Design and application of intake and exhaust simulation system for altitude ground test facilities
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摘要:
基于国内某高空台进排气系统的结构与试验特性开展了相关设备的动态特性建模、仿真系统设计以及应用研究。针对管道、调节阀、节流部件、液压控制系统和模拟发动机流量的拉瓦尔喷管等关键试验设备进行了数学建模,得到了相应的模型库;根据高空台进排气结构设计了全数字仿真系统和半物理仿真系统,并通过与实际试验数据的对比证明了仿真系统的有效性。根据仿真验证结果以及仿真系统应用分析可以得出:利用仿真系统计算的发动机进气温度和压力与试验数据相比动态变化趋势一致,温度的最大相对误差不大于0.5%,压力的最大相对误差不大于3%;基于高空台试验设备模型和仿真系统开发的控制方法使得压力调节时间缩短为原来的1/3,有效提升了过渡态调节性能。
Abstract:Based on the layout and test characteristics of the aviation engine altitude ground test facilities, the simulation system was created, the required equipment was modeled, and application research was conducted. The mathematical modeling of key test equipment such as piping, regulating valves, throttling components, hydraulic control system and Laval nozzle (used to simulate engine flow) was carried out to obtain a model library. A comprehensive digital simulation system and a semi-physical simulation system were built, and their performance was demonstrated by comparing them with real-life test results. The engine’s intake temperature and pressure calculated by the simulation system were compatible with the dynamic change trend when compared with the test data, according to the simulation verification results and analysis. Where temperature relative error was limited to a maximum of 0.5 percent, the pressure relative error was limited to a maximum of 3 percent. The pressure regulation time was shortened to 1/3 by the control technique created based on the model and simulation system of the high-altitude test equipment, the transition state regulation performance was significantly enhanced.
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