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134 条记录 (耗时 0.013 秒)

    Multi-mode unmanned and manned vehicle systems and methods
    11.
    发明申请
    Multi-mode unmanned and manned vehicle systems and methods 有权
    多模式无人驾驶和载人车系统及方法

    公开(公告)号：US20070221782A1

    公开(公告)日：2007-09-27

    申请号：US11388026

    申请日：2006-03-22

    申请人： Dino Cerchie ,  Gregory Dockter ,  William Hardesty

    发明人： Dino Cerchie ,  Gregory Dockter ,  William Hardesty

    IPC分类号： B64C13/00

    CPC分类号： B64C39/024 ,  B64C13/22 ,  B64C13/46 ,  B64C13/50 ,  B64C2201/024 ,  B64C2201/146 ,  G05D1/0044

    摘要： An apparatus for converting a manned aircraft for unmanned flight, the aircraft including at least one pilot control capable of manipulation to affect operation of the aircraft, the apparatus comprising a first actuator and a second actuator each configured to selectively provide movement or resistance to movement in a first manner including linear or rotational motion, a first clutch and a second clutch each configured to selectively couple movement of the associated actuator to the pilot control, and a vehicle controller capable of being selectively enabled to operate the pilot control actuators and clutches providing unmanned operation of the aircraft or disabled providing manned operation of the aircraft. The first actuator has a first scope describing a first amount of allowable movement, while the second actuator has a second scope larger than the first scope.

    摘要翻译： 一种用于转换用于无人驾驶的载人飞行器的装置，所述飞行器包括能够操纵以影响飞行器的操作的至少一个先导控制装置，所述装置包括第一致动器和第二致动器，每个致动器和第二致动器被配置为选择性地提供运动或抵抗运动 包括线性或旋转运动的第一方式，第一离合器和第二离合器，每个离合器和第二离合器都被配置为选择性地将相关联的致动器的运动耦合到先导控制器;以及车辆控制器，其能够被选择性地使能操作提供无人驾驶的先导控制致动器和离合器 飞机的运行或残疾人提供载人操作的飞机。 第一致动器具有描述第一允许移动量的第一范围，而第二致动器具有大于第一范围的第二范围。

    Method and apparatus for stabilizing the steering force in an aircraft, especially a helicopter
    12.
    发明授权
    Method and apparatus for stabilizing the steering force in an aircraft, especially a helicopter 失效
    用于稳定飞机，特别是直升机中的转向力的方法和装置

    公开(公告)号：US4664346A

    公开(公告)日：1987-05-12

    申请号：US730546

    申请日：1985-05-06

    申请人： Herbert Koenig

    发明人： Herbert Koenig

    IPC分类号： B64C13/46 ,  G05D1/00 ,  G05D1/08

    CPC分类号： B64C13/46 ,  G05D1/0061 ,  G05D1/0858

    摘要： The steering or control force for operating a steering column in an aircraft, especially in a rotary wing aircraft, is stabilized. The steering column influences through an articulated steering or control linkage the elevator assembly or the rotor blade adjustment, whereby a signal is employed which is dependent on the measured flight speed. It is necessary to signal to the pilot at all times how the steering column must be moved. Such signalling must be definite and free of any disturbing influences and the pilot must receive such signalling through the steering column manual force which is a force reacting to the operation of the steering column. For this purpose a speed dependent signal is supplied to a servomotor. This signal rises with the flight speed at least above a preselectable threshold value. The servomotor in turn controls the tensioning state of a spring which is pivoted at one end to the steering column and at the other end to the displacement member of the servomotor. Preferably, the point of articulation between the spring and the steering column is located approximately opposite the point of articulation between the steering column and the steering or control linkage. Additionally, a feedback signal derived from sensing the displacement caused by the servomotor is added to the speed dependent signal. The feedback signal varies in the same sense as the displacement caused by the servomotor and serves to achieve proportionality between the signal S and said displacement.

    摘要翻译： 用于在飞行器，特别是旋转翼飞行器中操作转向柱的转向或控制力是稳定的。 转向柱通过铰接式转向或控制联动装置影响电梯组件或转子叶片调节，由此使用取决于测量的飞行速度的信号。 必须始终向飞行员发信号，转向柱必须如何移动。 这种信号必须是确定的，没有任何扰动的影响，飞行员必须通过转向柱手动力来接收这种信号，这是对转向柱的操作作用的力。 为此，向伺服电机提供与速度相关的信号。 该信号随飞行速度升高至少高于预选阈值。 伺服马达又控制弹簧的张紧状态，该弹簧的一端枢转到转向柱，另一端枢转到伺服马达的移动构件。 优选地，弹簧和转向柱之间的铰接点大致与转向柱和转向或控制连杆机构之间的铰接点相对。 此外，从感测由伺服电动机引起的位移导出的反馈信号被加到速度相关信号上。 反馈信号在与伺服电动机产生的位移相同的意义上变化，并且用于实现信号S和所述位移之间的比例。

    Steering mechanism with an active force feedback, especially for aircraft
    13.
    发明授权
    Steering mechanism with an active force feedback, especially for aircraft 失效
    具有主动力反馈的转向机构，尤其适用于飞机

    公开(公告)号：US4236685A

    公开(公告)日：1980-12-02

    申请号：US13748

    申请日：1979-02-21

    申请人： Gerhard K. Kissel

    发明人： Gerhard K. Kissel

    IPC分类号： B64C13/50 ,  B64C13/46 ,  G05D1/00 ,  G05D1/08

    CPC分类号： B64C13/46 ,  G05D1/0061

    摘要： The present steering mechanism, especially for an aircraft includes a manly operable steering member and an automatic steering system. A difference signal formed from a pilot input and trim signal and from a gyro feedback signal is supplied to a force control and damping circuit twice, once directly and once through an authority limit circuit. The output of the authority limit circuit is also supplied to the motors forming part of the automatic steering system. The force control and damping circuit also receives further input signal or signals representing steering information. The output of the force control and damping circuit is connected to the feel unit of the steering system, whereby an immediate manual control by the pilot is effective, however limited against an excessive control or so-called manual over control.

    摘要翻译： 本发明的转向机构，特别是用于飞行器的转向机构包括手动操作的转向构件和自动转向系统。 从导频输入和微调信号形成的差分信号和来自陀螺反馈信号的差分信号一次直接和一次地通过权限限制电路被提供给力控制和阻尼电路两次。 权限限制电路的输出也提供给形成自动转向系统的一部分的电动机。 力控制和阻尼电路还接收进一步的输入信号或表示转向信息的信号。 力控制和阻尼电路的输出连接到转向系统的感觉单元，由此飞行员的即时手动控制是有效的，但是受到过度控制或所谓的手动过载控制的限制。

    Aerodynamic surface control feel augmentation system
    14.
    发明授权
    Aerodynamic surface control feel augmentation system 失效
    气动表面控制感觉增强系统

    公开(公告)号：US3960348A

    公开(公告)日：1976-06-01

    申请号：US601815

    申请日：1975-08-04

    申请人： Donald W. Fowler ,  Sean J. O'Connor

    发明人： Donald W. Fowler ,  Sean J. O'Connor

    IPC分类号： B64C27/64 ,  B64C13/46 ,  G05D1/00

    CPC分类号： B64C13/46 ,  G05D1/0066

    摘要： In a helicopter, a pilot-actuated lever controls, through linkage mechanisms, a servo valve to drive a hydraulic piston; the piston moves a swash plate which in turn controls movement of rotor blade pitch positioning mechanisms against the force of blade loading, caused by aerodynamic forces. Blade loading, heretofore monitored visually by the pilot on a cruise guide indicator instrument, is used herein to control a secondary input to the servo valve, thereby to alter the position linkage mechanism which causes the force of a spring attached thereto to impose a force on the collective pitch control for blade loadings in excess of one-third of maximum allowable blade loads, in a direction tending to drive the control to lower collective pitch (lower blade loading). This provides "feel" to the pilot in proportion to blade loading when at critical magnitudes. A trim system is selectively actuatable to provide an input to the auxiliary valve which tends to maintain the collective pitch control in a selected position.

    摘要翻译： 在直升机中，先导操纵杆通过连杆机构控制伺服阀来驱动液压活塞; 活塞移动斜盘，该斜盘又由于空气动力而控制转子叶片俯仰定位机构的动作抵抗叶片负载的力。 目前为止，在巡航导向指示器仪表上由飞行员目视监视的叶片装载，用于控制伺服阀的次级输入，从而改变连接机构，使连接到其上的弹簧的力施加力 叶片装载的总体俯仰控制超过最大允许叶片载荷的三分之一，方向倾向于驱动控制以降低总体俯仰（下叶片载荷）。 当在临界量级时，这对飞行员的“感觉”与叶片负载成比例。 修剪系统可选择性地致动以向辅助阀提供输入，其倾向于将集体俯仰控制保持在选定位置。

    Variable load feel
    15.
    发明授权
    Variable load feel 失效
    可变负载感

    公开(公告)号：US3747876A

    公开(公告)日：1973-07-24

    申请号：US3747876D

    申请日：1971-06-01

    申请人： MC DONNELL DOUGLAS CORP

    发明人： FORTNA S ,  KOROCH R

    IPC分类号： B64C13/24 ,  B64C13/04

    CPC分类号： B64C13/24 ,  B64C13/46 ,  Y10T74/20006 ,  Y10T74/206

    摘要： A system to generate control surface feedback forces in an aircraft employing powered control surfaces. The system is primarily mechanical in nature and includes at least two springs as the force generating elements, and means which predeterminately interconnect the springs, predeterminately vary the preload of one spring, and predeterminately vary the effective spring rates of the springs in correspondence to the flight conditions of the aircraft.

    摘要翻译： 在采用动力控制面的飞机中产生控制面反馈力的系统。 该系统本质上是机械的，并且包括至少两个弹簧作为力产生元件，以及预先连接弹簧的装置，预先改变一个弹簧的预载荷，并且预先根据飞行器改变弹簧的有效弹簧刚度 飞机的状况