Landing gear actuator control lock

Abstract

The invention discloses a landing gear actuator control lock which comprises a shell with an axial through hole. A first nozzle is mounted at the left end of the shell, a third nozzle is mounted at the right end of the shell, the first nozzle is communicated with a first rod cavity of an actuator, the third nozzle is communicated with a second rod cavity of the actuator, an opening and closing structure is mounted in the axial through hole of the shell and used for opening or closing oil circuits of the first rod cavity and the second rod cavity of the actuator, a first thermal safety valve and a second thermal safety valve are mounted in the axial through hole of the shell, the first thermal safety valve is used for controlling excessive pressure due to excessive temperature and starting pressure release when the first rod cavity of the actuator is locked, and the second thermal safety valve is used for controlling excessive pressure due to excessive temperature and starting pressure release when the second rod cavity of the actuator is locked. Design complexity of a hydraulic system is reduced, the weight of the system is reduced, space is saved, and reliability and safety of the system and a mechanism are improved.

Description

technical field [0001] The invention relates to a landing gear actuator control lock, which is especially suitable for a hydraulic system that has strict requirements on space layout and weight control, and has a hydraulic lock function and a thermal safety insurance function, such as an aircraft landing gear strut actuator, Hydraulic system of flap drive mechanism and other products with similar functions. Background technique [0002] The functions of the landing gear door actuator are: 1) Under the action of hydraulic oil, drive the landing gear door to retract or lower; 2) Under the joint action of the control lock and the built-in mechanical lock, fix the door In open or closed position state. [0003] With the continuous improvement of modern aircraft landing gear door retractable mechanisms and system reliability requirements, generally a mechanical lock is installed in the door actuator, and a hydraulic lock is also required, so that the mechanical lock and hydrauli...

AI Technical Summary

Problems solved by technology

[0004] At present, when the landing gear door actuating cylinder is realized, the hydraulic lock function, the oil thermal safety protection function of the double lock chamber, and the double redundancy design of unlocking when the door is closed are generally completed by multiple independent hydraulic control components. , which will increase the complexity of the design of the hydraulic system and the door retractable mechanism, and will also bring about problems such as difficulty in structural layout, increased weight, and reduced reliability.

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