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere. | 11-11-2010 |
20100288889 | SPRING FLYING DEVICE - The Spring flying device ( | 11-18-2010 |
20130181095 | DEVICE TO GENERATE LIFT FORCE (OPTIONS) - The options of the invention relate to the aviation and can be used in order to create lifting vehicle as well as load lifting devices. In order to achieve technical result—the decrease of energy losses on the while creating and change of vector of moving, aerodynamic, composite force, including as a component a lift force,—in the device to generate lift force containing a tubiform frame, superchargers, the wings having in section an aerofoil profile oriented by the leading edge to the direction of working medium exhaust out of the super-charger, adjusting units for a wing, guiding devices, each of those is installed in front of leading edge of each wing, the system to maintain the required working temperature of medium, unit to connect outdoor environment, as per the invention in the first option of the device a tubiform frame is of the form of a tore, in the second option—the form of closed volumetric loop, in the third option—a cylindrical form. Meanwhile each option of the device is equipped with relevant distinguishing units, providing the achieving of a technical result. | 07-18-2013 |
20130306802 | METHODS AND APPARATUS FOR VERTICAL SHORT TAKEOFF AND LANDING - Methods and apparatus for vertical or short takeoff and landing. In one embodiment, the apparatus comprises two or more counter driven rings with one or more airfoils attached. In one variant, there is an upper ring and a lower ring, each with multiple airfoils attached. In one variant, lift is generated largely via ambient air currents, allowing for long term on-station operation of the device. | 11-21-2013 |
20130306803 | AIRCRAFT GENERATING A LIFT FROM AN INTERIOR THEREOF - The invention discloses an aircraft generating a larger lift from its interior. The fluid channel inside the aircraft communicates with the engine and the ports on the upper surface of the outer shell. With the powerful suction of the engine, the fluid on the upper surface of the outer shell is quickly sucked into the fluid channel via respective ports under conditions of long path, large area, high speed and low air pressure, which results in large lift from the interior of the aircraft. In the course of generating the lift, the fluid resistances of the fluid wall and the fluid hole are sucked into the fluid channel through the ports at the front and the surrounding area of the aircraft, then high-speed fluid is emitted from the rear port. This approach contributes greatly to the transformation of the existing aircraft. The unified big wing significantly improves the lift, the speed and the carrying capacity of the existing aircraft with lowered energy consumption. | 11-21-2013 |
20090039206 | BIRD VORTEX FLYING MACHINE - The present invention comprises, in one embodiment, an inexpensive, lightweight flying vehicle using fixed pitch helicopter blades powered by ramjet engines mounted to a power-ring which transfers torque to the lifting rotors. The use of fixed pitch blades eliminates the need for a tail boom and tail rotor, as well as for variable incidence control of blade pitch and/or cyclic and collective rotor-pitch controls. An optional ballistic parachute may be deployed for emergency landings. A radial shroud encloses the ramjet engines to act as a sound shield. Since the rotor has a fixed pitch, lift may be controlled by rotor speed, where increased speed results in ascent, and decreased speed, descent. | 02-12-2009 |
20100193643 | LIFT FAN SYSTEM - Embodiments of the present invention include a system, e.g., for a short takeoff and vertical landing (STOVL) aircraft. The system includes a power generator, such as a gas turbine engine; a lift fan powered by the power generator; and includes two or more nozzles in fluid communication with the lift fan. | 08-05-2010 |
20110204188 | ROTOCRAFT - An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle. | 08-25-2011 |
20140077039 | Heated Screen For Air Intake Of Aircraft Engines - An aircraft includes a fuselage and wings mounted on opposite sides of the fuselage for sustained forward flight. An engine is mounted in the fuselage or at least one of the wings and includes an air intake. At least a portion of the air intake generally faces the forward direction for receiving intake air during forward flight. A filter assembly is mounted adjacent the air intake and disposed to impinge air and block objects from passing therethrough. A heated screen includes a heater and is mounted adjacent the air intake and upstream of the engine such that ice entering the air intake contacts the heated screen before entering the engine. A power source is provided to supply power to the heater. | 03-20-2014 |
20190144108 | Aircraft having Hover Stability in Inclined Flight Attitudes | 05-16-2019 |
20080223993 | HOMEOSTATIC FLYING HOVERCRAFT - A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control. | 09-18-2008 |
20080283673 | Ducted Fan Vtol Vehicles - A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | 11-20-2008 |
20090020654 | Harness with mounted engine frame - A harness with mounted engine frame comprises a harness to be worn by a user. An engine support arm is mounted on the harness and a pair of lateral arms extend from the engine support arm. At least one engine is associated with each lateral arm. A connector attaches directly or indirectly to the harness for receiving the engine support arm, so that the engine support arm is movable relative to the harness in response to engine output and other flight conditions. | 01-22-2009 |
20090121087 | High speed vertical take-off and land aircraft with active fan balancing system - A high-speed vertical take-off and land aircraft includes a body with an engine supported by the body. A fan assembly is also carried by the body. The fan assembly includes a hub and a plurality of blades to provide vertical lift for the aircraft. A nozzle ring is provided on the fan assembly. The nozzle ring includes an annular nozzle array. Hot gases from the engine are fed to the nozzle array by a feed duct. A bearing mechanism supports the fan assembly on the body. The bearing mechanism is carried in a work space. A brush seal assembly thermally isolates the work space from the hot exhaust gases passing through the feed duct to the nozzle array. | 05-14-2009 |
20090159757 | Ducted Fan Vtol Vehicles - A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | 06-25-2009 |
20090250557 | Whirling Wheel Airborne Vehicles - A sliding-arm whirling wheel thruster includes first and second whirling wheels and a housing. The first whirling wheel is disposed about a first rotational axis, and the second whirling wheel about a second rotational axis parallel to the first rotational axis. The housing comprises an arc over an enclosed space into which the first and second whirling wheels fit. The air blown outward by each of the whirling wheels is amassed inside the housing so as to make a pressure difference between inside and outside of the housing. The relative position of the first rotational axis to the second rotational axis is configured to be controlled. The airborne vehicle is lifted by buoyant force caused by the pressure difference. | 10-08-2009 |
20100012790 | GYRO-STABILIZED AIR VEHICLE - A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage. | 01-21-2010 |
20100019098 | Ducted Fan Core for Use with an Unmanned Aerial Vehicle - A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame, attached to which are an engine, gearbox assembly, fan, and a plurality of control vanes. A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle. | 01-28-2010 |
20100051753 | WALL EFFECTS ON VTOL VEHICLES - ducted air flow vehicle that includes a fuselage having a longitudinal axis, supporting at least one air flow duct and a prime mover arranged to force surrounding air into the duct through an inlet at an upper end of the duct with normally symmetrical airflow streams, thereby creating a lift force directed substantially along a duct axis; a plurality of vanes extending across the inlet, substantially parallel to the longitudinal axis; and wherein one or more groups of the vanes are selectively pivotable to align with adjacent abnormal asymmetrical airflow streams. | 03-04-2010 |
20100078523 | Tandem powered power tilting tilt rotor aircraft - An aircraft with a long body | 04-01-2010 |
20100127131 | System and Method For a Fuel Bladder Assembly With Embossed Film - Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto. The fuel bladder may include an embossed pattern disposed to prevent a vacuum being formed by the collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV). | 05-27-2010 |
20100140415 | VERTICAL TAKE OFF AND LANDING UNMANNED AERIAL VEHICLE AIRFRAME STRUCTURE - An unmanned aerial vehicle selectively formed of high strength composite structural part portions and lightweight aerodynamic foam portions to provide a low-cost and lightweight UAV that comports with export, civil airspace, and safety regulations. To further to reduce an overall weight of the UAV, mechanical elements are designed to provide multiple functionalities. Structural elements may be manufactured in same or similar non-specialized processes, and non-structural elements manufactured in same or similar non-specialized processes, reducing overall manufacturing costs. Materials and bonding elements are selected to provide frangibility and yet maintain normal flight structural integrity. | 06-10-2010 |
20100140416 | Ducted Fans with Flow Control Synthetic Jet Actuators and Methods for Ducted Fan Force and Moment Control - The present invention relates to the field of aerodynamics. More particularly, the present invention relates to manipulating air flow over a surface, such as the surface of a duct of a ducted fan vehicle. By controlling air flow over, at, or around the surface of a duct, the flight of the vehicle can be controlled. One embodiment of the invention provides a vertical take-off and landing (VTOL) ducted-fan vehicle comprising means for producing steady or unsteady blowing at a surface of a duct for producing control forces and moments for controlling flight. The means for unsteady blowing can be provided by synthetic jets and the means for steady blowing can be provided by a pressurized air supply. The synthetic jets can be integrated into the ducted-fan vehicles in numerous ways, including at the surface of the leading and/or trailing edge of the ducts. The synthetic jets can be independently operated to control the flight of the vehicle. A novel use of these inventive flow control concepts is to apply the control asymmetrically to the duct in order to produce an imbalance in forces, thus resulting in a moment or torque, which can be used to control flight. | 06-10-2010 |
20100171000 | Tandem powered tilt rotor aircraft - An aircraft with a long body | 07-08-2010 |
20100320333 | Saucer-shaped gyroscopically stabilized vertical take-off and landing aircraft - An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating plate includes a groove that traces a sinusoidal pattern around an inside periphery of the plate. Tracking arms have a portion that fit within the groove and another portion that connects to a piston. The rotation of the plate causes the tracking arms to travel within the sinusoidal groove and impart movement on the plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere. | 12-23-2010 |
20110001017 | UAV DUCTED FAN SWEPT AND LEAN STATOR DESIGN - A ducted fan air-vehicle having an air duct and a fan is described. The air duct includes an outer rim and an inner rim, and the fan is located within the air duct and rotates in a direction. The fan also includes a hub, a plurality of struts extending from the hub and positioned adjacent the outer rim of the fan, a plurality of stators extending from the hub and positioned adjacent the inner rim of the fan, and a plurality of rotor blades extending from the hub and positioned between the plurality of struts and the plurality of stators. The stators are lean in a plane of fan rotation and swept in a plane normal to fan rotation to create the optimum amount of noise reduction in the ducted fan air-vehicle. | 01-06-2011 |
20110049306 | CONTROL FLOWS AND FORCES IN VTOL VEHICLES - The present application relates to VTOL vehicles with multi-function capabilities and, specifically to ducted fan arrangements that facilitate the control of forces and flows of air to control movement of the vehicle in six degrees of freedom in both primary and secondary modes of operation. Also disclosed are pitch control mechanisms for the lift propellers of VTOL vehicles: drive and transmission arrangements; a specially configured exhaust duct for directing exhaust gases from such vehicles along an upper surface of the vehicle; and shock absorbing components for the landing gear of such vehicles. | 03-03-2011 |
20110049307 | VTOL VEHICLE WITH OFFSET ENGINE - A ducted air flow vehicle includes a fuselage having a longitudinal axis, supporting forward and aft air flow ducts having respective lift fans arranged to force surrounding air into said ducts through inlets at upper ends of said ducts and out of said ducts through outlets at lower ends of said ducts, thereby creating a lift force. A single engine is located on one side of said longitudinal axis, and is operatively configured to power the lift fans. A payload bay is located in a central area of said fuselage, between the forward and aft ducts, spanning the longitudinal axis. | 03-03-2011 |
20110139939 | PERSONAL FLIGHT DEVICE INCORPORATING RADIATOR COOLING PASSAGE - A personal flight device which includes: a housing which is securable to a pilot; at least one pair of ducted fans, one fan of the pair mounted to one side of the housing, the other fan of the pair mounted to the other side of the housing; wherein each fan rotates about an axis of rotation so as to draw air through the corresponding duct from an entry end of the duct to an exit end of the duct; and wherein the axis of rotation of each fan is fixed relative to the housing; at least one engine mounted on the housing for driving the fans such that both fans rotate in the same direction for producing thrust; the or each engine being cooled by a radiator; the or each radiator being associated with at least one passage having an entry end in communication with one surface of the radiator and an exit end adjacent the entry end of one of said ducts. | 06-16-2011 |
20110147533 | MORPHING DUCTED FAN FOR VERTICAL TAKE-OFF AND LANDING VEHICLE - A morphing duct of a ducted fan for a vertical take-off and landing (VTOL) vehicle is configured to change shape as function of the flight mode of the vehicle to improve the thrust per unit energy input for the ducted fan. Additionally, the morphing duct may be configured to change shape to change the flight path of the VTOL vehicle. | 06-23-2011 |
20110155859 | AIRCRAFT VERTICAL LIFT DEVICE - A lift device is disclosed that can be used to provide vertical lift to an aircraft or other vehicle. The lift device can include a fan that produces an airflow and a vane box that can direct the airflow. In one form the fan can be oriented at an angle relative to a reference plane in the aircraft. In another form the vane box can be oriented at an angle. The vane box can be structured to provide a maximum flow area between an aft flow vector and a forward flow vector. | 06-30-2011 |
20110155860 | FLUID DYNAMIC DEVICE WITH THRUST CONTROL SHROUD - A fluid dynamic device ( | 06-30-2011 |
20110210212 | Tilt rotor aircraft with tilting tail rotor - TT - A vertical take-off aircraft comprising a main power plant | 09-01-2011 |
20110266397 | SOLAR THERMAL ROTORCRAFT - A vehicle includes a housing having a wall with a central port and radial port formed at a lower portion of the housing, a blower disposed within the housing to move air through the central port, a distributor coupled to the blower to distribute air inside the housing, a heat-absorbing body disposed within the housing to absorb thermal energy, and at least one arm coupled to the housing. | 11-03-2011 |
20120056040 | Electric VTOL Aircraft - An electric and hybrid Vertical-Take Off and Landing (“VTOL”) aircraft is disclosed comprising a plurality of small Electric Ducted Fans (“EDFs”) of various sizes and orientations. The thrust of each fixed EDF is individually controlled by modulation of motor power by one or more onboard microcomputers connected to a plurality of onboard laser distance measuring sensors, at least three onboard three-axis accelerometers and at least one GPS thereby allowing extremely precise and safe VTOL operation. The aircraft may be employed to allow robotic and passenger vehicles to transition extremely quickly between normal linear flight and VTOL and tb operate in extreme and gusty conditions. | 03-08-2012 |
20120080564 | DUCTED PLATFORMS - A ducted fan for a VTOL vehicle includes a substantially cylindrical duct having an inlet at an upper end and an outlet at a lower end, and an air mover unit located within the substantially cylindrical duct. The duct also includes inner and outer wall portions and a substantially annular upper lip connecting the inner and outer wall portions, thus defining the inlet. The substantially annular upper lip has opposed fore and aft portions and opposed side portions and is provided with at least first and second openings, respectively, at each of the opposed side portions. The first and second arrays of openings permit flow of air into at least first and second respective chambers formed within the duct, the first and second chambers connected by at least one passageway to thereby enable substantial equalization of surface pressure at the opposed side portions of the substantially annular upper lip. | 04-05-2012 |
20120091284 | UNMANNED AERIAL VEHICLE - The various embodiments of the present invention provide an unmanned aerial vehicle comprising a hemispherical body, a brushless type electrical, a propeller, a plurality of wingtip devices, a plurality of servomotors and each of the plurality of the servomotors is connected to each of the plurality of the wingtip devices respectively, a plurality of carbon rods, and a casing. The brushless type electrical motor provides a lifting force for a Vertical take-off and landing (VTOL) and the plurality of wing tip devices are classified into three types of wing tip devices and the three types of wing tip devices are controlled by the respective servomotors to control yaw, pitch and roll movements thereby stabilizing and controlling the movement of an aircraft. | 04-19-2012 |
20120126064 | UAV DUCTED FAN LIP SHAPING - A ducted fan air-vehicle having a duct lip shape is described. The duct lip has an internal duct lip portion and an external duct lip portion, both of which are substantially curvature continuous around the circumference of the air duct. The duct has a plurality of cross-sections along its circumference and at least some of the plurality of cross-sections have a different shape. Further, each cross-section around the circumference of the duct has an a/b ratio and the a/b ratio for each cross-section is substantially the same. | 05-24-2012 |
20120153087 | Modular Pods for Use with an Unmanned Aerial Vehicle - A pod for an unmanned aerial vehicle is provided that may be removed and re-attached to the vehicle. The pod comprises an outer shell, within which a variety of payloads may be carried. A first surface on the vehicle frame comprises a plurality of connects or electrical traces. The plurality of attachments are used to removably attach the pods to the first surface. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle. | 06-21-2012 |
20120234984 | Integrated Duct Design for an Unmanned Aerial Vehicle - A ducted fan air vehicle having increased storage capacity inside the duct for equipment and electronics provides improved airflow and fan efficiency over ducted fan air vehicles carrying cargo in external pods. The outside of the duct may extend outwardly to allow equipment and electronics to be stored inside the duct in storage areas located at intervals along the duct. The storage areas may form a square duct having a circular inside wall. Additionally, the storage areas may extend in the direction of the axis of rotation of the fan to provide additional storage above the lower lip of the duct. | 09-20-2012 |
20130068895 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 03-21-2013 |
20130105635 | QUAD TILT ROTOR VERTICAL TAKE OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV) WITH 45 DEGREE ROTORS | 05-02-2013 |
20130126680 | UNMANNED AIR VEHICLE FAULT TOLERANT FLIGHT CONTROL SYSTEM AND METHOD - Methods and apparatus are provided for controlling an unmanned air vehicle (UAV) that includes a plurality of independently controllable control vanes. Control vane position commands are supplied that will move each of the control vanes to a position that will cause the UAV to implement a commanded maneuver. Inoperability of one of the control vanes is sensed, and the position of the inoperable control vane is determined New control vane position commands are determined, based on the determined position of the inoperable control vane, which will also cause the UAV to implement the commanded maneuver. | 05-23-2013 |
20130134263 | WINGLESS HOVERING OF MICRO AIR VEHICLE - Embodiments of the subject invention relate to an air vehicle and a power source. Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | 05-30-2013 |
20130140404 | SYSTEM AND METHOD FOR IMPROVING TRANSITION LIFT-FAN PERFORMANCE - A system and method enabled to increase efficiency during a VTOL aircraft's transition. A VTOL aircraft enabled to operate multiple lift fans arranged into separately controllable groups, wherein the VTOL aircraft initially has vertical flight but transitions to horizontal flight. A first group of lift fans may be kept at full throttle, a second group of lift fans may be throttled to balance thrust and/or weight, and a third group of lift fans may be shut off. | 06-06-2013 |
20130206919 | SYSTEMS AND METHODS FOR CONTROLLING AN AERIAL UNIT - An aerial unit that includes a first propeller; a second propeller that is spaced apart from the first propeller and is below the first propeller; a propelling module that is configured to rotate the first propeller and the second propeller about a first axis; an apertured duct that comprises a first duct portion and a second duct portion. The first duct portion surrounds the first propeller. The second duct portion surrounds the second propeller. The apertured duct defines at least one aperture at an intermediate area that is positioned below the first propeller and is above the second propeller. The aggregate size of the at least one aperture is at least fifty percent of a size of the intermediate area; a frame; and at least one steering element; an interfacing module arranged to be connected to a connecting element that couples the aerial unit to a ground unit. The propelling module and the duct are connected to the frame. | 08-15-2013 |
20140048657 | CROSS FLOW FAN FLYING DEVICE - A cross flow fan flying device includes a first thrusting means having a first cross flow fan and a second thrusting means having a second cross flow fan, wherein the first flow fan and the second cross flow fan rotate in directions opposite with each other, and the cross flow fan flying device is driven and flies by airflow thrust generated by the first cross flow fan and the second cross flow fan. | 02-20-2014 |
20140158832 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 06-12-2014 |
20140263849 | PERSONAL PROPULSION DEVICES WITH IMPROVED BALANCE - A personal propulsion device, including a platform configured to support a passenger's body; and at least one fluid discharge nozzle coupled to the platform and angled with respect to the platform, where the angle defined between the nozzle and the platform is between approximately 95° and 120°; where the personal propulsion device is configured to receive pressurized fluid from a remote pressurized fluid source, and where the personal propulsion device is configured to achieve flight. | 09-18-2014 |
20140332634 | MULTI-PURPOSE PERSONAL PROPULSION SYSTEM - A personal propulsion system, including an assembly adapted to support a passenger and achieve flight through the discharge of pressurized fluid; and a pressurized fluid source in fluid communication with the assembly, where the pressurized fluid source does not achieve flight, and where the pressurized fluid source is constructed at least in part from one or more ballistic armor materials. | 11-13-2014 |
20140332635 | TANDEM PERSONAL PROPULSION DEVICE - A personal propulsion device, including a passenger assembly configured to support a plurality of passengers, the passenger assembly including one or more nozzles adapted to discharge pressurized fluid; and a pressurized fluid source in fluid communication with the passenger assembly, where the passenger assembly is capable of achieving flight by discharging pressurized fluid provided by the pressurized fluid source. The pressurized fluid source may be a personal watercraft, and the passenger assembly may be configured to support two passengers positioned side-by-side, one in front of the other, or facing different directions. | 11-13-2014 |
20150053826 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - There is provided a vertical take-off and landing aircraft including: a propulsion mechanism for generating lift and thrust; a power supply unit (e.g. an engine as a power source) for supplying power to the propulsion mechanism; a main frame for supporting the engine, a seat, and a landing undercarriage; a sub-frame for supporting the propulsion mechanism; a frame coupling unit for rotatably coupling the main frame and the sub-frame; and a control stick connected to the sub-frame, so that an occupant sitting on a seat operates a control stick thereby to move the sub-frame relative to the main frame so as to change the orientation of the propulsion mechanism. | 02-26-2015 |
20150108282 | FLOATING MOBILE OBJECT AND FLOATING MOBILE SYSTEM USING THE SAME - A holonomic floating mobile object is operated under gravity and includes a main body and six or more thrusters for generating thrust by changing the momentum of a fluid. The six or more thrusters are controlled independently of one another such that the thrust is set at a desired value. The six or more thrusters are arranged in a fuselage coordinate system defined on the main body, such that the range in which a total thrust vector obtained by combining vectors of the thrust generated by all of the thrusters can be generated spans a six-dimensional space with three directions of translation and three directions of rotation. Incoming and outgoing flows to and from one of the thrusters are spaced apart from incoming and outgoing flows to and from the other thrusters and even apart from every other fuselage structure aside from that one thruster. | 04-23-2015 |
20150360776 | VERTICAL TAKE-OFF AND LANDING AERIAL VEHICLE - A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The control system being able to control the orientation of the inner frame. The gimbal system connecting the inner frame to the outer frame with at least two rotation axis allowing rotation freedom between the outer frame to rotate independently from the inner frame. | 12-17-2015 |
20160101852 | Annular ducted lift fan VTOL aircraft - The invention is an annular ducted lift fan system for a VTOL type aircraft. In detail, the invention comprises an annular duct, a lift fan set, engines, a central fuselage, a peripheral wing, and means for pneumatic coupling or mechanic coupling of engines and the lift fan set. The lift fan set is mounted in the annular duct and powered by the engines through pneumatic coupling or mechanic coupling. The annular duct is opened with the lift fan set working to provide high lift efficiency in VTOL mode and transition mode and is closed off to reduce drag in cruise mode. | 04-14-2016 |
20160376002 | Aircraft with Rotating Outer Shell - An aircraft having a main body defining a passenger compartment therein, an upper shell portion above the main body and a lower shell portion below the main body, further includes a motor assembly operatively connected between the upper shell portion, the lower shell portion and the main body so as to be arranged to drive rotation of the upper and lower shell portions relative to the main body in opposing directions relative to one another. An engine assembly is supported on the main body in communication with a central thrust opening in the lower shell portion so as to be arranged to provide upward thrust to the main body. | 12-29-2016 |
20180022467 | SINGLE ENGINE, ASYMMETRICAL VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT | 01-25-2018 |
20090140102 | Ducted fan vehicles particularly useful as VTOL aircraft - A vehicle, including a vehicle frame, a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame, a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid therethrough from its inlet at the upper end of the duct through its exit at the lower end of the duct, and thereby to produce an upward lift force applied to the vehicle, and a plurality of parallel, spaced vanes pivotally mounted to and across the inlet end of the duct about pivotal axes perpendicular to the longitudinal axis of the duct and substantially parallel to the longitudinal axis of the vehicle frame, the vanes being selectively pivotal about their axes to produce a desired horizontal force component to the lift force applied to the vehicle. | 06-04-2009 |
20090140103 | Vehicle with vertical lift - An apparatus for producing vertical lift in a vehicle. In one embodiment, two sets of trans-flow fans discharge air through multi-directional vane assemblies that direct the discharged air outward and downward. Each one of the sets of fans is positioned on opposite sides of the vehicle. The multi-directional vane assemblies include vertical vanes that direct the discharged air fore and aft and horizontal vanes that direct the discharged air downward at various angles. In one embodiment, the vehicle includes a hovercraft skirt and a portion of the discharge air is directed into the skirt, causing the vehicle lift vertically on a cushion of air. In one such embodiment, a flow director controls the amount of discharged air flowing through the inlet to the volume defined by the skirt. | 06-04-2009 |
20110180671 | DIFFERENTIAL VANE VEHICLE CONTROL - A ducted fan air-vehicle capable of generating control moments. The ducted fan air-vehicle includes an air duct, a fan, a center body, a plurality of control vanes. The vanes are independently controlled and are deflected in the same direction but at different angles, thereby providing an increased control moments to the vehicle compared to the prior art. The increased pitching moment allows for additional control authority. Additional control authority is useful in forward flight and is especially desirable when the ducted fan air-vehicle is maneuvering in unsteady or turbulent winds or with various types of cargo that may effect the vehicle center of gravity location. | 07-28-2011 |
20140054423 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 02-27-2014 |
20140061390 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 03-06-2014 |
244023000 | Thrust diverters | 5 |
20080302920 | Aerial Lifting and Propulsion Device (ALPD) - This invention, an Aerial Lifting and Propulsion Device, introduces an aircraft and aircraft wing design that has an outer and inner circumference, both of which are employed in the entirety of each to evacuate air, air space, and/or atmosphere from above the circular wing/craft, to the area beneath the circular wing/craft, through the use of a propeller inside the inner circumference of the circular wing, and impellers at the outer circumference of the circular wing. When the air, air space, and/or atmosphere forced from above the circular wing into the area beneath the circular wing and propeller attempts to escape to the top of the circular wing to fill the newly created low pressure area above the circular wing, it is intercepted at the lower edge of the outer circumference of the circular wing and forced to returned to the area beneath the circular wing, where the atmospheric pressure is further increased or decreased at will, depending on the pitch and speed of the aircraft propeller and impeller blades. The noted reduced atmospheric pressure at the top of the circular wing, and the higher controlled atmospheric pressure in the area beneath the circular wing and propeller, forces the circular wing upward from its stationary position, achieving lift as described in Bernoulli's Principle. Stabilization and directional control is maintained through adjustments in the pitch of the impeller and propeller and the effects of torque are neutralized by the rotation of the impeller and propeller assemblies in opposite directions. The Aerial Lifting and Propulsion Device maintains its upright configuration while airborne in part because its center of gravity is well below the points where lift is generated. | 12-11-2008 |
20090084907 | Ground Effect Vanes Arrangement - A vehicle, particularly a VTOL air vehicle, includes a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame; a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid therethrough from its inlet at the upper end of the duct through its exit at the lower end of the duct, and thereby to produce an upward lift force applied to the vehicle, and a plurality of spaced vanes mounted to and across the inlet and exit ends of the duct about axes substantially perpendicular to the longitudinal axis of the duct and selectively operational to produce a desired horizontal control force in addition to the lift force applied to the vehicle. | 04-02-2009 |
20100001143 | Discoidal flying craft - A flying craft has an aerodynamic aircraft fuselage structure preferably disc shaped. A pair of coaxial electrokinetic motor-generators are mounted concentrically, and preferably centered within the disc shaped structure of the craft. Each of the motors is toroidal in configuration, providing a ring-shaped stator and rotor portions. The rotor portions of the motors drive counter rotating fans which are electro-magnetically levitated. The structure is open to the fans so that air may be drawn into the structure and expelled downward providing vertical lift to the aircraft. By use of auxiliary air braking flaps and electrokinetic thrusters, the craft may be tilted so as to develop a desired horizontal thrust. By impulse breaking one of the fans through tracking solenoids at different points around the stator, the aircraft may be made to rotate about its own vertical axis for changing direction. By a series of sudden braking of the motors the craft may be made to move by inertial reaction. | 01-07-2010 |
20120068021 | CRAFT AND METHOD FOR ASSEMBLING CRAFT WITH CONTROLLED SPIN - This invention relates to a craft designed to move through or on a surface of a fluid. It is believed to be principally of use in relation to airborne craft and missiles but the theory behind the invention is equally applicable for example to submarines. | 03-22-2012 |
20140027581 | AIRCRAFT HAVING A ROTATING TURBINE ENGINE - The present invention describes an aircraft having a rotating engine. The aircraft comprises a means for rotating the engine 360° to allow directional control of the aircraft via rotation of the engine's thrust output. The aircraft can further comprise a plurality of flap members located on the wings of the aircraft and in communication with the rotating gas turbine engine to further control and stabilize flight of the aircraft. The gas turbine engine of the aircraft can comprise a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating more thrust from a single engine. | 01-30-2014 |
20150028161 | Hydraulic Passenger Lifting and Maneuvering Device - This invention relates to a fluid driven propulsion device comprising a body arranged in a manner to facilitate flight and lift for a person, passenger or object(s) with a production of thrust from a portable or fixed power unit. A power unit is designated to move an incompressible fluid via pump through a flexible pipe or transmission tube to two or more pairs of restrictive axially offset nozzles within the embodiment of the invention allowing the incompressible fluid's pressure to build and its mass to be ejected underneath the person, passenger or object(s). This fluid is expelled with such velocity to create a force, directed into multiple, generally symmetrical force vectors, sufficient to facilitate balanced, easy to master free-flight. The invention also allows for powered, active inward and outward adjustment of the axially offset pairs of nozzles, as well as powered, active aperture adjustment of each of the nozzle outlets. | 01-29-2015 |
20160144960 | PERSONAL FLUID-JET THRUST PACK WHICH PROVIDES ROTATION FOR A RIDER ABOUT THREE AXES - The present invention provides lightweight fluid-jet thrust pack which provides three rotational axes and reduced restriction of fluid flow to the output nozzles. A first rotational axis is provided by a first rotatable coupling that is concentric with a coupler for a hose supplying pressurized fluid. The top of the first coupling has a splitter which directs incoming fluid into two splayed stub supply pipes. A preformed, reinforced rubber hose connects each stub supply pipe to one of a pair of coaxial rotatable couplings at opposite ends of a tiltable cross arm assembly that is pivotally secured to tower support bracket that is secured to the first rotatable coupling. An outward rotatable portion of each of the coaxial rotatable couplings is equipped with one boot-mounting platform and a downward-projecting jet nozzle that is in communication with the stub receiver pipe of the same rotatable coupling. | 05-26-2016 |
20160152338 | AN AERODYNAMIC LIFTING DEVICE | 06-02-2016 |
20090236475 | LIFT CHAMBER - A lift device having a generally cylindrical chamber formed by a top wall, a bottom wall, an outer wall and an inner wall. A plurality of lift members are mounted to the interior of a chamber wall and at least one fan is mounted within the chamber and an engine operatively connected to at lease one fan. | 09-24-2009 |
20100025540 | Compact ultralight aircraft reduced dimensions, with vertical take-off and landing - A compact ultralight aircraft ( | 02-04-2010 |
20100051754 | Aircraft - An aircraft has a generally circular main body including an upper surface portion supported for rotation about a central passenger compartment to produce a gyroscopic effect on the aircraft. The rotatable upper surface portion includes viewable panes therein arranged to provide visibility therethrough from the central passenger compartment to an exterior of the main body. An engine communicates between a central inlet opening in the upper surface portion and an exhaust opening in the bottom of the main body to provide upward thrust to the aircraft. | 03-04-2010 |
20100102174 | Wingless Hovering Of Micro Air Vehicle - Embodiments of the subject invention relate to a Wingless Hovering Micro Air Vehicle (WHOMAV) and its Power Source Unit (PSU). Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments of the subject invention can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | 04-29-2010 |
20100187369 | DUCTED FAN UAV CONTROL ALTERNATIVES - A ducted fan air-vehicle having alternative methods of control is described. The ducted fan air-vehicle includes an air duct, a fan, a center body, a plurality of control vanes. Each control vanes includes a separate servo for independent control of each control vane, and is therefore able to operate the control vanes in a non-traditional manner to provide maximum control authority. | 07-29-2010 |
20100282918 | Saucer shaped gyroscopically stabilized vertical take-off and landing aircraft - An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating sine-wave ring is used to activate and move a plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere. | 11-11-2010 |
20100288889 | SPRING FLYING DEVICE - The Spring flying device ( | 11-18-2010 |
20130181095 | DEVICE TO GENERATE LIFT FORCE (OPTIONS) - The options of the invention relate to the aviation and can be used in order to create lifting vehicle as well as load lifting devices. In order to achieve technical result—the decrease of energy losses on the while creating and change of vector of moving, aerodynamic, composite force, including as a component a lift force,—in the device to generate lift force containing a tubiform frame, superchargers, the wings having in section an aerofoil profile oriented by the leading edge to the direction of working medium exhaust out of the super-charger, adjusting units for a wing, guiding devices, each of those is installed in front of leading edge of each wing, the system to maintain the required working temperature of medium, unit to connect outdoor environment, as per the invention in the first option of the device a tubiform frame is of the form of a tore, in the second option—the form of closed volumetric loop, in the third option—a cylindrical form. Meanwhile each option of the device is equipped with relevant distinguishing units, providing the achieving of a technical result. | 07-18-2013 |
20130306802 | METHODS AND APPARATUS FOR VERTICAL SHORT TAKEOFF AND LANDING - Methods and apparatus for vertical or short takeoff and landing. In one embodiment, the apparatus comprises two or more counter driven rings with one or more airfoils attached. In one variant, there is an upper ring and a lower ring, each with multiple airfoils attached. In one variant, lift is generated largely via ambient air currents, allowing for long term on-station operation of the device. | 11-21-2013 |
20130306803 | AIRCRAFT GENERATING A LIFT FROM AN INTERIOR THEREOF - The invention discloses an aircraft generating a larger lift from its interior. The fluid channel inside the aircraft communicates with the engine and the ports on the upper surface of the outer shell. With the powerful suction of the engine, the fluid on the upper surface of the outer shell is quickly sucked into the fluid channel via respective ports under conditions of long path, large area, high speed and low air pressure, which results in large lift from the interior of the aircraft. In the course of generating the lift, the fluid resistances of the fluid wall and the fluid hole are sucked into the fluid channel through the ports at the front and the surrounding area of the aircraft, then high-speed fluid is emitted from the rear port. This approach contributes greatly to the transformation of the existing aircraft. The unified big wing significantly improves the lift, the speed and the carrying capacity of the existing aircraft with lowered energy consumption. | 11-21-2013 |
20090039206 | BIRD VORTEX FLYING MACHINE - The present invention comprises, in one embodiment, an inexpensive, lightweight flying vehicle using fixed pitch helicopter blades powered by ramjet engines mounted to a power-ring which transfers torque to the lifting rotors. The use of fixed pitch blades eliminates the need for a tail boom and tail rotor, as well as for variable incidence control of blade pitch and/or cyclic and collective rotor-pitch controls. An optional ballistic parachute may be deployed for emergency landings. A radial shroud encloses the ramjet engines to act as a sound shield. Since the rotor has a fixed pitch, lift may be controlled by rotor speed, where increased speed results in ascent, and decreased speed, descent. | 02-12-2009 |
20100193643 | LIFT FAN SYSTEM - Embodiments of the present invention include a system, e.g., for a short takeoff and vertical landing (STOVL) aircraft. The system includes a power generator, such as a gas turbine engine; a lift fan powered by the power generator; and includes two or more nozzles in fluid communication with the lift fan. | 08-05-2010 |
20110204188 | ROTOCRAFT - An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle. | 08-25-2011 |
20140077039 | Heated Screen For Air Intake Of Aircraft Engines - An aircraft includes a fuselage and wings mounted on opposite sides of the fuselage for sustained forward flight. An engine is mounted in the fuselage or at least one of the wings and includes an air intake. At least a portion of the air intake generally faces the forward direction for receiving intake air during forward flight. A filter assembly is mounted adjacent the air intake and disposed to impinge air and block objects from passing therethrough. A heated screen includes a heater and is mounted adjacent the air intake and upstream of the engine such that ice entering the air intake contacts the heated screen before entering the engine. A power source is provided to supply power to the heater. | 03-20-2014 |
20190144108 | Aircraft having Hover Stability in Inclined Flight Attitudes | 05-16-2019 |
20080223993 | HOMEOSTATIC FLYING HOVERCRAFT - A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control. | 09-18-2008 |
20080283673 | Ducted Fan Vtol Vehicles - A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | 11-20-2008 |
20090020654 | Harness with mounted engine frame - A harness with mounted engine frame comprises a harness to be worn by a user. An engine support arm is mounted on the harness and a pair of lateral arms extend from the engine support arm. At least one engine is associated with each lateral arm. A connector attaches directly or indirectly to the harness for receiving the engine support arm, so that the engine support arm is movable relative to the harness in response to engine output and other flight conditions. | 01-22-2009 |
20090121087 | High speed vertical take-off and land aircraft with active fan balancing system - A high-speed vertical take-off and land aircraft includes a body with an engine supported by the body. A fan assembly is also carried by the body. The fan assembly includes a hub and a plurality of blades to provide vertical lift for the aircraft. A nozzle ring is provided on the fan assembly. The nozzle ring includes an annular nozzle array. Hot gases from the engine are fed to the nozzle array by a feed duct. A bearing mechanism supports the fan assembly on the body. The bearing mechanism is carried in a work space. A brush seal assembly thermally isolates the work space from the hot exhaust gases passing through the feed duct to the nozzle array. | 05-14-2009 |
20090159757 | Ducted Fan Vtol Vehicles - A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | 06-25-2009 |
20090250557 | Whirling Wheel Airborne Vehicles - A sliding-arm whirling wheel thruster includes first and second whirling wheels and a housing. The first whirling wheel is disposed about a first rotational axis, and the second whirling wheel about a second rotational axis parallel to the first rotational axis. The housing comprises an arc over an enclosed space into which the first and second whirling wheels fit. The air blown outward by each of the whirling wheels is amassed inside the housing so as to make a pressure difference between inside and outside of the housing. The relative position of the first rotational axis to the second rotational axis is configured to be controlled. The airborne vehicle is lifted by buoyant force caused by the pressure difference. | 10-08-2009 |
20100012790 | GYRO-STABILIZED AIR VEHICLE - A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage. | 01-21-2010 |
20100019098 | Ducted Fan Core for Use with an Unmanned Aerial Vehicle - A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame, attached to which are an engine, gearbox assembly, fan, and a plurality of control vanes. A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle. | 01-28-2010 |
20100051753 | WALL EFFECTS ON VTOL VEHICLES - ducted air flow vehicle that includes a fuselage having a longitudinal axis, supporting at least one air flow duct and a prime mover arranged to force surrounding air into the duct through an inlet at an upper end of the duct with normally symmetrical airflow streams, thereby creating a lift force directed substantially along a duct axis; a plurality of vanes extending across the inlet, substantially parallel to the longitudinal axis; and wherein one or more groups of the vanes are selectively pivotable to align with adjacent abnormal asymmetrical airflow streams. | 03-04-2010 |
20100078523 | Tandem powered power tilting tilt rotor aircraft - An aircraft with a long body | 04-01-2010 |
20100127131 | System and Method For a Fuel Bladder Assembly With Embossed Film - Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto. The fuel bladder may include an embossed pattern disposed to prevent a vacuum being formed by the collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV). | 05-27-2010 |
20100140415 | VERTICAL TAKE OFF AND LANDING UNMANNED AERIAL VEHICLE AIRFRAME STRUCTURE - An unmanned aerial vehicle selectively formed of high strength composite structural part portions and lightweight aerodynamic foam portions to provide a low-cost and lightweight UAV that comports with export, civil airspace, and safety regulations. To further to reduce an overall weight of the UAV, mechanical elements are designed to provide multiple functionalities. Structural elements may be manufactured in same or similar non-specialized processes, and non-structural elements manufactured in same or similar non-specialized processes, reducing overall manufacturing costs. Materials and bonding elements are selected to provide frangibility and yet maintain normal flight structural integrity. | 06-10-2010 |
20100140416 | Ducted Fans with Flow Control Synthetic Jet Actuators and Methods for Ducted Fan Force and Moment Control - The present invention relates to the field of aerodynamics. More particularly, the present invention relates to manipulating air flow over a surface, such as the surface of a duct of a ducted fan vehicle. By controlling air flow over, at, or around the surface of a duct, the flight of the vehicle can be controlled. One embodiment of the invention provides a vertical take-off and landing (VTOL) ducted-fan vehicle comprising means for producing steady or unsteady blowing at a surface of a duct for producing control forces and moments for controlling flight. The means for unsteady blowing can be provided by synthetic jets and the means for steady blowing can be provided by a pressurized air supply. The synthetic jets can be integrated into the ducted-fan vehicles in numerous ways, including at the surface of the leading and/or trailing edge of the ducts. The synthetic jets can be independently operated to control the flight of the vehicle. A novel use of these inventive flow control concepts is to apply the control asymmetrically to the duct in order to produce an imbalance in forces, thus resulting in a moment or torque, which can be used to control flight. | 06-10-2010 |
20100171000 | Tandem powered tilt rotor aircraft - An aircraft with a long body | 07-08-2010 |
20100320333 | Saucer-shaped gyroscopically stabilized vertical take-off and landing aircraft - An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating plate includes a groove that traces a sinusoidal pattern around an inside periphery of the plate. Tracking arms have a portion that fit within the groove and another portion that connects to a piston. The rotation of the plate causes the tracking arms to travel within the sinusoidal groove and impart movement on the plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere. | 12-23-2010 |
20110001017 | UAV DUCTED FAN SWEPT AND LEAN STATOR DESIGN - A ducted fan air-vehicle having an air duct and a fan is described. The air duct includes an outer rim and an inner rim, and the fan is located within the air duct and rotates in a direction. The fan also includes a hub, a plurality of struts extending from the hub and positioned adjacent the outer rim of the fan, a plurality of stators extending from the hub and positioned adjacent the inner rim of the fan, and a plurality of rotor blades extending from the hub and positioned between the plurality of struts and the plurality of stators. The stators are lean in a plane of fan rotation and swept in a plane normal to fan rotation to create the optimum amount of noise reduction in the ducted fan air-vehicle. | 01-06-2011 |
20110049306 | CONTROL FLOWS AND FORCES IN VTOL VEHICLES - The present application relates to VTOL vehicles with multi-function capabilities and, specifically to ducted fan arrangements that facilitate the control of forces and flows of air to control movement of the vehicle in six degrees of freedom in both primary and secondary modes of operation. Also disclosed are pitch control mechanisms for the lift propellers of VTOL vehicles: drive and transmission arrangements; a specially configured exhaust duct for directing exhaust gases from such vehicles along an upper surface of the vehicle; and shock absorbing components for the landing gear of such vehicles. | 03-03-2011 |
20110049307 | VTOL VEHICLE WITH OFFSET ENGINE - A ducted air flow vehicle includes a fuselage having a longitudinal axis, supporting forward and aft air flow ducts having respective lift fans arranged to force surrounding air into said ducts through inlets at upper ends of said ducts and out of said ducts through outlets at lower ends of said ducts, thereby creating a lift force. A single engine is located on one side of said longitudinal axis, and is operatively configured to power the lift fans. A payload bay is located in a central area of said fuselage, between the forward and aft ducts, spanning the longitudinal axis. | 03-03-2011 |
20110139939 | PERSONAL FLIGHT DEVICE INCORPORATING RADIATOR COOLING PASSAGE - A personal flight device which includes: a housing which is securable to a pilot; at least one pair of ducted fans, one fan of the pair mounted to one side of the housing, the other fan of the pair mounted to the other side of the housing; wherein each fan rotates about an axis of rotation so as to draw air through the corresponding duct from an entry end of the duct to an exit end of the duct; and wherein the axis of rotation of each fan is fixed relative to the housing; at least one engine mounted on the housing for driving the fans such that both fans rotate in the same direction for producing thrust; the or each engine being cooled by a radiator; the or each radiator being associated with at least one passage having an entry end in communication with one surface of the radiator and an exit end adjacent the entry end of one of said ducts. | 06-16-2011 |
20110147533 | MORPHING DUCTED FAN FOR VERTICAL TAKE-OFF AND LANDING VEHICLE - A morphing duct of a ducted fan for a vertical take-off and landing (VTOL) vehicle is configured to change shape as function of the flight mode of the vehicle to improve the thrust per unit energy input for the ducted fan. Additionally, the morphing duct may be configured to change shape to change the flight path of the VTOL vehicle. | 06-23-2011 |
20110155859 | AIRCRAFT VERTICAL LIFT DEVICE - A lift device is disclosed that can be used to provide vertical lift to an aircraft or other vehicle. The lift device can include a fan that produces an airflow and a vane box that can direct the airflow. In one form the fan can be oriented at an angle relative to a reference plane in the aircraft. In another form the vane box can be oriented at an angle. The vane box can be structured to provide a maximum flow area between an aft flow vector and a forward flow vector. | 06-30-2011 |
20110155860 | FLUID DYNAMIC DEVICE WITH THRUST CONTROL SHROUD - A fluid dynamic device ( | 06-30-2011 |
20110210212 | Tilt rotor aircraft with tilting tail rotor - TT - A vertical take-off aircraft comprising a main power plant | 09-01-2011 |
20110266397 | SOLAR THERMAL ROTORCRAFT - A vehicle includes a housing having a wall with a central port and radial port formed at a lower portion of the housing, a blower disposed within the housing to move air through the central port, a distributor coupled to the blower to distribute air inside the housing, a heat-absorbing body disposed within the housing to absorb thermal energy, and at least one arm coupled to the housing. | 11-03-2011 |
20120056040 | Electric VTOL Aircraft - An electric and hybrid Vertical-Take Off and Landing (“VTOL”) aircraft is disclosed comprising a plurality of small Electric Ducted Fans (“EDFs”) of various sizes and orientations. The thrust of each fixed EDF is individually controlled by modulation of motor power by one or more onboard microcomputers connected to a plurality of onboard laser distance measuring sensors, at least three onboard three-axis accelerometers and at least one GPS thereby allowing extremely precise and safe VTOL operation. The aircraft may be employed to allow robotic and passenger vehicles to transition extremely quickly between normal linear flight and VTOL and tb operate in extreme and gusty conditions. | 03-08-2012 |
20120080564 | DUCTED PLATFORMS - A ducted fan for a VTOL vehicle includes a substantially cylindrical duct having an inlet at an upper end and an outlet at a lower end, and an air mover unit located within the substantially cylindrical duct. The duct also includes inner and outer wall portions and a substantially annular upper lip connecting the inner and outer wall portions, thus defining the inlet. The substantially annular upper lip has opposed fore and aft portions and opposed side portions and is provided with at least first and second openings, respectively, at each of the opposed side portions. The first and second arrays of openings permit flow of air into at least first and second respective chambers formed within the duct, the first and second chambers connected by at least one passageway to thereby enable substantial equalization of surface pressure at the opposed side portions of the substantially annular upper lip. | 04-05-2012 |
20120091284 | UNMANNED AERIAL VEHICLE - The various embodiments of the present invention provide an unmanned aerial vehicle comprising a hemispherical body, a brushless type electrical, a propeller, a plurality of wingtip devices, a plurality of servomotors and each of the plurality of the servomotors is connected to each of the plurality of the wingtip devices respectively, a plurality of carbon rods, and a casing. The brushless type electrical motor provides a lifting force for a Vertical take-off and landing (VTOL) and the plurality of wing tip devices are classified into three types of wing tip devices and the three types of wing tip devices are controlled by the respective servomotors to control yaw, pitch and roll movements thereby stabilizing and controlling the movement of an aircraft. | 04-19-2012 |
20120126064 | UAV DUCTED FAN LIP SHAPING - A ducted fan air-vehicle having a duct lip shape is described. The duct lip has an internal duct lip portion and an external duct lip portion, both of which are substantially curvature continuous around the circumference of the air duct. The duct has a plurality of cross-sections along its circumference and at least some of the plurality of cross-sections have a different shape. Further, each cross-section around the circumference of the duct has an a/b ratio and the a/b ratio for each cross-section is substantially the same. | 05-24-2012 |
20120153087 | Modular Pods for Use with an Unmanned Aerial Vehicle - A pod for an unmanned aerial vehicle is provided that may be removed and re-attached to the vehicle. The pod comprises an outer shell, within which a variety of payloads may be carried. A first surface on the vehicle frame comprises a plurality of connects or electrical traces. The plurality of attachments are used to removably attach the pods to the first surface. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle. | 06-21-2012 |
20120234984 | Integrated Duct Design for an Unmanned Aerial Vehicle - A ducted fan air vehicle having increased storage capacity inside the duct for equipment and electronics provides improved airflow and fan efficiency over ducted fan air vehicles carrying cargo in external pods. The outside of the duct may extend outwardly to allow equipment and electronics to be stored inside the duct in storage areas located at intervals along the duct. The storage areas may form a square duct having a circular inside wall. Additionally, the storage areas may extend in the direction of the axis of rotation of the fan to provide additional storage above the lower lip of the duct. | 09-20-2012 |
20130068895 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 03-21-2013 |
20130105635 | QUAD TILT ROTOR VERTICAL TAKE OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV) WITH 45 DEGREE ROTORS | 05-02-2013 |
20130126680 | UNMANNED AIR VEHICLE FAULT TOLERANT FLIGHT CONTROL SYSTEM AND METHOD - Methods and apparatus are provided for controlling an unmanned air vehicle (UAV) that includes a plurality of independently controllable control vanes. Control vane position commands are supplied that will move each of the control vanes to a position that will cause the UAV to implement a commanded maneuver. Inoperability of one of the control vanes is sensed, and the position of the inoperable control vane is determined New control vane position commands are determined, based on the determined position of the inoperable control vane, which will also cause the UAV to implement the commanded maneuver. | 05-23-2013 |
20130134263 | WINGLESS HOVERING OF MICRO AIR VEHICLE - Embodiments of the subject invention relate to an air vehicle and a power source. Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | 05-30-2013 |
20130140404 | SYSTEM AND METHOD FOR IMPROVING TRANSITION LIFT-FAN PERFORMANCE - A system and method enabled to increase efficiency during a VTOL aircraft's transition. A VTOL aircraft enabled to operate multiple lift fans arranged into separately controllable groups, wherein the VTOL aircraft initially has vertical flight but transitions to horizontal flight. A first group of lift fans may be kept at full throttle, a second group of lift fans may be throttled to balance thrust and/or weight, and a third group of lift fans may be shut off. | 06-06-2013 |
20130206919 | SYSTEMS AND METHODS FOR CONTROLLING AN AERIAL UNIT - An aerial unit that includes a first propeller; a second propeller that is spaced apart from the first propeller and is below the first propeller; a propelling module that is configured to rotate the first propeller and the second propeller about a first axis; an apertured duct that comprises a first duct portion and a second duct portion. The first duct portion surrounds the first propeller. The second duct portion surrounds the second propeller. The apertured duct defines at least one aperture at an intermediate area that is positioned below the first propeller and is above the second propeller. The aggregate size of the at least one aperture is at least fifty percent of a size of the intermediate area; a frame; and at least one steering element; an interfacing module arranged to be connected to a connecting element that couples the aerial unit to a ground unit. The propelling module and the duct are connected to the frame. | 08-15-2013 |
20140048657 | CROSS FLOW FAN FLYING DEVICE - A cross flow fan flying device includes a first thrusting means having a first cross flow fan and a second thrusting means having a second cross flow fan, wherein the first flow fan and the second cross flow fan rotate in directions opposite with each other, and the cross flow fan flying device is driven and flies by airflow thrust generated by the first cross flow fan and the second cross flow fan. | 02-20-2014 |
20140158832 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 06-12-2014 |
20140263849 | PERSONAL PROPULSION DEVICES WITH IMPROVED BALANCE - A personal propulsion device, including a platform configured to support a passenger's body; and at least one fluid discharge nozzle coupled to the platform and angled with respect to the platform, where the angle defined between the nozzle and the platform is between approximately 95° and 120°; where the personal propulsion device is configured to receive pressurized fluid from a remote pressurized fluid source, and where the personal propulsion device is configured to achieve flight. | 09-18-2014 |
20140332634 | MULTI-PURPOSE PERSONAL PROPULSION SYSTEM - A personal propulsion system, including an assembly adapted to support a passenger and achieve flight through the discharge of pressurized fluid; and a pressurized fluid source in fluid communication with the assembly, where the pressurized fluid source does not achieve flight, and where the pressurized fluid source is constructed at least in part from one or more ballistic armor materials. | 11-13-2014 |
20140332635 | TANDEM PERSONAL PROPULSION DEVICE - A personal propulsion device, including a passenger assembly configured to support a plurality of passengers, the passenger assembly including one or more nozzles adapted to discharge pressurized fluid; and a pressurized fluid source in fluid communication with the passenger assembly, where the passenger assembly is capable of achieving flight by discharging pressurized fluid provided by the pressurized fluid source. The pressurized fluid source may be a personal watercraft, and the passenger assembly may be configured to support two passengers positioned side-by-side, one in front of the other, or facing different directions. | 11-13-2014 |
20150053826 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - There is provided a vertical take-off and landing aircraft including: a propulsion mechanism for generating lift and thrust; a power supply unit (e.g. an engine as a power source) for supplying power to the propulsion mechanism; a main frame for supporting the engine, a seat, and a landing undercarriage; a sub-frame for supporting the propulsion mechanism; a frame coupling unit for rotatably coupling the main frame and the sub-frame; and a control stick connected to the sub-frame, so that an occupant sitting on a seat operates a control stick thereby to move the sub-frame relative to the main frame so as to change the orientation of the propulsion mechanism. | 02-26-2015 |
20150108282 | FLOATING MOBILE OBJECT AND FLOATING MOBILE SYSTEM USING THE SAME - A holonomic floating mobile object is operated under gravity and includes a main body and six or more thrusters for generating thrust by changing the momentum of a fluid. The six or more thrusters are controlled independently of one another such that the thrust is set at a desired value. The six or more thrusters are arranged in a fuselage coordinate system defined on the main body, such that the range in which a total thrust vector obtained by combining vectors of the thrust generated by all of the thrusters can be generated spans a six-dimensional space with three directions of translation and three directions of rotation. Incoming and outgoing flows to and from one of the thrusters are spaced apart from incoming and outgoing flows to and from the other thrusters and even apart from every other fuselage structure aside from that one thruster. | 04-23-2015 |
20150360776 | VERTICAL TAKE-OFF AND LANDING AERIAL VEHICLE - A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The control system being able to control the orientation of the inner frame. The gimbal system connecting the inner frame to the outer frame with at least two rotation axis allowing rotation freedom between the outer frame to rotate independently from the inner frame. | 12-17-2015 |
20160101852 | Annular ducted lift fan VTOL aircraft - The invention is an annular ducted lift fan system for a VTOL type aircraft. In detail, the invention comprises an annular duct, a lift fan set, engines, a central fuselage, a peripheral wing, and means for pneumatic coupling or mechanic coupling of engines and the lift fan set. The lift fan set is mounted in the annular duct and powered by the engines through pneumatic coupling or mechanic coupling. The annular duct is opened with the lift fan set working to provide high lift efficiency in VTOL mode and transition mode and is closed off to reduce drag in cruise mode. | 04-14-2016 |
20160376002 | Aircraft with Rotating Outer Shell - An aircraft having a main body defining a passenger compartment therein, an upper shell portion above the main body and a lower shell portion below the main body, further includes a motor assembly operatively connected between the upper shell portion, the lower shell portion and the main body so as to be arranged to drive rotation of the upper and lower shell portions relative to the main body in opposing directions relative to one another. An engine assembly is supported on the main body in communication with a central thrust opening in the lower shell portion so as to be arranged to provide upward thrust to the main body. | 12-29-2016 |
20180022467 | SINGLE ENGINE, ASYMMETRICAL VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT | 01-25-2018 |
20090140102 | Ducted fan vehicles particularly useful as VTOL aircraft - A vehicle, including a vehicle frame, a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame, a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid therethrough from its inlet at the upper end of the duct through its exit at the lower end of the duct, and thereby to produce an upward lift force applied to the vehicle, and a plurality of parallel, spaced vanes pivotally mounted to and across the inlet end of the duct about pivotal axes perpendicular to the longitudinal axis of the duct and substantially parallel to the longitudinal axis of the vehicle frame, the vanes being selectively pivotal about their axes to produce a desired horizontal force component to the lift force applied to the vehicle. | 06-04-2009 |
20090140103 | Vehicle with vertical lift - An apparatus for producing vertical lift in a vehicle. In one embodiment, two sets of trans-flow fans discharge air through multi-directional vane assemblies that direct the discharged air outward and downward. Each one of the sets of fans is positioned on opposite sides of the vehicle. The multi-directional vane assemblies include vertical vanes that direct the discharged air fore and aft and horizontal vanes that direct the discharged air downward at various angles. In one embodiment, the vehicle includes a hovercraft skirt and a portion of the discharge air is directed into the skirt, causing the vehicle lift vertically on a cushion of air. In one such embodiment, a flow director controls the amount of discharged air flowing through the inlet to the volume defined by the skirt. | 06-04-2009 |
20110180671 | DIFFERENTIAL VANE VEHICLE CONTROL - A ducted fan air-vehicle capable of generating control moments. The ducted fan air-vehicle includes an air duct, a fan, a center body, a plurality of control vanes. The vanes are independently controlled and are deflected in the same direction but at different angles, thereby providing an increased control moments to the vehicle compared to the prior art. The increased pitching moment allows for additional control authority. Additional control authority is useful in forward flight and is especially desirable when the ducted fan air-vehicle is maneuvering in unsteady or turbulent winds or with various types of cargo that may effect the vehicle center of gravity location. | 07-28-2011 |
20140054423 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 02-27-2014 |
20140061390 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 03-06-2014 |