Double-redundancy electro-hydrostatic actuator (EHA)

Abstract

The invention relates to a novel double-redundancy electro-hydrostatic actuator (EHA) adopting a novel hydraulic cylinder based on a single-output-rod hydraulic symmetry principle. The double-redundancy EHA mainly comprises two EHA bodies, namely an upper passage EHA body and a lower passage EHA body which are exactly identical, and a novel series hydraulic cylinder, wherein each EHA body comprises a DSP (Digital Signal Processing) controller, a power drive unit, a direct-current brushless motor, a bidirectional servo pump, one-way valves, an energy accumulator, a damping bypass valve, safety valves, a current sensor, a revolution speed sensor and pressure sensors; the series hydraulic cylinder comprises four chambers, namely a chamber A, a chamber B, a chamber C and a chamber D, the action area of the chamber A is the same as that of the chamber D, the action area of the chamber B is the same as that of the chamber C, and the chambers (B and C) and the chambers (A and D) are respectively connected with an oil inlet / outlet of the upper passage EHA body and an oil inlet / outlet of the lower passage EHA body. According to the designed double-redundancy EHA, the size and weight of the existing double-redundancy EHA can be reduced, and the change to the existing EHA is minimal; the designed novel hydraulic cylinder is simple in structure, convenient to manufacture and easy to implement, and thus, the application prospect is broad.

Description

technical field [0001] The invention relates to a double-redundancy electric hydrostatic actuator, which belongs to the technical field of electro-hydraulic servo control and actuation. Background technique [0002] The actuation system is an important part of the aircraft. There are four types of actuation systems on modern aircraft: hydraulic, electric, pneumatic and mechanical actuation systems. The current airborne hydraulic actuation system is the most widely used method in the field of flight control. Most of the current aircraft use hydraulic pressure as power, and the flight control computer performs comprehensive control by wire to control the rudder surface of the aircraft and realize flight control. Attitude and trajectory control. The performance of the airborne actuation system will directly affect the overall performance of the aircraft. [0003] In order to meet the future development of aircraft in the direction of high maneuverability, ultra-high speed an...

AI Technical Summary

Problems solved by technology

Although the above solution solves the problem of the large space occupied by the double-rod hydraulic cylinder in series, the structure is relatively complicated

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