The invention belongs to the technical field of airplane electromechanical control, and discloses an electric dual-redundancy electro-hydrostatic airplane wheel brake system which comprises a left brake oil cup, a right brake oil cup, a left electric control brake combination valve, a right electric control brake combination valve, a left airplane wheel brake device, a right airplane wheel brake device, a left wheel speed sensor, a right wheel speed sensor and a control box for redundancy switching. The left brake oil cup is connected with a left airplane wheel brake device through a left electric control brake combination valve, the right brake oil cup is connected with a right airplane wheel brake device through a right electric control brake combination valve, and the left electric control brake combination valve and the right electric control brake combination valve are both combinations of piston structures driven by motors and electromagnetic valves. The left electric control brake combination valve and the right electric control brake combination valve are connected with a fly pipe computer through signal lines and are controlled by the fly pipe computer. The left wheel speed sensor and the right wheel speed sensor are used for monitoring the rotating speed of an aircraft left wheel and the rotating speed of an aircraft right wheel respectively; the control box for redundancy switching switches the control relation of the right electric control brake combination valve and the left electric control brake combination valve to the left airplane wheel brake device and the right airplane wheel brake device respectively. The device can realize power telex, adopts pressure closed-loop control, is high in precision, and has the advantages of relatively high integration level, small size, convenience in installation and maintenance and the like. The dual-redundancy design of an electrical part is adopted, redundancy switching is achieved through independent equipment, the reliability of a braking system is guaranteed, synchronous skid resistance can be achieved, and safe operation of an airplane is guaranteed.

    本发明属于飞机机电控制技术领域,公开了一种电气双余度的电静液机轮刹车系统,包括左刹车油杯、右刹车油杯、左电控刹车组合阀、右电控刹车组合阀、左机轮刹车装置、右机轮刹车装置、左轮速传感器、右轮速传感器、承担余度切换的控制盒;左刹车油杯通过左电控刹车组合阀连接左机轮刹车装置,右刹车油杯通过右电控刹车组合阀连接右机轮刹车装置,左电控刹车组合阀和右电控刹车组合阀均为电机驱动的活塞结构与电磁阀的组合,左电控刹车组合阀和右电控刹车组合阀均通过信号线连接飞管计算机并接受飞管计算机的控制;左轮速传感器和右轮速传感器分别监测飞机左轮的转速和飞机右轮的转速;承担余度切换的控制盒切换右电控刹车组合阀和左电控刹车组合阀分别对左机轮刹车装置和右机轮刹车装置的控制关系。本发明可实现功率电传,同时采用压力闭环控制,精度高,具有集成度较高、体积小、安装维护方便等优点。电气部分两余度设计,通过独立设备实现余度切换,保证刹车系统的可靠性,可实现同步防滑,保障飞机的安全运行。


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    Title :

    Electro-hydrostatic airplane wheel brake system with electric dual redundancy


    Additional title:

    一种电气双余度的电静液机轮刹车系统


    Contributors:
    LIU LONG (author) / LI ZHILONG (author) / YUAN ZHIWEN (author) / WU DELE (author) / WANG ZHE (author) / WANG NANXING (author) / HUANG ZHIJUN (author) / BAI CHENWEI (author)

    Publication date :

    2025-03-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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