The invention discloses a launch and recovery electrical control system of an aircraft landing gear. The launch and recovery electrical control system comprises a landing gear control switch, a displayer, a plurality of position sensors, a mechanical and electrical management computer, a power driving device, a landing gear hydro-electric valve, a guard board hydro-electric valve, a landing gear mechanism and a guard board mechanism. After the mechanical and electrical management computer receives a launch and recovery instruction of the control switch of the landing gear, and corresponding control signals are output to the power driving device according to logistics by collecting feedback signals of position sensors mounted on the landing gear mechanism and the guard board mechanism, so that the landing gear hydro-electric valve and the guard board hydro-electric valve are controlled to be reversed, and normal launch and recovery of the landing gear mechanism and the guard board mechanism are achieved; and meanwhile, the mechanical and electrical management computer monitors the states of the landing gear and the state of guard boards in real time, and the position states and failure alarm information are sent to the displayer. The development cost of an aircraft is effectively reduced, and the development period is effectively shortened; and the monitoring on the states and failures of the launch and recovery system of the landing gear is reinforced, and the maintenance of the system is greatly improved.
Launch and recovery electrical control system of aircraft landing gear
2015-10-28
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |