초록 ▼

A hydraulic control system for an aircraft landing gear system has a hydraulic pressure source connected to a hydraulic fluid pressure transmission line, and at least one hydraulic actuator for extending and/or retracting a landing gear. A supply valve and a direction valve are arranged in series al

A hydraulic control system for an aircraft landing gear system has a hydraulic pressure source connected to a hydraulic fluid pressure transmission line, and at least one hydraulic actuator for extending and/or retracting a landing gear. A supply valve and a direction valve are arranged in series along the hydraulic fluid pressure transmission line. The supply valve and direction valve are adjustable to control the hydraulic pressure supplied to the at least one hydraulic actuator. The control system also controls uplock actuators.

대표청구항 ▼

1. An actuation control system for an aircraft landing gear, the actuation control system comprising: a hydraulic fluid pressure transmission line connectable to a hydraulic pressure source;at least one hydraulic actuator for extending and/or retracting a landing gear; anda supply valve and a direct

1. An actuation control system for an aircraft landing gear, the actuation control system comprising: a hydraulic fluid pressure transmission line connectable to a hydraulic pressure source;at least one hydraulic actuator for extending and/or retracting a landing gear; anda supply valve and a direction valve arranged in series along the hydraulic fluid pressure transmission line, the supply valve and the direction valve being adjustable to control the hydraulic pressure supplied to the at least one hydraulic actuator,wherein an open position of the supply valve in combination with an open position of the direction valve cause retraction of the landing gear, andwherein an open position of only one of the supply valve and the direction valve causes no retraction of the landing gear when the landing gear is already extended. 2. An actuation control system according to claim 1, wherein when at least one of the supply valve and the direction valve is in a closed position, the system causes the landing gear to extend. 3. An actuation control system according to claim 1, wherein the supply valve and the direction valve have substantially the same internal structure as one another. 4. An actuation control system according to claim 1, wherein the supply valve and the direction valve comprise 2-way valves. 5. An actuation control system according to claim 1, wherein the supply valve and the direction valve are solenoid actuated and spring biased to their closed positions. 6. An actuation control system according to claim 1, wherein the supply valve and the direction valve are directly connected to one another. 7. An actuation control system according to claim 1, wherein the supply valve and the direction valve are situated within a valve block. 8. An actuation control system according to claim 7, further including one or more barriers for preventing the propagation of cracks. 9. An actuation control system according to claim 7, wherein an uplock valve is included in the valve block. 10. An actuation control system according to claim 1, wherein the supply valve and the direction valve are in hydraulic contact with one another. 11. An actuation control system according to claim 1, further including at least one uplock valve.