Fault Injection of Electro-Hydrostatic Actuator and its Influence Analysis of Aircraft Flight Performance

Airborne actuation system is one of the key flight control subsystems to realize flight attitude and trajectory control. Its performance directly affects the flight quality of aircraft. This paper discusses the influence of Electro-Hydrostatic Actuator (EHA) failure on flight performance of aircraft. This paper first describes the development of EHA, introduces its structure and working principle, decomposes the electro-hydrostatic actuator into the original component level, analyses and models them respectively, and proposes a fault injection scheme for possible faults. Finally, assuming that the actuator on the rudder of an aircraft fails, the impact on the flight performance of the aircraft is carried out. In this paper, the control performance of aircraft under different faults is simulated and analyzed, which provides a theoretical basis for fault-tolerant control of aircraft under faults.