Abstract: A system reduces force fight between hydraulic actuators (22, 24) operated on independent hydraulic circuits (29, 49) which position a control surface (20) of an aircraft. Each circuit includes a hydraulic supply (30, 50). A pressure equalization valve (70) is connected to first sides (42, 62) of the actuators. In the event of a pressure imbalance, a spool (82) shifts in the pressure equalization valve. Movement of the spool enables fluid from the circuit supply to be delivered through the equalization valve to the actuator at the lower pressure, rapidly eliminating the imbalance.

Abstract: A direct drive valve wherein a force motor (10) controls the position of a valve slide (20) through a linkage (14). The force motor includes a spring assembly (62) having cantilevered springs (68 and 70) that include petals (72). The armature (48) of the force motor is guided by a plurality of balls (84) that contact both an internal tube assembly (47) and the armature.

Abstract: A hydraulic system includes a pump, a reservoir, and an actuator system. A hydraulic circuit breaker is arranged to compare fluid flow to and from the actuator system and to shut off this flow in the event the flow to the actuator system is greater than the flow returning from the actuator system by more than a predetermined differential, thereby indicating a leakage condition. A hydraulic circuit breaker reset device is hydraulically connected to the actuator system and to the circuit breaker. When the circuit breaker is in a shut-off condition, the reset device continuously pressure tests the actuator system. If the pressure in the actuator system increases to indicate the absence of fluid leakage, the reset device responds to the pressure increase in the actuator system to provide a reset signal to the circuit breaker. After the circuit breaker is reset to its normal operating position, a timing piston returns the reset device to its normal operating condition.