基于Matlab/Simulink的超声速自由射流试验系统建模分析  

Modeling Analysis of Supersonic Free Jet Test System Based on Matlab/Simulink

作　　者：孙顺利 李纲[1] 芦海洋 Sun Shunli;Li Gang;Lu Haiyang(China Airborne Missile Academy,Luoyang 471009,China)

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2021年第4期76-81,共6页Aero Weaponry

基　　金：航空科学基金项目(2018ZD12008);中国空空导弹研究院科技创新基金(201804S11)。

摘　　要：为实现对关键指标舱压的动态变化过程仿真,基于Matlab/Simulink对某超声速自由射流试验系统的关键物理过程建模,并将仿真结果与试验结果比较分析。该模型的仿真舱压与试验舱压的曲线变化规律一致,试验状态稳定段的仿真舱压与试验舱压的误差在1 kPa以内,喷管出口仿真静压值与试验静压值也小于1 kPa,同时还具备模拟启动迟滞现象和启动后的舱压与喷管进口总压的正线性关系现象的能力。对比分析结果表明,该Simulink建模方法能有效模拟超声速自由射流试验系统舱压的动态变化。In order to simulate the dynamic change process of the key index cabin pressure,the key physical process of supersonic free jet test system is modeled based on Matlab/Simulink,and the simulation results are compared with the test results.The curve variation law of the simulated cabin pressure of the model is consistent with that of the test cabin pressure.The error between the simulated cabin pressure and the test cabin pressure in the stable section of the test state is within 1 kPa,and the simulated static pressure at the nozzle outlet and the test static pressure are also less than 1 kPa.At the same time,it also has the ability to simulate the start-up hysteresis phenomenon and the main line relationship between the cabin pressure after startup and the total pressure at the nozzle inlet.The comparative analysis results show that the Simulink modeling method can effectively simulate the dynamic change of cabin pressure of supersonic free jet test system.

关 键 词：自由射流试验 舱压 超声速喷管 引射 扩压 

分 类 号：TJ763[兵器科学与技术—武器系统与运用工程] V231.3[航空宇航科学与技术—航空宇航推进理论与工程]