| 摘要 |
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=Ex(Vc/Vm)2xPm+F/A where 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.
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