Design Of Landing Gear Shock Absorber For Helicopter Using PID Active Control

Landing gear is an important part of helicopter for ground support, security sliding and energy absorption. In order to improve the performance of the landing gear, we use PID active control technology to optimize the landing gear. Based on helicopter landing gear shock absorber, this paper establish the dynamic analysis model of landing gear shock absorber and complete the parametric design. The landing gear test simulation is carried out by ADAMS/Aircraft. It follows that we use the particle swarm optimization to optimize PID parameters and establish the simulation model of landing gear by Matlab/Simulink. As the same, we complete the analyses-drop simulation under different conditions. At last, we get the conclusion by the comparison of two different simulation results.In this paper, the main contents are included as follows:1. On the background of the widely used of helicopter, this paper expounds the importance of the landing gear and introduces the development of the landing gear shock absorber. Then we introduce the virtual prototype technology and PID active control technology. The research content and methods are described briefly in this paper.2. On the basis of the swing arm landing gear, we use the traditional methods with a two-mass model to establish the dynamics analysis model of the landing gear. Then we expound advantage of the double cavity oil and gas shock absorber. The parameters of the landing gear is designed through the establishment of the kinematics and dynamics differential equation.3. According to the above parameters established, the virtual prototype model of the landing gear is set up by ADAMS/Aircraft, and complete the analyses-drop analyses which is for further analysis and discussion of the simulation results.4. Set up the mathematical model of landing gear shock absorber under the active control system.Then we deduce the dynamic function of the whole system and give the concrete realization form of active control of landing gear.5. We use the particle swarm optimization to optimize PID parameters in order to set up the simulation model by Matlab/Simulink as the same, so we obtain the simulation results.Finally, we compare the above results under different projects. The results show that: the performance of the landing gear is improved obviously with the PID active control technology compared with the ordinary landing gear.