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    • 54. 发明授权
    • Hydraulic control system for aircraft
    • 飞机液压控制系统
    • US5351914A
    • 1994-10-04
    • US894554
    • 1992-06-05
    • Toru NagaoHiroyuki Kataoka
    • Toru NagaoHiroyuki Kataoka
    • B64C13/40F15B9/03F15B11/028B64C13/36
    • B64C13/40F15B9/03Y02T50/44
    • A hydraulic control system for aircraft is disclosed, which has a flight maneuver system mounted on the aircraft and provided with a maneuver signal input and output system for controlling the aircraft depending on flight conditions. The system includes a differentiating circuit responsive to a first output signal for calculating an actuating speed of a servo actuator and for generating a speed signal Vc, a load calculating circuit responsive to the load signal for computing the load on the actuator and for producing a load signal, a pressure calculating circuit responsive to the speed and load signals for computing a pressure Ps to the actuator and for producing a pressure signal, and a setting circuit responsive to the pressure signal for deciding an optimum pressure of the hydraulic pump so as to precisely control the flight surface without energy loss. The pressure Ps is calculated by the following formula:Ps=E.multidot.(Vc/Vm).sup.2 .multidot.Pm+F/Awhere E: coefficient, Pm: maximum pressure of the pump, VM; maximum speed of the actuator, F: a load of the actuator, and A; actuating piston area of the actuator.
    • 公开了一种用于飞机的液压控制系统,其具有安装在飞行器上的飞行机动系统,并且具有根据飞行条件来控制飞行器的机动信号输入和输出系统。 该系统包括响应于第一输出信号的微分电路,用于计算伺服致动器的致动速度并产生速度信号Vc,负载计算电路响应于负载信号,用于计算致动器上的负载并产生负载 信号,响应于速度和负载信号的压力计算电路,用于计算致动器的压力Ps和产生压力信号,以及响应于压力信号的设定电路,用于确定液压泵的最佳压力以精确地 控制飞行面无能量损失。 压力Ps通过以下公式计算:Ps = Ex(Vc / Vm)2xPm + F / A其中E:系数,Pm:泵的最大压力,VM; 执行器的最大速度,F:执行器的负载,A; 致动器的活塞区域。