| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | UNMANNED AERIAL SYSTEM | US15595758 | 2017-05-15 | US20170247110A1 | 2017-08-31 | Dana Robert CHAPPELL |
| Embodiments of unmanned aerial systems are disclosed, which may comprise: a frame; a landing member attached to the frame; a propulsion system support member attached to the frame; a propulsion system attached to the propulsion system support member; a shroud having a paraboloid surface attached to the frame; a external equipment carrier attached to the frame; a sensor system; a sealed equipment container attached to the frame and located beneath the shroud; an electronic control system within the sealed equipment container and configured to control the propulsion system and the sensor system; and a power source within the sealed equipment container and configured to power the electronic control system. | ||||||
| 122 | INDEPENDENT CONTROL FOR UPPER AND LOWER ROTOR OF A ROTARY WING AIRCRAFT | US15504525 | 2015-09-30 | US20170233067A1 | 2017-08-17 | Ezra Eller; Matthew A. White; David H. Hunter |
| An aircraft is provide including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer. | ||||||
| 123 | Modular and Morphable Air Vehicle | US15476612 | 2017-03-31 | US20170210469A1 | 2017-07-27 | John W. Piasecki; Frederick W. Piasecki; Brian Geiger; Douglas Johnson; David Pitcairn |
| An air module may be attached to a ground module. The air module may be equipped with a center of gravity effector to change the relative locations and hence the center of gravity of the air and ground modules when the modules are attached. The center of gravity effector may be active or passive or a combination of active and passive. The center of gravity effector may be combined with a center of lift effector to change the relative locations of the center of gravity and center of lift. | ||||||
| 124 | Power safety instrument system | US15168356 | 2016-05-31 | US09663243B2 | 2017-05-30 | James M. McCollough; Erik Oltheten; Nicholas Lappos |
| A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available. | ||||||
| 125 | Rotor-mast-tilting apparatus and method for lower flapping loads | US14544796 | 2015-02-18 | US09611036B1 | 2017-04-04 | Jehan Zeb Khan |
| A method and apparatus for reducing flapping loads imposed on a rotor are disclosed. The method may include flying a rotorcraft comprising an airframe, a rotor, a mast extending to connect the rotor to the airframe, a tilt mechanism, at least one sensor, and a computer system. The computer system may obtain in real time, from the at least one sensor, data characterizing at least one flapping load experienced by the rotor during the flying. Using the data, the computer system may issue at least one command to the tilt mechanism. In response to the command, the tilt mechanism may reorient the mast with respect to the airframe. This reorienting may lower the flapping load experienced by the rotor. | ||||||
| 126 | Modular and morphable air vehicle | US15205162 | 2016-07-08 | US09610817B1 | 2017-04-04 | John W. Piasecki; Frederick W. Piasecki; Brian Geiger; Douglas Johnson; David Pitcairn |
| An unmanned air module includes one or more rotors, engines, a transmission and avionics. Any of several different ground modules may be attached to the air module. The air module may fly with and without the ground module attached. The ground module may be manned. The air module may have two rotors, which may be ducted fans. The air module may include a parachute, an airbag and landing gear. | ||||||
| 127 | Propeller/rotor control apparatus and method | US14242932 | 2014-04-02 | US09555881B2 | 2017-01-31 | Richard L. Kulesha |
| An apparatus for controlling a rotor of a rotary wing aircraft, including a stationary frame, a rotary propulsion shaft extending through the frame, the propulsion shaft having a first shaft portion and a second shaft portion coupled to the first shaft portion at a joint, the first shaft portion being configured to be coupled to a drive unit and the second shaft portion being pivotable relative to a centerline of the first shaft portion in two degrees of freedom about the joint, and at least one actuator coupled to the stationary frame at one end and connected to the second shaft portion at the other end so that the second shaft portion rotates relative to the at least one actuator, the at least one actuator being configured to pivot the second shaft portion in the two degrees of freedom. | ||||||
| 128 | System, a method and a computer program product for maneuvering of an air vehicle | US14415433 | 2013-09-12 | US09540100B2 | 2017-01-10 | Guy Dekel; Lior Zivan; Yoav Efraty; Amit Wolff; Avner Volovick |
| A control system configured to control an acceleration of an air vehicle which comprises a tiltable propulsion unit that is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle, the control system comprising: (a) an input interface for receiving information indicative of a monitored airspeed of the air vehicle; and (b) a control unit, configured to issue controlling commands to a controller of the tiltable propulsion unit for controlling the acceleration of the air vehicle. | ||||||
| 129 | MULTICOPTERS WITH VARIABLE FLIGHT CHARACTERISTICS | US15112386 | 2015-01-20 | US20160340028A1 | 2016-11-24 | Suvro Datta |
| An aircraft (40a) is provided that includes a plurality of arms (41, 42, 43, 44) with selected arms having the ability to either adjust their length, have arm segments operative to move about an articulated joint in two or three dimensions, or have one arm operative to adjust an angle between the one arm and another arm, or any combination of the foregoing. Thrust generators are repositionably mounted on selected arms, and a control system enables automated, on-board, or remote control of the thrust generators, repositioning of the thrust generators on the arms, adjustment in the length of the selected arms, the movement of selected arms about the articulated joints, and adjustment of the angle between two or more arms, all while maintaining directional control of the aircraft in flight or on the ground. The aircraft has operational capabilities that exceed existing designs and facilitates manned and unmanned delivery of cargo and transportation of passengers. | ||||||
| 130 | Aircraft With A Plurality Of Engines Driving A Common Driveshaft | US15204547 | 2016-07-07 | US20160311530A1 | 2016-10-27 | Frick A. Smith |
| An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | ||||||
| 131 | Transmission mechanism for remote-controlled model stimulated helicopter | US13740247 | 2013-01-13 | US09434472B2 | 2016-09-06 | Anping Shen |
| A transmission mechanism for a remote-controlled model simulation helicopter includes a body frame which is orderly provided with a main rotor holder, a main rotor shaft, and a main reduction gear provided with a plurality of washout holes which are evenly distributed about an axis thereof. The body frame is provided with a swashplate module and a servo arrangement at a middle portion thereof. Since the main reduction gear is provided with washout holes and the introduction of internally installed swashplate module together with taking advantage of self structural features of the body frame, it enables the elimination of the commonly used swashplate guide board. The servo devices are provided in a same plane within the body frame and provide a triangular configuration, so that the structure is reasonable and the transmittance of motion is stable. | ||||||
| 132 | VEHICLE CONFIGURATION WITH MOTORS THAT ROTATE BETWEEN A LIFTING POSITION AND A THRUSTING POSITION | US14626357 | 2015-02-19 | US20160244157A1 | 2016-08-25 | Ricky Dean Welsh |
| This disclosure describes a configuration of an unmanned aerial vehicle (“UAV”) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (also known as an octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pivot assembly that may rotate about an axis from a lifting position to a thrusting position. The pivot assembly may include two or more offset motors that generate a differential force that will cause the pivot assembly to rotate between the lifting position and the thrusting position without the need for any additional motors or gears. | ||||||
| 133 | Amphibious Flying Car | US15026103 | 2014-08-04 | US20160243910A1 | 2016-08-25 | Xinru HU |
| The present invention provides an amphibious flying car, comprising: a casing, a chassis, a ship bottom body, a vehicle wheel, a drive system and an operating system; an upper airfoil and a rotor wing which are arranged on the top of the casing, are fixed on a bearing carrier located at the orthocenter of the fuselage; a strake wing is provided at the position where the casing, the chassis and the ship bottom body are combined; the horizontal wing comprises a stabilizing plane and an elevator, which are respectively located at the front end and the rear end of the fuselage; the vertical twin fins are arranged at both sides of the rear end of the fuselage, and its root segments are fixedly connected to the strake wing. | ||||||
| 134 | Power safety instrument system | US14715236 | 2015-05-18 | US09352849B2 | 2016-05-31 | James M. McCollough; Erik Oltheten; Nicholas Lappos |
| A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available. | ||||||
| 135 | AIRCRAFT | US14896008 | 2015-03-25 | US20160129988A1 | 2016-05-12 | Gerhard T. MEIER; Otmar BIRKNER |
| The invention relates to an aircraft with a thrust propeller (18), a tail unit (20) and a connection (22) by means of which the tail unit (20) is fastened.According to the invention, it is provided that the connection (22) has a sound-absorbing structure (24). | ||||||
| 136 | Controlling Rotary Wing Aircraft | US14829866 | 2015-08-19 | US20160059958A1 | 2016-03-03 | Vladimir Kvitnevskiy |
| A rotary wing aircraft can include a central body and at least three rotors, each rotor connected to the central body by a swashplate. A system for controlling the flight of an aircraft with a plurality of rotors can include: an electronic control system programmed to calculate a pitch for blades of each rotor of the plurality of rotors based on an input indicating a desired motion of the aircraft; and a plurality of swashplates, each swashplate associated with a unique rotor of the plurality of rotors, each swash plate in electronic communication with the electronic control system and operable to control the pitch for blades of the associated unique rotor in response to signals from the electronic control system. | ||||||
| 137 | Hybrid electric power helicopter | US13916283 | 2013-06-12 | US09248908B1 | 2016-02-02 | Leo J. Luyks |
| A helicopter has a propulsion system that includes a diesel engine driven electric generator, battery storage, power inverters for converting AC current to DC current and converting DC current to AC current, and an electric motor powered main rotor and an electric motor powered tail rotor. The propulsion system is integrated with electric controls of the main rotor electric motor and the tail rotor electric motor to provide additional system efficiencies. The design of the helicopter allows a single engine helicopter to be just as safe as a twin engine design helicopter while consuming less fuel. The helicopter design also includes a main rotor tilt system which tilts the rotation axis of the main rotor forward during high-speed flight to improve the aerodynamic efficiency of the helicopter airframe and rotary wing. | ||||||
| 138 | ROTARY PYLON CONVERSION ACTUATOR FOR TILTROTOR AIRCRAFT | US14712218 | 2015-05-14 | US20150360774A1 | 2015-12-17 | Charles Eric Covington; Eric S. Olson; David R. Bockmiller; Carlos A. Fenny |
| A tiltrotor aircraft can include a pylon rotatable about a conversion axis. A first differential planetary assembly can include a first housing; a first ring gear; a first differential planetary gear having a first output portion; and a first differential sun gear. A second differential planetary assembly can include a second housing; a second ring gear; a second differential planetary gear having a second output portion; and a second differential sun gear. The first output portion is coupled to the second housing such that the second housing rotates at a first output speed. Further, the second output portion is coupled to the shaft, the shaft being coupled to the pylon such that rotation of the shaft rotates the pylon. | ||||||
| 139 | SYSTEM, APPARATUS AND METHOD FOR LONG ENDURANCE VERTICAL TAKEOFF AND LANDING VEHICLE | US14507198 | 2014-10-06 | US20150336666A1 | 2015-11-26 | JAMES DONALD PADUANO; PAUL NILS DAHLSTRAND; JOHN BROOKE WISSLER; ADAM WOODWORTH |
| A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends. | ||||||
| 140 | Direct orientation vector rotor | US13715006 | 2012-12-14 | US09193452B2 | 2015-11-24 | Raymond George Carreker |
| A direct orientation vector rotor (DOVER) for use on rotary wing aircraft includes a gear set for multidirectional rotor orientation based on the spherical coordinate system; an inclination mechanism, wherein the rotor is moved from the 0° horizontal position to an inclined position; a rotational turret, wherein the rotor is moved along the azimuth and wherein the inclination mechanism is housed; and a motion-adapted gear lubrication housing. | ||||||
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