公开(公告)号：US20240166336A1

公开(公告)日：2024-05-23

申请号：US18421169

申请日：2024-01-24

申请人： Kitty Hawk Corporation

发明人： Alexander David Selwa ,  Todd Reichert ,  Mark Johnson Cutler

IPC分类号： B64C13/04 ,  B64C27/08 ,  B64C27/20 ,  G05G9/047

CPC分类号： B64C13/0421 ,  B64C27/08 ,  B64C27/20 ,  G05G9/047

摘要： A forward velocity associated with an aircraft is received. The aircraft includes a multicopter with a plurality of rotors which rotate in a substantially horizontal plane. A pitch offset is determined based at least in part on the forward velocity, where the pitch offset changes monotonically with the forward velocity. A desired pitch is determined based at least in part on the pitch offset and a pitch angle specified via a hand control. A plurality of control signals for the plurality of rotors is determined based at least in part on the desired pitch.

公开(公告)号：US20240124129A1

公开(公告)日：2024-04-18

申请号：US18218573

申请日：2023-07-05

申请人： AVIAN AEROSPACE LLC

发明人： Clayton Prescan SMELTZ ,  Buddy Prescan SMELTZ

IPC分类号： B64C13/04

CPC分类号： B64C13/0421 ,  B64C13/044

摘要： Provided is an aircraft hand controls. The aircraft hand controls may comprise a set of left and right brake hand controls and a rudder hand control. The set of left and right brake hand controls may be operatively connected to the rudder pedals or toe brakes. The set of left and right brake hand controls may also comprise a hydraulic brake adaptation for plumbing hydraulic pressure into the aircraft's hydraulic brake system. The aircraft hand controls may comprise one or more push-to-talk buttons.

公开(公告)号：US20240025534A1

公开(公告)日：2024-01-25

申请号：US18265163

申请日：2021-12-02

申请人： Safran Electronics & Defense

发明人： Badr MANSOURI ,  Hicham JANATI IDRISSI ,  Pascal COPPÉE

IPC分类号： B64C13/04 ,  G05G9/047

CPC分类号： B64C13/0421 ,  G05G9/047 ,  G05G2009/04766

摘要： A method for controlling an engine, a device for controlling an engine and an aircraft, the method comprising the steps of determining a first intensity Kp, representing a stiffness, according to a physical stiffness Kss of the mechanical connection and a stiffness setpoint Kpspec to be rendered on the control column, a second intensity Kv, representing a damping, according to a physical damping fss between the control column and the engine and a damping setpoint Kvspec to be rendered on the control column, and a third intensity Ka, representing an inertia, according to a physical inertia Jss of the control column and an inertia setpoint Kaspec to be rendered on the control column.

公开(公告)号：US20240010331A1

公开(公告)日：2024-01-11

申请号：US18022500

申请日：2021-08-23

申请人： HILL GROUP TECHNOLOGIES LIMITED

发明人： Jason HILL

IPC分类号： B64C27/56 ,  B64C13/04 ,  B64D11/06

CPC分类号： B64C27/56 ,  B64C13/0421 ,  B64D11/0646 ,  B64D11/0689

摘要： Disclosed is a collective control arrangement for a helicopter having a plurality of rotor blades, the collective control arrangement comprising: an armrest for a pilots seat, the armrest comprising an elongate channel; and a collective handle comprising: a first end slidably disposed in the elongate channel for coupling to one or more helicopter actuators that control collective pitch of the plurality of rotor blades; and a second end for gripping by a pilot. Advantageously the armrest comprises an elbow support portion configured to be located backwards of the hollow when the armrest is installed in the helicopter.

公开(公告)号：US11787527B2

公开(公告)日：2023-10-17

申请号：US17511349

申请日：2021-10-26

申请人： Lockheed Martin Corporation

发明人： Michael A Connor ,  Igor Cherepinsky ,  Christopher J. Marini ,  Nicholas Visinski ,  Ashley M. Currivan

IPC分类号： B64C13/50 ,  B64C13/04 ,  B64C13/34 ,  F16D28/00 ,  F16D48/06 ,  F16D27/00

CPC分类号： B64C13/50 ,  B64C13/0421 ,  B64C13/34 ,  F16D27/00 ,  F16D28/00 ,  F16D48/06 ,  F16D2500/1023

摘要： An actuation system for an aircraft can include an actuator and a plurality of clutches connected to and structured to be moved by the actuator. The actuation system can include a plurality of control levers connected to the plurality of clutches and structured to be moved by the plurality of clutches when the plurality of clutches are moved by the actuator. The actuation system can include a processor connected to the actuator and to the plurality of clutches. The processor can identify one or more clutches connected to one or more control levers of the plurality of control levers for controlling an operation of the aircraft, and cause the one or more clutches connected to the one or more control levers to be in an engaged stat. The processor can activate the actuator to cause movement of the one or more control levers via the one or more clutches.

公开(公告)号：US11724794B2

公开(公告)日：2023-08-15

申请号：US17205198

申请日：2021-03-18

申请人： Ratier-Figeac SAS

发明人： Bruno Seminel ,  Arnaud Delpeuch ,  Cedric Antraygue

IPC分类号： B64C13/04 ,  G01L5/00 ,  B64C13/50

CPC分类号： B64C13/0421 ,  B64C13/503 ,  B64C13/507 ,  G01L5/0061

摘要： An aircraft inceptor system includes an inceptor member arranged to be operated by a user to cause a corresponding movement of a moveable aircraft surface. The system also includes means for detecting the operation of the inceptor member by the user and for providing a movement signal, associated with the detected operation, to a flight control computer, the flight control computer providing a control signal to an actuator to move the aircraft surface according to the movement signal. The means for detecting the operation of the inceptor member by the user comprises a force sensor configured to sense the force applied by the user to the inceptor member, the movement signal being derived based on the sensed force.

公开(公告)号：US11702191B1

公开(公告)日：2023-07-18

申请号：US18147640

申请日：2022-12-28

申请人： Archer Aviation, Inc.

发明人： Nathan Thomas Depenbusch ,  Jeffery Scott Greenwood

IPC分类号： B64C13/00 ,  B64C13/04 ,  G05D1/08 ,  B64C13/50

CPC分类号： B64C13/0421 ,  B64C13/503 ,  G05D1/0858

摘要： Disclosed are systems and methods for controlling an electric vertical take-off and landing (eVTOL) aircraft. In one embodiment, a system comprises a processor, a first inceptor, communicatively coupled to the processor, the first inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, and a second inceptor, communicatively coupled to the processor, the second inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, wherein the processor is configured to control a heading of an aircraft using a signal received from the second inceptor corresponding to lateral linear movement of the second inceptor. Some embodiments may additionally include at least one sensor and a thumb stick for each inceptor.

公开(公告)号：US20190061917A1

公开(公告)日：2019-02-28

申请号：US16010336

申请日：2018-06-15

申请人： SUBARU CORPORATION

发明人： Takuma MIZUTANI

IPC分类号： B64C13/10 ,  B64D43/00

CPC分类号： B64C13/10 ,  B64C13/0421 ,  B64C13/044 ,  B64D11/0689 ,  B64D43/00 ,  B64D45/00

摘要： According to one implementation, an information transmission system includes: a transmission information determination part, an output device; and at least one vibrating device. The transmission information determination part is adapted to determine transmission information to a pilot of an aircraft. The output device is adapted to transmit the transmission information to the pilot by a visual representation, voice, sound or a light. The at least one vibrating device is adapted to propagate a vibration to the pilot when the transmission information is transmitted to the pilot.

公开(公告)号：US20180346110A1

公开(公告)日：2018-12-06

申请号：US16109170

申请日：2018-08-22

申请人： Merlin Technology Inc.

发明人： John E. Mercer ,  Marc Feifel ,  Mark Marvin ,  Nicholas Albion

IPC分类号： B64C27/68 ,  F16F15/121 ,  B64C13/18 ,  B64C27/58 ,  B64C27/57 ,  B64C13/04 ,  B64C27/59 ,  B64C13/30

CPC分类号： B64C27/58 ,  B64C13/0421 ,  B64C13/18 ,  B64C13/343 ,  B64C27/57 ,  F16F15/121 ,  Y02T50/44

摘要： An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.

公开(公告)号：US20180017987A1

公开(公告)日：2018-01-18

申请号：US15209186

申请日：2016-07-13

申请人： Hamilton Sundstrand Corporation

发明人： Cory M. Crandall-Seibert ,  Jeffrey Paul Jacobs

IPC分类号： G05G5/03 ,  B64C13/14 ,  B64C13/26 ,  B64C13/50

CPC分类号： G05G5/06 ,  B64C13/04 ,  B64C13/0421 ,  B64C13/10 ,  B64C13/14 ,  B64C13/26 ,  B64C13/50 ,  G05G1/04 ,  G05G5/005 ,  G05G5/18 ,  G05G2505/00

摘要： A detent alignment mechanism assembly is provided and includes a shaft, a lock mechanism configured to selectively occupy an unlocked position at which the shaft is movable and a locked position at which the shaft is immovable, a detent mechanism coupled to the shaft and formed to define detent positions for the shaft to assume and move between and a detent alignment mechanism configured to provide to an operator of the shaft feedback and assistance corresponding to assumptions of the detent positions by the shaft during movements thereof by the operator.