Redundant Controller Design For Electric Actuating Cylinder Of Small Aerial Vehicle Landing Gear

All electric aircraft is a developing trend of aircraft in the future. Retractable undercarriage driven by wire is a research hot spot at home. In recent years, There is an increasing trend at the application of UAV in our country, which provides a research platform to it. As military aerospace products are characterized by high reliability and safety, it is a key and difficult point to realize the design of a high-reliability control system aimed at controlling electric cylinder actuator. In accordance to the control requirements of the landing gear system of small aerial vehicle, this paper has designed a set of redundant controller for the electric cylinder actuator. The main contents are as follows:(1) On the basis of high-reliability requirements of the control system, a redundant control scheme for the electric actuator cylinder of landing gear was proposed, and the design of management strategy for the redundant system has been carried on.(2) Regarding the electric cylinder actuator as the object, its mathematical model was established, Integrator clamping anti-windup control strategy and double closed-loop PID controller of speed and current were used, its simulation model was set up and simulated, the results showed that the designed strategy could meet the design requirements of the system; At the same time, the modeling and simulation of the single-control system of the electric actuating cylinder were completed, the results showed that the designed controller could meet the control requirements of the consumed time and speed trajectory of retracting.(3) Based on the overall design of the redundant control system, the hardware and software of the redundant control system of electric actuating cylinder was designed in detail, mainly including the hardware design of a single-lane redundant controller and the software design of its redundant management and servo control, the design of the voter hardware and the voting logic software, and the hardware design of the driver circuit.(4) The function and performance tests of the landing gear system were designed and carried out, and the results showed that the redundant control system could meet the design requirements.