自动飞行控制板仿真分析与实验研究

Simulation analysis and experimental research of automatic flight control plate

在热稳态理论和动力学随机振动理论的基础上,建立了自动飞行控制板关键部件仿真模型,通过数值仿真分析,得到了温度和应力分布状况,使用接触式与非接触式结合的方式进行热稳态试验,得到了高温区的实际温度,通过随机振动模态测试,得到仪表支架等效3σ应力和电源前6阶频率,表明数值仿真分析的结果与实验相差小于10%。给出了提高仿真和实验结果精度的关键措施。仿真和试验分析获得的热稳态和力学性能为自动飞行控制板设计改进提供了依据,可为后续提高复杂工作环境下的稳健性设计提供参考。

The numerical models of flight control plate were established based on thermal steady state theory and dynamic random vibration theory.The temperature and stress distribution were obtained though the simulation.Then the actual temperatures at high temperature areas from simulation were tested.The three sigma equivalent stress and first six frequencies were also observed through the vibration modal test.It is shown that the relative gaps between experiment results with the numerical simulation results are less than 10%.The key measures to improve the accuracy of simulation and experimental results are given.The obtained properties could provide a direct guide for the design and could be a significant reference for the future robustness design when considering the complicated working environment.