An Aircraft Electrostatic Hydraulic Brake Actuator

Abstract

The invention provides an aircraft electro hydrostatic brake actuator. The output shaft of a brushless direct current motor is coaxially connected with a displacement-fixed two-way plunger pump, a pressurized tank is used for supplying initial pressure for the inlet of the displacement-fixed two-way plunger pump, one outlet of the displacement-fixed two-way plunger pump is connected with a hydraulic cylinder through an oil filter and a two-position two-way solenoid valve, the other outlet of the displacement-fixed two-way plunger pump is connected with the two-position two-way solenoid valve through the oil filter and a relief valve, the pickup state of the two-position two-way solenoid valve is controlled by a solenoid valve control unit, thus switching between brake pressure tracking and take-off line brake pressure maintaining functions is realized, the internal pressure of the hydraulic cylinder is measured by a pressure measuring unit, the pressure information is transmitted to a controller for pressure closed-loop control, the controller receives a brake pressure instruction through an instruction port, to further control the solenoid valve control unit and the brushless direct current motor and a brake disc is driven by the hydraulic cylinder. The aircraft electro hydrostatic brake actuator is simple in structure, high in efficiency, high in frequency response and small in size and weight, and take-off line brake pressure maintaining can be realized for a long time.

Description

technical field [0001] The invention relates to an aircraft brake actuator. Background technique [0002] Early aircraft braking systems borrowed directly from automobile braking technology. In the 1920s, the mechanical linkage brake system was used on aircraft, which was a form of control using human power as the power source, exactly the same as the car brakes at that time. In the 1930s, the airbag brake system was adopted. The system added direct-acting accessories, which increased the braking force and reduced the pilot's operating burden, but the control form was still mainly manual operation. Soon the hydraulic brake device officially entered the stage of history. Compared with the previous ones, its control method and system structure have made great progress, which is mainly reflected in the addition of a dual-redundancy system for air-conditioning backup. The control system has changed from human brain control to Inertial sensor (on / off) control form. The disadva...

AI Technical Summary

Problems solved by technology

Its disadvantages are that the system efficiency is very low (less than 50%), the frequency response is not high, it cannot maintain the brake pressure of the take-off line for a long time, and the volume and weight are large

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