| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244023000 | Fluid sustained | 48 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20100025540 | Compact ultralight aircraft reduced dimensions, with vertical take-off and landing - A compact ultralight aircraft ( | 02-04-2010 |
| 20100288889 | SPRING FLYING DEVICE - The Spring flying device ( | 11-18-2010 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20130068895 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 03-21-2013 |
| 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 |
| 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 |
| 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 |
| 20110210212 | Tilt rotor aircraft with tilting tail rotor - TT - A vertical take-off aircraft comprising a main power plant | 09-01-2011 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20100078523 | Tandem powered power tilting tilt rotor aircraft - An aircraft with a long body | 04-01-2010 |
| 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 |
| 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 |
| 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 |
| 20100171000 | Tandem powered tilt rotor aircraft - An aircraft with a long body | 07-08-2010 |
| 20110155860 | FLUID DYNAMIC DEVICE WITH THRUST CONTROL SHROUD - A fluid dynamic device ( | 06-30-2011 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 244023000 | Lifting thrusters | 31 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20100025540 | Compact ultralight aircraft reduced dimensions, with vertical take-off and landing - A compact ultralight aircraft ( | 02-04-2010 |
| 20100288889 | SPRING FLYING DEVICE - The Spring flying device ( | 11-18-2010 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20130068895 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 03-21-2013 |
| 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 |
| 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 |
| 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 |
| 20110210212 | Tilt rotor aircraft with tilting tail rotor - TT - A vertical take-off aircraft comprising a main power plant | 09-01-2011 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20100078523 | Tandem powered power tilting tilt rotor aircraft - An aircraft with a long body | 04-01-2010 |
| 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 |
| 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 |
| 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 |
| 20100171000 | Tandem powered tilt rotor aircraft - An aircraft with a long body | 07-08-2010 |
| 20110155860 | FLUID DYNAMIC DEVICE WITH THRUST CONTROL SHROUD - A fluid dynamic device ( | 06-30-2011 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 244023000 | Dual propulsion means, horizontal and vertical | 3 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20100025540 | Compact ultralight aircraft reduced dimensions, with vertical take-off and landing - A compact ultralight aircraft ( | 02-04-2010 |
| 20100288889 | SPRING FLYING DEVICE - The Spring flying device ( | 11-18-2010 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20130068895 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 03-21-2013 |
| 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 |
| 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 |
| 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 |
| 20110210212 | Tilt rotor aircraft with tilting tail rotor - TT - A vertical take-off aircraft comprising a main power plant | 09-01-2011 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20100078523 | Tandem powered power tilting tilt rotor aircraft - An aircraft with a long body | 04-01-2010 |
| 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 |
| 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 |
| 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 |
| 20100171000 | Tandem powered tilt rotor aircraft - An aircraft with a long body | 07-08-2010 |
| 20110155860 | FLUID DYNAMIC DEVICE WITH THRUST CONTROL SHROUD - A fluid dynamic device ( | 06-30-2011 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 244023000 | Circular configuration | 7 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20100025540 | Compact ultralight aircraft reduced dimensions, with vertical take-off and landing - A compact ultralight aircraft ( | 02-04-2010 |
| 20100288889 | SPRING FLYING DEVICE - The Spring flying device ( | 11-18-2010 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20130068895 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 03-21-2013 |
| 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 |
| 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 |
| 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 |
| 20110210212 | Tilt rotor aircraft with tilting tail rotor - TT - A vertical take-off aircraft comprising a main power plant | 09-01-2011 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20100078523 | Tandem powered power tilting tilt rotor aircraft - An aircraft with a long body | 04-01-2010 |
| 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 |
| 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 |
| 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 |
| 20100171000 | Tandem powered tilt rotor aircraft - An aircraft with a long body | 07-08-2010 |
| 20110155860 | FLUID DYNAMIC DEVICE WITH THRUST CONTROL SHROUD - A fluid dynamic device ( | 06-30-2011 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 244023000 | Thrust diverters | 3 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20100025540 | Compact ultralight aircraft reduced dimensions, with vertical take-off and landing - A compact ultralight aircraft ( | 02-04-2010 |
| 20100288889 | SPRING FLYING DEVICE - The Spring flying device ( | 11-18-2010 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20130068895 | Device and System for Propelling a Passenger - The invention relates to a propulsion device ( | 03-21-2013 |
| 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 |
| 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 |
| 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 |
| 20110210212 | Tilt rotor aircraft with tilting tail rotor - TT - A vertical take-off aircraft comprising a main power plant | 09-01-2011 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20100078523 | Tandem powered power tilting tilt rotor aircraft - An aircraft with a long body | 04-01-2010 |
| 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 |
| 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 |
| 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 |
| 20100171000 | Tandem powered tilt rotor aircraft - An aircraft with a long body | 07-08-2010 |
| 20110155860 | FLUID DYNAMIC DEVICE WITH THRUST CONTROL SHROUD - A fluid dynamic device ( | 06-30-2011 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
