| 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 | MULTI-SERVICE COMMON AIRFRAME-BASED AIRCRAFT | EP96945928.0 | 1996-12-09 | EP0866764A1 | 1998-09-30 | BURNHAM, Robert, W.; FITZPATRICK, Michael, F.; MUILENBERG, Dennis, A.; SCHOEBELEN, Joseph, K.; TROLLEN, Laurence, B. |
| A modular approach to the manufacture of high performance military aircraft allows different aircraft to be manufactured at affordable cost and with high part number commonality. An aircraft so constructed includes a delta wing (4); a forebody section (28), including a cockpit (2), which is mounted to the front of the wing (4), and a propulsion system support frame (23) mounted beneath the forebody section (28) and the underside of the wing (4). The propulsion system (10) is supported within this frame. The aircraft can also include an aftbody section (20) mounted to the aft end of the wing (4), which includes a 2-D variable thrust vectoring nozzle (11) and a pair of canted vertical tails (6). The forebody section (28) includes a chin inlet (9) below the cockpit. The wing (4) is preferably constructed using thermoplastic welding. | ||||||
| 122 | Compact vertical take-off and landing aircraft | EP90305236.3 | 1990-05-15 | EP0418998A1 | 1991-03-27 | Hatanaka, Takefumi |
A vertical take-off and landing aircraft which can be of basically very simple construction and compact size includes an air flow chamber (20) and an impulsion device such as an engine-driven propeller (22) for driving a high-velocity air flow through the air flow chamber (20). The high-velocity air flow can be directed to flow across the upper surfaces of the aircraft wings (16), to thereby generate dynamic lift during take-off or landing operation, and can be directed to flow out from the rear of the aircraft fuselage (12) to produce propulsive force during normal forward flying operation. |
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| 123 | Spin-Landing Drone | US15670223 | 2017-08-07 | US20190039728A1 | 2019-02-07 | Donald Bolden Hutson; Charles Wheeler Sweet, III; Paul Ferrell |
| Various embodiments include a drone having a landing control device that is configured to rotate wings into an auto-rotation decent configuration causing the drone to enter a nose-down attitude and spin about a long axis of the drone, and to collectively control pivot angles of the wings to enables control of decent rate and lateral motion during an auto-rotation descent. The landing control device may be a landing carousel including a pivotal frame secured to a drone body and configured to rotate about a carousel axis extending laterally relative to a longitudinal axis of the body. The landing carousel may include a first wing motor configured to pivot a first wing about a wing pivot axis extending parallel to the carousel axis, and a second wing motor configured to pivot a second wing about the wing pivot axis independent of the pivot the first wing. | ||||||
| 124 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT | US16108405 | 2018-08-22 | US20180354614A1 | 2018-12-13 | Masayoshi TUNEKAWA; Tetsuya TAMURA; Masao HASEGAWA |
| A vertical take-off and landing aircraft according to an embodiment of the present disclosure includes: a pair of ducted fans; a fuselage that is disposed at a lower position than the ducted fans; a frame body that connects the fuselage and the ducted fans; and a stabilizer fin that is disposed at a position at which the stabilizer fin does not obstruct airflows from the ducted fans, which is a position that is lower than an airframe center of gravity and which is rearward of the fuselage. | ||||||
| 125 | ASSISTED TAKEOFF | US16106652 | 2018-08-21 | US20180348793A1 | 2018-12-06 | Jun SHI; Xu Yang PAN |
| A method of assisted takeoff of a movable object includes increasing output to an actuator that drives a propulsion unit of the movable object under a first feedback control scheme, determining whether the movable object has met a takeoff threshold, and controlling the output to the actuator using a second feedback control scheme different from the first feedback control scheme in response to the movable object having met the takeoff threshold. | ||||||
| 126 | ELECTRICALLY POWERED AERIAL VEHICLES AND FLIGHT CONTROL METHODS | US16027848 | 2018-07-05 | US20180312248A1 | 2018-11-01 | Markus Leng |
| An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control. | ||||||
| 127 | Universal multi-role aircraft protocol | US14843565 | 2015-09-02 | US10112625B2 | 2018-10-30 | Sydney Robert Curtis |
| The Curtis Protocol, an aircraft control interface, is provided. The Curtis Protocol standardizes the division and selection of aircraft flight regimes and flight modes within the selected flight regime. | ||||||
| 128 | CONTROL AND STABILIZATION OF A FLIGHT VEHICLE FROM A DETECTED PERTURBATION BY TILT AND ROTATION | US15935689 | 2018-03-26 | US20180284814A1 | 2018-10-04 | Thomas A. Youmans |
| A flight vehicle control and stabilization process detects and measures an orientation of a non-fixed portion relative to a fixed frame or portion of a flight vehicle, following a perturbation in the non-fixed portion from one or both of tilt and rotation thereof. A pilot or rider tilts or rotates the non-fixed portion, or both, to intentionally adjust the orientation and effect a change in the flight vehicle's direction. The flight vehicle control and stabilization process calculates a directional adjustment of the rest of the flight vehicle from this perturbation and induces the fixed portion to re-orient itself with the non-fixed portion to effect control and stability of the flight vehicle. The flight vehicle control and stabilization process also detects changes in speed and altitude, and includes stabilization components to adjust flight vehicle operation from unintentional payload movement on the non-fixed portion. | ||||||
| 129 | Modular and Morphable Air Vehicle | US15953421 | 2018-04-14 | US20180281944A1 | 2018-10-04 | John W. Piasecki; Frederick W. Piasecki; Brian Geiger; Douglas Johnson; David Pitcairn |
| A personal air vehicle may feature an air module that may be attached to a ground module. The air module may be equipped with exit vanes or vectored engine exhaust to provide redundant control effectors to the cyclic or collective pitch of at least one rotary wing under the control of a control system. | ||||||
| 130 | Heavy Lift airborne transport device | US14756861 | 2015-10-23 | US10071800B2 | 2018-09-11 | Jedidya L. Boros |
| The device is capable of transporting people and goods from one location to another: it includes a circular shaped body, a uniquely designed propeller mounted on the top of the body with propeller blades that produce a low pressure region above the device, the difference between the air pressure on the bottom and the top of the device's body provides the uplift force for holding the device in the air, capable of vertical takeoff and landing; on the surrounding wall, sideways and in back, service propellers are mounted in horizontal direction to help navigate the device; land and sea landing version of the device is disclosed as well; its bottom is extended in order to keep the doors above the water level during floating. | ||||||
| 131 | Aerial system utilizing a tethered uni-rotor network of satellite vehicles. | US15430475 | 2017-02-11 | US20180229838A1 | 2018-08-16 | Justin Selfridge |
| A tethered uni-rotor network of satellite vehicles, is a novel aerial system which combines the best features of both fixed-wing and rotorcraft design methodologies, while minimizing their respective deficiencies. It is made up of a central hub with multiple tethers, where each tether arm radiates outward and attaches to a satellite vehicle; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The entire system operates in a state of rotation, which is driven by the propulsion units on each satellite. As the system rotates, centrifugal forces pull the satellite vehicles outward, which maintain tension on the tether arms. As the satellite vehicles move through space, the airfoils generate lift which supports each satellite and a distributed portion of the weight of the central hub. | ||||||
| 132 | Plasma control and power system | US12983205 | 2010-12-31 | US10011344B1 | 2018-07-03 | Edmund J. Santavicca, Jr.; Srikanth Vasudevan; Frederick J. Lisy; Mike Ward |
| An improved high-voltage AC power supply energizes and regulates plasma actuators for aerodynamic flow control. Such plasma actuators are used, for example, on aerodynamic surfaces, wind turbine blades, and the like for vehicle control, drag or noise reduction, or efficient power generation. Various embodiments of the power supply are small, compact, lightweight, portable, modular, self-contained in its own housing, easily replaceable and swappable, autonomous, self-cooling, and/or gangable in series or parallel to provide any desired control authority over the selected surface. In some embodiments, the parameters for the plasma electronics can be manually selected and pre-programmed for a specific application, while in preferred embodiments, the plasma electronics can automatically identify the appropriate parameters and self-tune the performance of the plasma actuators. | ||||||
| 133 | Loop Yoke for Proprotor Systems | US15375356 | 2016-12-12 | US20180162518A1 | 2018-06-14 | Thomas Clement Parham, JR.; Jouyoung Jason Choi; Gary Miller; Frank Bradley Stamps; Richard Erler Rauber |
| A yoke for providing a centrifugal force retention load path between a proprotor blade and a hub of a soft-in-plane proprotor system operable for use on a tiltrotor aircraft. The yoke includes a continuous loop having a longitudinal axis and first and second longitudinal sections extending between inboard and outboard arcuate sections. A flapping bearing receiving region is disposed at least partially within the inboard arcuate section to an interior of the continuous loop. A centrifugal force bearing receiving region is disposed at least partially within the outboard arcuate section to the interior of the continuous loop. The continuous loop is formed from a composite material having a plurality of double bias material plies and a plurality of unidirectional material plies such that the number of unidirectional material plies is greater than the number of double bias material plies. | ||||||
| 134 | Vertical takeoff and landing (VTOL) air vehicle | US15638970 | 2017-06-30 | US09988147B2 | 2018-06-05 | Dana J. Taylor; Phillip T. Tokumaru; Bart Dean Hibbs; William Martin Parks; David Wayne Ganzer; Joseph Frederick King |
| A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing. | ||||||
| 135 | Control and stabilization of a flight vehicle from a detected perturbation by tilt and rotation | US15091566 | 2016-04-05 | US09946267B2 | 2018-04-17 | Thomas A. Youmans |
| A flight vehicle control and stabilization process detects and measures an orientation of a non-fixed portion relative to a fixed frame or portion of a flight vehicle, following a perturbation in the non-fixed portion from one or both of tilt and rotation thereof. A pilot or rider tilts or rotates the non-fixed portion, or both, to intentionally adjust the orientation and effect a change in the flight vehicle's direction. The flight vehicle control and stabilization process calculates a directional adjustment of the rest of the flight vehicle from this perturbation and induces the fixed portion to re-orient itself with the non-fixed portion to effect control and stability of the flight vehicle. The flight vehicle control and stabilization process also detects changes in speed and altitude, and includes stabilization components to adjust flight vehicle operation from unintentional payload movement on the non-fixed portion. | ||||||
| 136 | EXTERNAL LOAD MANAGEMENT FUNCTIONS FOR VERTICAL TAKE-OFF AND LANDING AIRCRAFT | US15566282 | 2016-04-01 | US20180099748A1 | 2018-04-12 | Jesse J. Lesperance; Thomas Zygmant |
| According to an aspect, a system in an aircraft includes a vehicle management system (VMS) and a load control system (LCS). The LCS includes an LCS processor operable to receive and transmit a plurality of data and load management commands to one or more of: the VMS and a load control interface. The LCS processor is further operable to interact with one or more of: the VMS, one or more LCS sensors, and a load capturing interface of the aircraft to execute the load management commands as a sequence of one or more load management subcommands. The load capturing interface is operable to capture and release an external load relative to the aircraft using a load capture device. The LCS processor is also operable to report a status of execution of the load management commands to the VMS and the load control interface. | ||||||
| 137 | Providing services using unmanned aerial vehicles | US15147762 | 2016-05-05 | US09849979B2 | 2017-12-26 | Eric Peeters; Eric Teller; William Graham Patrick |
| Embodiments described herein may help to provide support via a fleet of unmanned aerial vehicles (UAVs). An illustrative medical-support system may include multiple UAVs, which are configured to provide support for a number of different situations. Further, the medical-support system may be configured to: (a) identify a remote situation, (b) determine a target location corresponding to the situation, (c) select a UAV from the fleet of UAVs, where the selection of the UAV is based on a determination that the selected UAV is configured for the identified situation, and (d) cause the selected UAV to travel to the target location to provide support. | ||||||
| 138 | Vertical takeoff and landing (VTOL) aircraft and system | US15340585 | 2016-11-01 | US09840327B1 | 2017-12-12 | Roger S. Frank |
| A VTOL aircraft system includes a first unit having a cockpit, at least one propeller, at least two landing legs and at least two locking mechanisms. A second unit has a housing with a base portion, a first unit engaging portion, and at least two lock mechanism-engaging structure, each corresponding to one of the at least two locking mechanisms of the first unit. The housing of the second unit defines at least one interior cavity with at least one cargo area, a central passage providing access between the first and second unit, and a fuel cell configured around the central passage. | ||||||
| 139 | 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. | ||||||
| 140 | 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. | ||||||
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