高空台飞行环境模拟系统数字建模与仿真研究

In order to analyze the dynamic control performance of a newly built altitude test facility flight environment simulation system and study the coupling level of each subsystem, the modeling and simulation of the system were conducted. The characteristics of the inlet valves, exhaust valve, the hydraulic servo system and the pipe-volume were studied by numerical method. Using similar theory and component level modeling method, the mathematical models of the test facilities were established, and the double closed-loop pressure control structure of the flight environment simulation system was designed. Based on the function decomposition of actual system, the digital simulation platform of the flight environment simulation system was established, and pressure dynamic control simulation was carried out in the platform. Simulation results indicate that the pressure dynamic regulating processes were consistent with the actual system and could reflect the pressure dynamic regulating processes of the actual system, the mathematical models of the system were reasonable. To examine the dynamic control performance of the flight environment simulation system, the influence of engine mass flow variation on each subsystem was simulated in the simulation platform, and the maximum pressure deviation of pressure stabilizing cavity, inlet and exhaust of engine was 4.5kPa, 3.4kPa and 1.5kPa.