The Semi-Active Optimal Control Method of Aircraft Landing Gear

Abstract

When designing a landing gear damper, it is well-known that damper characteristics required for good handling are not the same as those required for good ride comfort. Semi-active control landing gear damper, as their name implies, fill the gap between purely passive damper and fully active control Langing gear-control systems and offer the reliability of passive systems, yet maintain the versatility and adaptability of fully active devices. During recent years there has been considerable interest towards theoretical study and practical practical implementation of this semi-active control landing gear damper for their low energy requirement and cost. For this reason, The basic theoretical for semi-active landing gear damper design and implementation has been briefly reviewed, mathematical model of semi-active control landing gear is established . A state feedback semi-active controller is designed. At last, the passive control landing gear model and semi -active control landing gear model are simulated. Simulation result shows that the vibration of passive control landing gear is vehement, and the system stable time is long.But in the simi-active control landing gear system the impact load and vibraton can be reduced, the aircraft can reach the stability state in a few seconds. Using linear quadratic optimal control effect is good.