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以某型双腔式起落架为研究对象,建立了起落架着陆动力学方程,应用ADAMS软件构建该起落架的虚拟样机模型,在考虑控制对象模型的不确定性和系统干扰抑制的情况下,基于混合灵敏度问题求得鲁棒H∞控制器。应用ADAMS及Matlab/Simulink软件,对半主动起落架的落震仿真过程进行实时控制,进行机械系统和控制系统的联合仿真分析,并对比被动控制和半主动控制起落架的仿真结果。对比研究结果表明:半主动控制起落架能够有效地降低直升机着陆时的冲击载荷和振动响应,从而提高直升机着陆的安全性和舒适性。
Taking a certain type of dual-cavity landing gear as the research object, a landing gear dynamics equation is established, and a virtual prototype model of the landing gear is constructed by ADAMS software. Considering the uncertainty of the control object model and the system interference suppression, Robust H∞ Controller Based on Mixed Sensitivity Problems. ADAMS and Matlab / Simulink software are used in real-time control of the falling simulation of semi-active undercarriage. The joint simulation of mechanical system and control system is carried out. The simulation results of passive control and semi-active control landing gear are compared. The results of the comparative study show that the semi-active control of the landing gear can effectively reduce the impact load and vibration response of the helicopter landing, thus improving the safety and comfort of helicopter landing.