公开(公告)号：WO2017178789A2

公开(公告)日：2017-10-19

申请号：PCT/GB2017/050861

申请日：2017-03-28

Applicant: BAE SYSTEMS PLC

Inventor： DEE, Justin, Mark ,  BEAN, Jason, Howard

CPC classification number: B64C13/12 ,  B64C13/0421 ,  B64C13/10

Abstract: A control system for electronically linked pilot and co-pilot inceptors (103) permits an asymmetric roll axis feel depending on whether an inceptor is moved inboard or outboard. A circuit (401) receives a signal representative of a force applied to the pilot's inceptor resulting from a side-to-side movement and detects if the force applied is in an inward or an outward direction. A gain factor is applied to the received force signal to produce a factored force signal. The gain applied to a signal representative of force applied in an outward direction is greater than the gain factor applied to a signal representative of force applied in an inward direction. A summer (212, 213) sums the factored force signal with a corresponding factored force signal derived from force signals from the co-pilot's inceptor to produce a modified force signal for use in a force feedback control system associated with each inceptor.

Abstract translation: 用于电子连接的飞行员和副驾驶员感应器（103）的控制系统根据感应器是被移动到内侧还是外侧而允许不对称的横摇轴感觉。 电路（401）接收表示由于左右移动导致的施加到飞行员的受体的力的信号，并检测施加的力是在向内还是向外的方向。 将增益因子应用于接收到的力信号以产生因子力信号。 施加到表示向外方向施加的力的信号的增益大于施加到表示向内方向施加的力的信号的增益因子。 夏令时（212,213）将因子受力信号与从来自副驾驶员感受器的力信号导出的相应的因子受力信号相加，以产生用于与每个受体相关联的力反馈控制系统中的修正的力信号。

公开(公告)号：WO2017178790A1

公开(公告)日：2017-10-19

申请号：PCT/GB2017/050862

申请日：2017-03-28

Applicant: BAE SYSTEMS PLC

Inventor： TAYLOR, Adam

IPC: B64C13/12

CPC classification number: B64C13/0421 ,  B64C13/12 ,  B64D43/00

Abstract: An aircraft (101) is provided with a single centrally located inceptor (110) for controlling pitch and roll of the aircraft. The inceptor (110) is provided with a double grip (11, 112) so that it may be comfortably operated by either a pilot or a co-pilot. A central location for the inceptor ensures that its motion and position is visible to both pilot and co-pilot. Not only is this a benefit from a safety point of view but also during pilot training. Alternatively, two inceptors (411, 412) are provided in the centre console (406) adjacent to one another for operation respectively by the pilot and co-pilot and may be mechanically linked. Optionally, the aircraft may be provided with outboard throttle quadrants (117, 118) for operation respectively by the co-pilot and pilot. The outboard throttle quadrants may be mechanically linked together.

Abstract translation: 飞机（101）具有单个位于中央的感应器（110），用于控制飞机的俯仰和俯仰。 感受器（110）设有双握柄（11,112），以便其可以由飞行员或副驾驶员舒适地操作。 导弹的中心位置确保其飞行员和副驾驶员都能看到其动作和位置。 从安全角度来看，这不仅是一个好处，而且在飞行员培训期间也是如此。 或者，两个感受器（411,412）设置在中央控制台（406）中彼此相邻，以分别由飞行员和副驾驶员操作，并且可以机械地连接。 可选地，飞行器可以设置有舷外节气门象限（117,118）以供副驾驶和飞行员分别操作。 舷外扇形象限可以机械连接在一起。

公开(公告)号：WO2017180855A1

公开(公告)日：2017-10-19

申请号：PCT/US2017/027393

申请日：2017-04-13

Applicant: TERRAFUGIA, INC.

Inventor： HENION, Julie ,  COLBURN, Kevin ,  DIETRICH, Carl, Curtis ,  DUKACH, Dagny ,  GOLASKI, Edmund ,  HEAFITZ, Andrew ,  VON DER HEYDT, Elizabeth ,  PENALVER-AGUILA, Liuis ,  SANDOZ, Bryan ,  STOWE, Ethan

IPC: B60F5/02 ,  F16H59/02

CPC classification number: F16H59/105 ,  B60F5/02 ,  B64C13/04 ,  B64C13/0421 ,  B64C37/00 ,  F16H59/0217 ,  F16H59/10 ,  F16H61/36 ,  F16H2059/0239

Abstract: The present invention relates to an electronic gear shifter assembly for a dual-mode flying and driving vehicle. The electronic gear shifter assembly may include a lever moveable between a first shifting path that includes at least one drive-related operating position, and a second shifting path that includes at least one flying-related operating position

Abstract translation: 本发明涉及一种用于双模式飞行和驾驶车辆的电子换档杆组件。 电子换档杆组件可以包括杆，该杆能够在包括至少一个驱动相关操作位置的第一换档路径和包括至少一个飞行相关操作位置的第二换档路径之间移动，

公开(公告)号：WO1995003212A1

公开(公告)日：1995-02-02

申请号：PCT/US1994008121

申请日：1994-07-19

Applicant: HONEYWELL INC.

Inventor： HONEYWELL INC. ,  HEGG, Jeffrey, W.

IPC: B64C13/12

CPC classification number: B64C13/12 ,  B64C13/0421 ,  B64C13/10 ,  B64C13/30 ,  B64C13/503 ,  B64C13/505 ,  G05G2009/04766 ,  Y02T50/44

Abstract: Conventional column controls for aircraft flight control systems are replaced by active sidesticks (80) which are connected to port and starboard aircraft mechanical, electrical or hydraulic systems by means of servo motors (76) and cables (26, 52). Movement of the active sidestick handles (80) is detected and a signal generated to drive a servo motor (76) in manner corresponding thereto, which in turn will drive cable assemblies (26, 52) which control aircraft flight control surfaces. Two sidesticks (80) are provided, preferably with an electrical cross-cockpit interconnect to cause movement of one sidestick to result in a signal being transmitted to a second sidestick to cause the motor thereof to force the sidestick to track the movement of the first sidestick. In an alternative implementation, the sidesticks are employed in a fly-by-wire system with a conventional cable system as backup. The cable system is disengaged from the sidesticks by means of a disengage clutch (86, 94) whereupon failure of the fly-by-wire system,the clutch will engage the cable system and provide a mechanical backup to the fly-by-wire system in the event of failure thereof.

Abstract translation: 用于飞行器飞行控制系统的常规列控制由主动侧线（80）代替，其通过伺服电机（76）和电缆（26,52）连接到端口和右舷飞行器机械，电气或液压系统。 检测到活动侧杆手柄（80）的移动和产生的驱动伺服电动机（76）的信号，该信号又将驱动控制飞行器飞行控制表面的电缆组件（26,52）。 提供两个侧线（80），优选地具有电叉车互连线，以引起一个侧线的运动，导致信号被传递到第二侧线，以使其电机强迫侧线跟踪第一侧线的移动 。 在替代实施方案中，侧线被用于具有传统电缆系统的备用线控系统。 电缆系统借助于脱离离合器（86,94）与侧线脱离接合，由此，线控飞行系统的故障，离合器将接合电缆系统，并为线控线系统提供机械备用 在发生故障的情况下。