To address the problem of long development cycle and high cost of passive shot high altitude test of solid rocket engine,based on the N-S equation and the S-A model,numerical simulations are carried out for the engine pressure building,pressure stabilization and pressure reduction stages of the high altitude simulator test using small expansion ratio nozzles,small size high altitude chambers with different diameters,pressure diffusers and pressure far fields,and the flow field structures in the high altitude chambers and diffusers are analyzed at each stage of each model.The results show that when the engine pressure is stabilized,the pressure inside the large size cabin is more stable than that inside the small size cabin,and the diffuser in the pilot system has a better pressure expansion effect and a better ability to extract the gas inside the cabin;while the deceleration and pressurisation effect of the large aspect ratio diffuser in the pilot system is not obvious compared with that of the small aspect ratio,and the changes in pressure and Mach number when the airflow passes through the surge are within 2 KPa and 0.04.The calculation error at the outlet of the diffuser is strongly related to the setting of the pressure far field.
solid rocket motorshigh altitude simulation test vehiclesnumerical simulationdiffuser
维普
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