大后翼与主流相互作用的模拟点火试验

推进技术 ›› 1997, Vol. 18 ›› Issue (3): 33-36.

大后翼与主流相互作用的模拟点火试验

王慧,蹇泽群,王华,允敏

陕西动力机械研究所!西安;710000;陕西动力机械研究所!西安;710000;陕西动力机械研究所!西安;710000;陕西动力机械研究所!西安;710000

发布日期:2021-08-15

SIMULATED IGNITION TEST OF THE INTERACTION BETWEEN LARGE REAR FIN AND MAIN STREAM

Shanxi Iust. of Power Machinery, Xi’an, 710000;Shanxi Iust. of Power Machinery, Xi’an, 710000;Shanxi Iust. of Power Machinery, Xi’an, 710000;Shanxi Iust. of Power Machinery, Xi’an, 710000

Published:2021-08-15

摘要/Abstract

摘要： 论述了缩比模拟发动机中大后翼与主流的相互作用以及大后翼点火的工作状态。通过试验,得出了主流和大后翼相互作用时,缝底部产生的压强较翼缝外空腔高。在试验条件下,模拟后翼气流与前部气流相互作用时没有爆燃现象。

关键词: 固体推进剂火箭发动机;模拟装药;固体推进剂点火;仿真试验

Abstract: By simulated testing motors, the interaction between mainstream from grain cyliderchannel and the gas flow from large,rear fin of grain during ignition pened is researched. It can bedrawn from tests that (1) the pressurization rate at the bottom of the fin slit is obviously higher thanthat in cylider channel and in the cavity outside the fin slit, (2) the pressure at the bottom of fin slitis higher than that outside the fin, (3) Deflagration is not found during ignition on the simulated testconditions.

Key words: Solid propellant rocket engine;Simulation charge;Solid propellant ignition;Simulation test

王慧,蹇泽群,王华,允敏. 大后翼与主流相互作用的模拟点火试验[J]. 推进技术, 1997, 18(3): 33-36.