公开(公告)号：EP4357242A1

公开(公告)日：2024-04-24

申请号：EP23204074.1

申请日：2023-10-17

申请人： Lockheed Martin Corporation

发明人： Luszcz, Matthew

IPC分类号： B64C13/04 ,  B64C27/56

CPC分类号： B64C13/0421 ,  B64C13/507 ,  B64C27/56 ,  B64C13/04 ,  B64C13/503

摘要： Systems and methods for providing tactile feedback via an inceptor. A control system for an aircraft includes an inceptor and a controller. The inceptor includes a grip portion moveable between a plurality of positions and one or more motors to apply a variable force to the grip portion. The controller is coupled to the one or more motors. The controller includes an electronic processor and a memory. The controller is configured to operate in a first operating mode, select a first tactile feedback profile associated with the first operating mode, and control the one or more motors based on the first tactile feedback profile. The controller is further configured to detect a transition from the first operating mode to a second operating mode, select a second tactile feedback profile associated with the second operating mode, and control the one or more motors based on the second tactile feedback profile.

公开(公告)号：EP3213990B1

公开(公告)日：2018-12-05

申请号：EP17159073.0

申请日：2017-03-03

申请人： Sikorsky Aircraft Corporation

发明人： Baran, Michael Paul ,  Cherepinsky, Igor

IPC分类号： B64C13/22 ,  B64C13/50 ,  B64C27/56 ,  B64C27/68

CPC分类号： B64C13/503 ,  B64C13/04 ,  B64C13/22 ,  B64C27/56 ,  B64C27/68 ,  B64F5/00

摘要： A method of retrofitting a mechanically controlled aircraft with a fly-by-wire system includes removing a plurality of mechanical links between a plurality of mechanical pilot inputs and a plurality of actuators operable to drive flight surfaces. A plurality of vehicle management computers is installed in the aircraft. Electromechanical actuators are coupled between the vehicle management computers and the actuators, where each of the electromechanical actuators is operable to receive commands from the vehicle management computers and output a mechanical force to an input linkage of one of the actuators. Electromechanical pilot input modules are coupled to the mechanical pilot inputs. Each of the electromechanical pilot input modules is operable to convert a pilot-driven input force of an instance of the mechanical pilot inputs into an electronic signal indicative of the pilot-driven input force. At least one high performance computer is coupled to at least one of the vehicle management computers. The high performance computer is configured to execute one or more high level intelligence algorithms to selectively operate the aircraft autonomously.

公开(公告)号：EP2674829B1

公开(公告)日：2018-06-13

申请号：EP12194483.9

申请日：2012-11-27

申请人： Embraer, S.A.

发明人： Rey, Hans Jorg ,  Castro Paiva, Luiz Fernando Silva de ,  Gueiros, Celso Aparecido Cruz ,  Cerqueira Lario, Rogério de ,  Castanha, Bruno Kimura

IPC分类号： G05G1/06 ,  G05G1/58 ,  B64C13/04 ,  G05G9/047

CPC分类号： G05G1/06 ,  B64C13/04 ,  G05G1/58 ,  G05G9/047 ,  G05G2009/04774 ,  Y10T74/20876

摘要： Sidestick controller grips are provided with a base, an elongate column grip extending upwardly from the base, a head at an upper end portion of the grip column, and a thumb rest surface extending laterally and upwardly relative to the column grip. The thumb rest surface may be supported by a concave outwardly extending support wall which joins the thumbrest surface at a generally serpentine edge which may extend generally outwardly convexly from a lower region thereof at the column grip to a convex apex region, and then extends from the apex region generally upwardly and concavely to an upper region thereof at the head. The thumbrest surface may be concave to facilitate comfort. The head of the sidestick controller grip may include a split face surface defining inboard and outboard face surfaces disposed laterally adjacent to one another. The inboard face surface may be disposed at an elevation that is lower than the outboard face surface with inboard and outboard pushbuttons projecting outwardly therefrom, respectively.

公开(公告)号：EP3308233A1

公开(公告)日：2018-04-18

申请号：EP16807973.9

申请日：2016-05-03

申请人： Intel Corporation

发明人： EKANDEM, Joshua ,  ANDERSON, Glen J. ,  DURHAM, Lenitra M. ,  BECKWITH, Richard T. ,  RAFFA, Giuseppe ,  SHERMAN, Jamie ,  YUEN, Kathy

IPC分类号： G05D1/00 ,  G06F3/01 ,  G05D1/02

CPC分类号： G06F3/017 ,  B64C13/04 ,  B64C13/24 ,  B64C39/024 ,  B64C2201/146 ,  G05D1/0016 ,  G05D1/0033 ,  G05D1/101 ,  G06F1/163 ,  G06F1/1694 ,  G06K9/00355 ,  G06K9/0063 ,  G08C17/02

摘要： In embodiments, apparatuses, methods and storage media (transitory and non-transitory) are described that receive sensor data from one or more sensor devices that depict a user gesture in three dimensional space, determine a flight path based at least in part on the sensor data, and store the flight path in memory for use to control operation of a drone. Other embodiments may be described and/or claimed.

公开(公告)号：EP3301019A1

公开(公告)日：2018-04-04

申请号：EP17191029.2

申请日：2017-09-14

申请人： Airbus Helicopters

发明人： HONNORAT, Olivier ,  NEVERS, Romain ,  KOVEL, Romain

IPC分类号： B64C13/50 ,  B64C27/56

CPC分类号： B64C13/46 ,  B64C13/04 ,  B64C13/50 ,  B64C27/56 ,  G05B19/402 ,  G05B2219/34013 ,  H02P21/13 ,  H02P21/141 ,  H02P21/18 ,  H02P21/20 ,  H02P23/14

摘要： La présente invention concerne un dispositif de commande (10) d'un aéronef (1), ce dispositif de commande (10) comportant au moins un "vérin de trim" (2) motorisé à ancrage de type actif, le vérin de trim (2) comportant au moins un moteur électrique, au moins un circuit électronique de puissance pour alimenter en énergie électrique le (ou les) moteur(s) électrique(s) (3, 3') et des moyens de réduction de vitesse permettant d'entraîner en rotation un arbre de sortie du vérin de trim (2). Ce dispositif de commande (10) met en oeuvre trois boucles d'asservissement distinctes et imbriquées les unes dans les autres, ces trois boucles d'asservissement étant formées par une boucle d'asservissement en courant électrique, une boucle d'asservissement en vitesse et une boucle d'asservissement en effort.

摘要翻译： 本发明涉及一种用于飞机（1）的控制装置（10），该控制装置（10）包括至少一个具有主动锚定装置的主动马达型“修剪器”（2） 2）包括至少一个电动机，至少一个用于向电动机（3,3'）供应电能的电子电源电路以及用于 旋转配平顶杆（2）的输出轴。 该控制装置（10）实现三个彼此互锁的单独的伺服控制回路，这三个控制回路由电流控制回路，速度控制回路和 努力的奴役循环。

公开(公告)号：EP3290868A1

公开(公告)日：2018-03-07

申请号：EP17177594.3

申请日：2017-06-23

申请人： The Boeing Company

发明人： SCHWARTZ, Samantha ,  REID, Katie M.

IPC分类号： G01C23/00 ,  G08G5/00 ,  G08G5/06

CPC分类号： B64D43/00 ,  B64C13/04 ,  B64D45/0005 ,  G01C23/00 ,  G08G5/0021 ,  G08G5/0065

摘要： A yaw feedback system for use by an aircraft is provided. The yaw feedback system includes a processor, a runway centerline indicator, and a yaw feedback indicator. The processor is configured to determine a yaw difference between a current track of the aircraft and a runway centerline. The runway centerline indicator is configured to virtually extend a runway visual range (RVR) for a pilot of the aircraft. The yaw feedback indicator is coupled to the processor and configured to prompt the pilot for a yaw input to compensate for the yaw difference.

摘要翻译： 提供了由飞机使用的偏航反馈系统。 偏航反馈系统包括处理器，跑道中心线指示器和偏航反馈指示器。 处理器被配置为确定飞行器的当前轨迹和跑道中心线之间的偏航差异。 跑道中心线指示器被配置为虚拟地延伸飞机的飞行员的跑道可视范围（RVR）。 偏航反馈指示器耦合到处理器并且被配置成提示驾驶员进行偏航输入以补偿偏航差异。

公开(公告)号：EP3251946A1

公开(公告)日：2017-12-06

申请号：EP17170302.8

申请日：2017-05-09

申请人： Honeywell International Inc.

发明人： WILKENS, Dean

IPC分类号： B64C13/24 ,  B64C13/34 ,  F16H49/00

CPC分类号： F16H49/001 ,  B64C13/04 ,  B64C13/18 ,  B64C13/24 ,  B64C13/28 ,  B64C13/34 ,  B64C27/605

摘要： An automatic actuator system is provided. The automatic actuator system includes an input linkage that receives an input and an output linkage adapted to control a flight surface actuator. The automatic actuator system includes a first strain wave gear having a first circular spline coupled to the input linkage and a first flex spline rotatably coupled to the first circular spline. The automatic actuator system includes a second strain wave gear having a second circular spline coupled to the first flex spline. The second strain wave gear includes a second flex spline, and the second flex spline is coupled to the output linkage such that at least a portion of the input from the input linkage is transferred to the output linkage via the first strain wave gear and the second strain wave gear.

摘要翻译： 提供自动致动器系统。 该自动致动器系统包括输入联动装置，该输入联动装置接收适于控制飞行表面致动器的输入和输出联动装置。 自动致动器系统包括第一应变波动齿轮，第一应变波动齿轮具有耦合到输入连杆的第一圆形花键和可旋转地耦合到第一圆形花键的第一柔性花键。 该自动致动器系统包括第二应变波齿轮，该第二应变波齿轮具有耦合到第一柔性花键的第二圆形花键。 第二应变波动齿轮包括第二挠性齿条，并且第二挠曲齿条联接到输出联动件，使得来自输入联动件的输入的至少一部分经由第一应变波动齿轮和第二应变波动齿轮传递到输出联动件 应变波齿轮。

公开(公告)号：EP2842010B1

公开(公告)日：2017-09-13

申请号：EP13750167.2

申请日：2013-01-28

申请人： The Boeing Company

发明人： BEAUFRERE, Henry L.

IPC分类号： G05D1/06 ,  B64C13/04

CPC分类号： B64C13/16 ,  B64C9/00 ,  B64C13/04 ,  B64C13/503 ,  G05D1/042 ,  G08G5/02

公开(公告)号：EP2178750B1

公开(公告)日：2017-08-23

申请号：EP08772755.8

申请日：2008-07-02

申请人： Embraer S.A.

发明人： CELSO, Ferraz Dias

IPC分类号： B64C13/04

CPC分类号： B64C13/04 ,  B64C13/16 ,  Y10T74/19516

公开(公告)号：EP3016857B1

公开(公告)日：2017-04-12

申请号：EP14736925.0

申请日：2014-06-27

申请人： BAE Systems PLC

发明人： DAVIES, Robin William

IPC分类号： B64C13/10 ,  B64C13/04 ,  G05D1/00 ,  G05G1/04 ,  G05G5/03

CPC分类号： B64C13/10 ,  B64C13/04 ,  B64C13/22

摘要： An inceptor apparatus (10) for controlling a vehicle, in particular an aircraft comprises a control stick (15) for operation by a user and a user feedback generator (28) coupled to the control stick and configured to receive signals from a vehicle condition indicator (40) remote from the inceptor apparatus. The apparatus also has a first vehicle condition sensor (54,56) dedicated to the operation of the inceptor apparatus. In a first mode of operation, the user feedback generator (28) is operable to generate tactile feedback to the user via the control stick in dependence upon signals received from the vehicle condition indicator (40). In a second mode of operation, in the event that no signal is received from the vehicle condition indicator (40), the user feedback generator (28) is operable to generate tactile feedback to the user via the control stick in dependence upon signals received from the first vehicle condition sensor (54,56).

摘要翻译： 用于控制车辆，特别是飞行器的受体装置（10）包括用于由用户操作的控制杆（15）和耦合到控制棒的用户反馈发生器（28），并且被配置为从车辆状态指示器 （40）远离受体装置。 该装置还具有专用于受体装置的操作的第一车辆状态传感器（54,56）。 在第一操作模式中，用户反馈发生器（28）可操作以根据从车辆状态指示器（40）接收到的信号经由控制杆产生触觉反馈给用户。 在第二操作模式中，在没有从车辆状态指示器（40）接收到信号的情况下，用户反馈发生器（28）可操作以通过控制棒产生触觉反馈给用户，这取决于从 第一车辆状态传感器（54,56）。