Class / Patent application number | Description | Number of patent applications / Date published |
244170190 | With auxiliary propulsion, counter-troque or steering device | 71 |
20090008498 | Aircraft stabilizer system and methods of using the same - An aircraft can include a tail section and a stabilizing system coupled to the tail section. The stabilizing system has a vertical stabilizer and at least one strake that cooperate to generate forces that compensate for a reaction torque generated by a main lifting rotor that produces lifting forces when the aircraft is in flight. Methods for improving aircraft performance include installing the at least one strake and retrofitting of a vertical stabilizer to increase thrust forces produced by a tail rotor. | 01-08-2009 |
20090014580 | VECTORED THRUSTER AUGMENTED AIRCRAFT - The Invention is a rotary-wing aircraft having at least two vectored thrusters that may be tilted from a horizontal to a vertical position and to positions intermediate between the horizontal and vertical positions. The two vectored thrusters are equipped with propellers having separately variable pitch. The two vectored thrusters also are equipped with vanes having selectable vane angles to direct separately the air flow from the two vectored thrusters. A control system detects the flight condition of the aircraft and selects vectored thruster control settings corresponding to the detected flight condition and consistent with predetermined control rules to provide lift, thrust, yaw moments and roll moments. | 01-15-2009 |
20090057480 | Helicopter Tail Assembly - A helicopter tail assembly includes a tail boom that extends along a tail axis, a tail fin mounted on one end of the tail boom, and a rudder mounted on the tail fin and pivotable relative to the tail fin about a pivot axis that is inclined with respect to the tail axis at an angle greater than 0 degrees and less than 90 degrees. | 03-05-2009 |
20090084891 | DE-ROTATION SYSTEM SUITABLE FOR USE WITH A SHAFT FAIRING SYSTEM - A de-rotation system includes a first ring gear defined about an axis of rotation, a second ring gear defined about the axis of rotation and a gear set in meshing engagement with the first ring gear and the second ring gear to control a position of a housing about the axis of rotation. | 04-02-2009 |
20090101753 | Device for compensation of the Tail rotor in a helicopter - According to the present invention, In case of tail rotor failure in a helicopter, pilot will activate Cockpit control unit which is installed in cockpit, wherein said unit contains activation switch and electronic circuits that automatically performs steps of: determining and releasing a predetermined pressurized gas from a capsule, wherein said capsule is located within the helicopter, and wherein said predetermined pressurized gas is based on a level of pressure in said capsule, and feedback received form yaw movement; and thereby compensating tail rotors torque and stabilizing said helicopter. | 04-23-2009 |
20090121075 | AIRCRAFT PROVIDED WITH A SILENT SHROUDED ROTOR - An aircraft has a streamlined structure ( | 05-14-2009 |
20090140095 | ELECTRIC POWERED ROTARY-WING AIRCRAFT - A rotary-wing aircraft with an electric motor mounted along an axis of rotation to drive a rotor system about the axis of rotation. | 06-04-2009 |
20100019079 | THRUST GENERATOR FOR A ROTARY WING AIRCRAFT - A thrust generator is provided. The thrust generator is configured to introduce a motive fluid along a Coanda profile and to entrain additional fluid to create a high velocity fluid flow, wherein the high velocity fluid flow is configured to generate thrust for counter-acting a torque generated by a rotating component. | 01-28-2010 |
20100025525 | TOY HELICOPTER - A toy helicopter, in accordance with the present disclosure, includes a body having a longitudinal length and a main rotor. There is an element movable along the longitudinal length. The element allows a user to selectively adjust the location of the center of gravity of a toy helicopter by moving the element along the longitudinal length, thereby changing the velocity of the helicopter. | 02-04-2010 |
20100044497 | Vertical take-off tilt rotor aircraft - A vertical take-off aircraft is disclosed. Looking at the aircraft it can be seen that the aircraft comprises a main power plant | 02-25-2010 |
20100123039 | Tail rotor system and method for controlling a tail rotor system - The present invention relates to a tail rotor system for an aircraft, in particular for a helicopter, with a multi-blade tail rotor with fixed blade angle of attack and to a method for controlling a tail rotor system for an aircraft, in particular for a helicopter. | 05-20-2010 |
20100264255 | Tilt rotor vertical take-off aircraft - J - An aircraft comprising a main propeller | 10-21-2010 |
20100270423 | PLANETARY DE-ROTATION SYSTEM FOR A SHAFT FAIRING SYSTEM - A de-rotation system includes a planetary gear set, and a fairing support structure mounted for rotation with a first ring gear. | 10-28-2010 |
20110121127 | POWER PLANT, A HELICOPTER INCLUDING SUCH A POWER PLANT, AND A METHOD IMPLEMENTED BY SAID POWER PLANT - The present invention relates to a power plant ( | 05-26-2011 |
20110147511 | ROTATING WING AIRCRAFT WITH TIP-DRIVEN ROTOR AND ROTOR-GUIDE RING - A helicopter includes a main rotor guided and protected in minor impacts by a guide-ring. In selected embodiments, the rotor is powered by an electric motor employing a magnetic field generator carried by the main rotor and stator coils installed on the guide-ring. The helicopter's main rotor thus effectively functions as the rotor of the electric power plant of the helicopter. In selected embodiments, the rotor's blades are arranged so as to create an opening in the center of the rotor, allowing pilot ejection or deployment of a parachute capable of safely lowering the helicopter in case of an emergency. | 06-23-2011 |
20120068007 | ROTARY WING AIRCRAFT PROVIDED WITH PROPULSION MEANS, AND A METHOD APPLIED BY SAID AIRCRAFT - An aircraft ( | 03-22-2012 |
20120104156 | USE OF AUXILIARY RUDDERS FOR YAW CONTROL AT LOW SPEED - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. | 05-03-2012 |
20120256041 | AIRCRAFT STABILIZER SYSTEM AND METHODS OF USING THE SAME - An aircraft can include a tail section and a stabilizing system coupled to the tail section. The stabilizing system has a vertical stabilizer and at least one strake that cooperate to generate forces that compensate for a reaction torque generated by a main lifting rotor that produces lifting forces when the aircraft is in flight. Methods for improving aircraft performance include installing the at least one strake and retrofitting of a vertical stabilizer to increase thrust forces produced by a tail rotor. | 10-11-2012 |
20120280079 | Airfoil Shaped Tail Boom - A system and method to control fuselage torque of an aircraft. The system includes a tail boom having a first surface that creates a high-pressure region in a downward rotorwash and a second surface that creates a low-pressure region in the downward rotorwash. The difference in pressure regions creates a lateral force that opposes the fuselage torque. | 11-08-2012 |
20120292433 | HELICOPTER TORQUE COUNTERACTION DEVICE - A torque resisting device for a helicopter, wherein the helicopter includes a body and a main rotor. The device includes a deflector secured to and movable relative to the body, wherein the body includes opposing lateral sides and the deflector is movable to a position to extend away from only one of the lateral sides of the opposing lateral sides. The deflector includes a dimension extending in a plane generally non-parallel to a plane of the main rotor. Further included is a method for counteracting a torque created by the rotation of a main rotor of a helicopter. | 11-22-2012 |
20120312915 | LOW SPEED AUTOGYRO YAW CONTROL APPARATUS AND METHOD - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion device, such as an air jet or a fan may be used. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. Apparatus for generating horizontal lift imbalance induced a tail boom positioned within the downwash of a rotor may also be used, including compressed air vents or lateral or trailing edge flaps. | 12-13-2012 |
20120312916 | Propulsive Anti-Torque Nozzle System with Rotating Thrust Director for a Rotorcraft - The system of the present application includes a duct for receiving airflow from within a duct portion of a tailboom. The airflow is a mixture of fan driven air and engine exhaust. The system includes a fixed nozzle assembly with an anti-torque nozzle, a pro-torque nozzle, and a thrust nozzle. A rotating thrust director is located upstream of the fixed nozzle assembly. The rotating thrust director located is configured to selectively redirect airflow into one or more of the anti-torque nozzle, the pro-torque nozzle and the thrust nozzle. | 12-13-2012 |
20130068877 | BOTTOM-ADJUSTABLE PROPELLER-TYPE FLYING OBJECT - An existing bottom-adjustable propeller-type flying object requires a device having a complex structure constructed through the combination of various components such as a servo, a control plate, and a hinge to control the rotor pitch at every moment and operate an adjustable blade for flight control. The bottom-adjustable propeller-type flying object of the disclosure includes a circular frame with a fixing plate and a protective plate installed at a lower portion of a shaft of a power propeller mounted to the central shaft, and an adjusting motor having an adjustable propeller. The flying object moves up or down by using force of the wind generated downward due to the rotation of the power propeller. The flying object makes a hovering flight, and leftward, rightward, forward, and backward flights by using the force of the wind generated due to the rotation of the adjustable propellers mounted on two adjusting motors. | 03-21-2013 |
20130168490 | Rotorcraft Counter-Torque Control Assembly and Method - There is provided a counter-torque control assembly for mounting to a tail boom of a rotorcraft where the rotorcraft has a single main rotor, no tail rotor, and no tail fin. The assembly has an air intake chamber with at least a first opening for receiving an air flow stream and a vane assembly housed within the air intake chamber. The vane assembly has at least two vane elements capable of counter-rotation in the air flow stream. The assembly further has one or more microjet propulsion devices coupled to a second end of the air intake chamber. The one or more microjet propulsion devices draw the air flow stream over the vane elements to generate a counter-torque force to counter a torque from the single main rotor. | 07-04-2013 |
20160046372 | Rocket Morphing Aerial Vehicle - A rocket morphing aerial vehicle has a first rocket configuration and a second aerial vehicle configuration. The rocket morphing aerial vehicle may be used to deploy an aerial vehicle at further distances faster. The rocket configuration may be used to get the aerial vehicle to its desired location, while the aerial vehicle is used for the desired task. The rocket morphing aerial vehicle may include a deceleration mechanism such that the speed of the rocket does not interfere with the deployment of the aerial vehicle. | 02-18-2016 |
20160167775 | HIGH-ALTITUDE DRONE | 06-16-2016 |
20160375982 | SYSTEM AND METHODS ASSOCIATED WITH A RIDEABLE MULTICOPTER - Embodiments described herein relate to multicopters with separate engines to power each rotor, wherein the multicopters also include with unique controls to guide the multicopter. | 12-29-2016 |
20180022450 | AVIATION DEVICE COMPRISING A BEARING STRUCTURE AND A ROTATING MEMBER EQUIPPED WITH FIXING MEANS WHICH MAKE IT POSSIBLE TO FIX AT LEAST ONE BLADE | 01-25-2018 |
244170210 | Auxiliary rotor | 43 |
20080237393 | Aircraft Having Helicopter Rotor and Front Mounted Propeller - An aircraft features a nose mounted propeller on a fuselage having a typical helicopter rotor assembly. By reducing the amount of forward thrust needed from the main rotor, the propeller allows greater forward speeds as the angle of attack on the rotor's blades can be kept low to avoid the stalling and violent vibration experienced by conventional helicopters at relatively high speeds. By reducing the maximum angle of attack experienced by the main rotor during its rotation during forward cruising from that of a conventional helicopter but still using the main rotor to generate lift, the addition of wings extending from both sides of the fuselage can be avoided. The aircraft may be flown in a forward direction in a generally horizontal orientation, as the nose does not have to be pitched downward to create thrust from the main rotor. | 10-02-2008 |
20090014581 | Counter-Torque Device for a Helicopter - A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a rotor axis, and rotor blades extending from the hub. The Rotor blades have a modulated angular distribution about the rotor axis. The stator includes a stator hub, and a plurality of stator vanes distributed around the stator hub. The stator vanes are angularly modulated around the stator hub. | 01-15-2009 |
20090121076 | HELICOPTER - A helicopter ( | 05-14-2009 |
20090159740 | Coaxial rotor aircraft - A dual, coaxial rotor helicopter is provided that is relatively easy to fly. Thrust is provided by two ducted fans that are mounted at the rear of the aircraft and spaced apart laterally. Differential thrust generated by the fans provides yaw control for the aircraft, and forward thrust is provided by the fans working in combination. The coaxial rotors are preferably utilized primarily for lift, and not for forward thrust, which simplifies the control requirements. The coaxial rotor with ducted fan configuration also results in lower vibratory loads being imposed on the helicopter, thereby increasing its speed capability. The fan ducts serve to protect the fans, augment the fan thrust at low airspeeds, increase the efficiency of the fans at cruise speeds, and provide horizontal and vertical stabilizing surfaces to ensure aircraft flight stability. | 06-25-2009 |
20090277991 | HELICOPTER HAVING MEANS FOR THE AERODYNAMIC SUPPORT OF THE TORQUE EQUALIZATION - A helicopter has at least one main rotor ( | 11-12-2009 |
20090283628 | DIRECTIONAL CONTROL ARRANGEMENT TO PROVIDE STABILIZING FEEDBACK TO A STRUCTURAL BENDING MODE - A control system and method of producing a stabilizing feedback includes generating a control output with a link in response to a deflection of a structure, the control output operable to at least partially resist the deflection. | 11-19-2009 |
20100032517 | Torque Counter-Action Device - A torque resisting device for a helicopter which comprises a body, a first rotor and a tail rotor wherein the device comprises a deflector secured to and moveable relative to the body, wherein the deflector is positioned between the main rotor and the tail rotor and wherein the deflector is positioned generally aligned with the body in a non-deployed position and a portion of the deflector is positioned spaced apart from the body in a deployed position. Additionally, a method to counteract torque in the operating of a helicopter. | 02-11-2010 |
20100038469 | Helicopter rotor - A rotor for a helicopter, the rotor having a drive shaft rotating about a first axis; a hub connected functionally to the drive shaft in angularly fixed manner with respect to the first axis and in rotary manner with respect to a second axis crosswise to the first axis; and two blades connected to the hub in angularly fixed manner with respect to the first and second axis and in rotary manner with respect to respective third axes; the rotor also having supporting means for supporting the blades with respect to the hub in rotary manner about the respective third axes; the supporting means having at least one supporting member made at least partly of elastomeric material and interposed between a first surface and a second surface integral with a respective blade and the hub respectively; and the supporting member deforming, in use, to permit rotation of the blade, with respect to the hub, about the respective third axis. (FIG. | 02-18-2010 |
20100044498 | VARIABLE SPEED TRANSMISSION FOR A ROTARY WING AIRCRAFT - A transmission gearbox for a rotary-wing aircraft includes a main gearbox and a variable speed gearbox in meshing engagement with the main rotor gearbox. The variable speed gearbox permits at least two different RPMs for the main rotor system without disengaging the engine(s) or changing engine RPMs. The variable speed gearbox includes a clutch, preferably a multi-plate clutch, and a freewheel unit for each engine. A gear path drives the main gearbox in a “high rotor speed mode” when the clutch is engaged to drive the main rotor system at high rotor rpm for hover flight profile. A reduced gear path drives the main gearbox in a “low rotor speed mode” when the clutch is disengaged and power is transferred through the freewheel unit, to drive the main rotor system at lower rotor rpm for high speed flight. The variable speed gearbox may be configured for a tail drive system that operates at a continuous speed, a tail drive system that changes speed with the main rotor shaft or for no tail drive system. | 02-25-2010 |
20100127114 | HELICOPTER - A helicopter capable of preventing an increase in size of an airframe and achieving high-speed flight is provided. Provided is an airframe for supporting a main rotor so as to be rotatable, a propeller having a plane of rotation intersecting a plane of rotation of the main rotor, a propeller supporting portion that supports the propeller so as to be movable between positions behind and at the side of the airframe, and a tail disposed on the airframe, having a surface intersecting the plane of rotation of the main rotor. | 05-27-2010 |
20100163668 | Helicopter Rotor - A rotor for a helicopter, having a drive shaft rotating about a first axis; a hub angularly integral with the drive shaft about the first axis; and at least two blades projecting from the hub, on the opposite side to the first axis, and extending along respective second axes crosswise to the first axis; each blade is movable with respect to the hub and the other blades about a respective fourth axis parallel to the first axis, about the respective second axis, and about a respective third axis crosswise to the first and respective second axis; the rotor also has a number of first dampers for damping vibration associated with at least oscillation of the relative blades about the respective fourth axes; the first dampers are connected to one another and each to a relative blade; and, in a radial direction with respect to the first axis, at least one first damper is located between the first axis and the fourth axis of the relative blade. | 07-01-2010 |
20100181416 | UNMANNED HELICOPTER - An airframe ( | 07-22-2010 |
20100258671 | Aircraft having helicopter rotor and front mounted propeller - An aircraft features a nose mounted propeller on a fuselage having a typical helicopter rotor assembly. By reducing the amount of forward thrust needed from the main rotor, the propeller allows greater forward speeds as the angle of attack on the rotor's blades can be kept low to avoid the stalling and violent vibration experienced by conventional helicopters at relatively high speeds. By greatly reducing the amount of thrust produced by the main rotor but still using it to generate lift, the addition of wings can be avoided. The aircraft can be flown in a forward direction in a generally horizontal orientation, as the nose does not have to be pitched downward to create thrust from the main rotor. | 10-14-2010 |
20110121128 | Helicopter Auxilary Anti-Torque System - A helicopter auxilary anti-torque system for efficiently supplying thrust and control at the tail of a helicopter during failure of the helicopter tail rotor. The helicopter auxilary anti-torque system generally includes a fluid thrust assembly selectively engageable onboard the helicopter, an auxiliary tail rotor selectively engageable onboard the helicopter, and at least one controller to operate the fluid thrust assembly and the auxiliary tail rotor to effect a controlled anti-torque force of the tail boom during failure of the conventional helicopter tail rotor. The fluid thrust assembly projects a non flammable fluid from the tail boom of the helicopter. The auxiliary tail rotor is collapsible within the tail boom of the helicopter when not in use. The fluid thrust assembly and the auxiliary tail rotor may be automatically activated in the case of the primary tail rotor failure, or activated by the pilot of the helicopter via one or more switches. | 05-26-2011 |
20110139924 | TAIL BOOM - A tail boom capable of creating propulsive force during forward flight to increase the forward speed is provided. A tail boom producing a force that cancels out a torque effect due to the Coanda effect by forcing airflow generated by a propeller disposed on an upstream side downward through a slit penetrating in the thickness direction and provided at a lower part of one side surface is configured such that the airflow generated by the propeller contributes to the propulsive force during forward flight. | 06-16-2011 |
20110253831 | Foldable rotor blade for toy helicopter - A toy helicopter includes a body, a rotor arrangement for generating a rotational power, and a foldable propeller blade including a bracket member coaxially mounted to the rotor arrangement and at least two blade leafs pivotally and symmetrically coupling with the bracket member in a horizontally movable manner to generate an evenly rotational motion thereof, so as to stably provide an upward force to lift up said body. When one of the blade leafs is pivotally folded by an external force to misalign the blade leafs with each other, the bracket member is kept rotating to generate a centrifugal force to essentially re-situate the blade leafs in line with each other so as to re-gain a control and balance of the body. | 10-20-2011 |
20120012693 | METHOD AND AN AIRCRAFT PROVIDED WITH A SWIVELING TAIL ROTOR - A method of piloting an aircraft ( | 01-19-2012 |
20120138731 | ROTORCRAFT STRUCTURAL ELEMENT FOR REDUCING AERODYNAMIC DRAG - A fairing ( | 06-07-2012 |
20120187238 | HELICOPTER WITH REMOTE CONTROL - Improvements in a helicopter with a remote control is presented the helicopter has a stacked main rotor to provide vertical lift and control. A plurality of outrigger rotors provides side-to-side stability as well as allowing the body of the helicopter to tip side-to- side. The helicopter further includes an angled tail rotor to provide angular tip to the helicopter as well as providing forward thrust. The remote control is configured as a single stick design. The single stick design allows a user to control the lift of the helicopter with a trigger control for the speed of the main rotor and thumb controlled joystick provides directional movement. The joystick can also provide a charging station for the helicopter where the batteries and the charging cable can be concealed completely within the controller. | 07-26-2012 |
20120248240 | VERTICAL TAKE-OFF AND VERTICAL LANDING GYROPLANE - A gyroplane comprises a fuselage | 10-04-2012 |
20120256042 | HELICOPTER WITH CYCLOIDAL ROTOR SYSTEM - The invention is related to a helicopter ( | 10-11-2012 |
20120298792 | DISMOUNTABLE HELICOPTER - An unmanned aerial vehicle helicopter including a dismountable tail section including a torque compensating rotor. Power transmission from the motor to the torque compensating rotor is accomplished by pulley-and-belt drive arrangements. | 11-29-2012 |
20120305699 | Front electric rotor helicopter - My invention is a helicopter having a front electric anti-torque rotor for the purpose of having a mechanically driven pusher propeller at the rear for increase forward speed. Speed has been a limiting factor in vertical flight. Various designs have been conceived by people around the world to make the helicopter go faster. My design is a high speed single rotor helicopter design that uses a gas-electric hybrid front electric anti-torque rotor system to allow for a mechanically driven pusher propeller at the rear. As the helicopter go forward, the front electric anti-torque gives control and the mechanically driven pusher propeller at the rear gives increase forward speed. The intent of the design is to make a high speed single rotor helicopter design. | 12-06-2012 |
20130087653 | AIRFOIL SHAPED TAIL BOOM - A tail boom adapted for counteracting a fuselage torque created by an engine carried by a fuselage of a rotary aircraft. The tail boom is positioned within the rotorwash from the rotary and includes a first side surface contoured to create a low-pressure region of an airfoil and a second opposing side surface contoured to create a high-pressure region of an airfoil. The pressure difference between the high-pressure region and the low-pressure region causes the tail boom to move towards the low-pressure region, resulting in a lateral force opposing the torque on the fuselage. | 04-11-2013 |
20130119185 | DRIVE SYSTEM FOR HELICOPTERS - The rotors of a helicopter are directly connected with electric high-torque motors, and are powered by the latter. Energy generation and rotor drive are separate from each other. The high-torque motor of the main rotor is pivoted to the cabin canopy, so that it can be tilted together with the main rotor. | 05-16-2013 |
20130119186 | TORQUE COMPENSATION FOR A HELICOPTER - The invention relates to compensation for the torque which is produced by the main rotor ( | 05-16-2013 |
20130134256 | ANTI-TORQUE DEVICE WITH LONGITUDINAL THRUST FOR A ROTORCRAFT - A tail assembly ( | 05-30-2013 |
20130175386 | HELICOPTER CONFIGURATION - A helicopter ( | 07-11-2013 |
20130228646 | RETRACTING TAILWHEEL ASSEMBLY AND FIN - A tailwheel assembly for an aircraft includes a ventral fin including a fixed airframe portion of the ventral fin and a moveable tailwheel portion of the ventral fin. A tailwheel strut extends through the ventral fin and includes a fixed first strut portion and an extendable second strut portion having the moveable tailwheel portion of the ventral fin secured thereto. A tailwheel is secured to the extendable second strut portion. A method of operating a tailwheel assembly for an aircraft includes extending an extendable portion of a tailwheel strut from an airframe of the aircraft. The tailwheel strut has a tailwheel secured thereto and is located at least partially in a ventral fin of the aircraft. A tailwheel portion of the ventral fin is moved away from a fixed airframe portion of the ventral fin via extension of the extendable portion of the tailwheel strut. | 09-05-2013 |
20130228647 | Rotary Wing Aircraft Propulsion System - A rotary wing aircraft propulsion system includes an engine, a heat exchanger cooling a fluid from the engine and a thermoelectric generator in thermal communication with the fluid to generate electrical power. The thermoelectric generator provides electrical power to at least one aircraft component. | 09-05-2013 |
20130327881 | HELICOPTER WITH A TRANSVERSE DUCT - A helicopter with a longitudinal axis and with a tail portion ( | 12-12-2013 |
20140008486 | ASYMMETRICAL SINGLE MAIN ROTOR UNMANNED AERIAL VEHICLE - A single engine rotary wing aircraft is provided including a fuselage having a longitudinal first axis. A main rotor assembly is mounted to the fuselage for rotation about a second axis, perpendicular to the first axis. A tailboom is connected to an empennage. The tailboom is mounted to an end of the fuselage such that the tailboom is laterally offset from the first axis in a first direction. The rotary wing aircraft also includes a propulsion system. The single engine of the propulsion system is laterally offset from the first axis in a second direction opposite the first direction. | 01-09-2014 |
20140197271 | HELICOPTER - A composite structure forming a load bearing composite shell for a helicopter, with a shell which defines the exterior of a fuselage and includes a central fuselage section and tail boom, a fuselage which is adapted house an engine or drive train, a layered composite crashworthy seat and support structure and a fastening and a method of fastening by providing an adhesive between two layers which is allowed to flow through opposing holes in the layers to provide a chemical and mechanical attachment between the layers. | 07-17-2014 |
20140217231 | ROTARY WING AIRCRAFT HAVING COLLOCATED EXHAUST DUCT AND PROPELLER SHAFT - An exhaust system for reducing infrared emissions of a rotary wing aircraft includes an exhaust duct having a fore end for connection with an aft turbine section of an engine of the rotary wing aircraft, the exhaust duct having an aft end having an exhaust opening to expel engine exhaust proximate to a tail fairing of the rotary wing aircraft; and a drive shaft collocated with the exhaust duct, the drive shaft configured to provide rotational force to an aft propeller of the rotary wing aircraft. | 08-07-2014 |
20140326826 | DUCTED ROTOR FOR AN AIRCRAFT AND A ROTORCRAFT - A rotorcraft ducted rotor comprising a rotary assembly arranged in a passage to rotate about an axis of symmetry (AX | 11-06-2014 |
20140353422 | Remotely-Controlled Emergency Aerial Vehicle - Devices, systems and methods for utilizing a remotely-controlled aerial vehicle for emergency situations are disclosed. In an aspect of the present disclosure, a remotely-controlled aerial vehicle consisting of a rotor with interchangeably attached blades, a camera, an antenna for transmitting data, and rescue equipment which may be used to assist an endangered person on location is disclosed. In another aspect, the aerial vehicle further comprises a light source to assist in the use of the device at night, a pressure gun to assist in the delivery of rope or other materials in mountain side situations, an explosive device dropping mechanism, and a cable hoist. | 12-04-2014 |
20140374534 | Rotorcraft Anti-torque Control System - According to one embodiment, a rotorcraft includes a main rotor system, an anti-torque rotor system, an anti-torque rudder system, and an anti-torque control system. The anti-torque rudder system includes at least one rudder surface operable to provide a second force on the body in the direction of rotation of the at least one main rotor blade. The anti-torque control system is operable to receive a request to change an amount of anti-torque force applied to the body, compare a rotorcraft performance parameter to a threshold value, instruct one of the anti-torque rotor system or the anti-torque rudder system to change the amount of the first force if the rotorcraft performance parameter is less than the threshold value, and, if the rotorcraft performance parameter is greater than the threshold value, instruct the other of the anti-torque rotor system or the anti-torque rudder system to change the amount of the second force. | 12-25-2014 |
20150034760 | AIRCRAFT TAIL ROTOR SYSTEM - An aircraft tail rotor system is provided and includes a rotating element, a translating element and a structure including a first bearing in series with a second bearing, the first bearing including a component rotatable with and movable within the rotating element in accordance with translational movement of the translating element. The structure is configured to selectively use the second bearing to prevent transmission of rotational energy from the rotating element to the translating element in an event of a seizing of the first bearing. | 02-05-2015 |
20160046371 | COAXIAL COUNTER-ROTATING ROTOR SYSTEM - A system and method to tilt coaxial counter-rotating rotor hub assemblies relative to a fuselage. The system includes a first rotor hub assembly and a second rotor hub assembly spaced apart from the first hub assembly and carried by the fuselage. The method includes pivotally attaching the first rotor hub assembly and the second rotor hub assembly to a pivot joint and thereafter tilting the first rotor hub assembly and the second rotor hub assembly about the pivot joint with a driver. | 02-18-2016 |
20160090176 | ROTORCRAFT HAVING A STABILIZER DEVICE - A rotorcraft having at least one stabilizer device of the tail plane and/or of the tail fin type. At least one stabilizer device is a variable wing area stabilizer device comprising an airfoil member provided with a stationary airfoil surface and a movable airfoil surface. A control system is connected to a mover system for moving the movable airfoil surface in translation between a refracted position for occupying when the rotorcraft has a forward speed less than a first speed threshold, and an extended position for occupying when the rotorcraft has a forward air speed greater than a second speed threshold greater than the first speed threshold. | 03-31-2016 |
20160129988 | AIRCRAFT - The invention relates to an aircraft with a thrust propeller ( | 05-12-2016 |
20160159476 | GUIDE VANES FOR A PUSHER PROPELLER FOR ROTARY WING AIRCRAFT - A propulsor system for a rotary winged aircraft includes a propeller including having a propeller hub rotatable about a propeller axis and a plurality of propeller blades secured to and extending radially outwardly from the propeller hub. The propeller is oriented on the rotary winged aircraft to provide forward thrust for the rotary winged aircraft when the propeller is rotated about the propeller hub. A plurality of guide vanes non rotatable about the propeller axis are positioned upstream of the plurality of propeller blades. The plurality of guide vanes are positioned to turn an airflow flowing into the plurality or propeller blades, thereby reducing an angle of attack of the plurality of propeller blades relative to the airflow. | 06-09-2016 |
20160251080 | TAIL ASSEMBLY FOR A ROTORCRAFT, ROTORCRAFT AND METHOD OF MANUFACTURE OF A STRENGTHENED TAIL ASSEMBLY | 09-01-2016 |