发射发动机气动分离机构设计与试验

推进技术 ›› 1997, Vol. 18 ›› Issue (5): 32-35.

发射发动机气动分离机构设计与试验

江兴宏,周士喆,汪浩平,门举先

上海新力动力设备研究所!上海;200125;上海新力动力设备研究所!上海;200125;上海新力动力设备研究所!上海;200125;上海新力动力设备研究所!上海;200125

发布日期:2021-08-15

DESIGN AND EXPERIMENT OF PNEUMATIC SEPARATION APPARATUS FOR TAKE-OFF MOTOR

Shanghai Xinli Power Equipment Research Inst., Shanghai, 200125;Shanghai Xinli Power Equipment Research Inst., Shanghai, 200125;Shanghai Xinli Power Equipment Research Inst., Shanghai, 200125;Shanghai Xinli Power Equipment Research Inst., Shanghai, 200125

Published:2021-08-15

摘要/Abstract

摘要： 对发射发动机气动分离机构工作过程进行数值仿真，着重分析了突缩突扩气流不等熵流动过程的流量计算方法，给出了内弹道p-t曲线、活塞腔压强p-t曲线、推力F-t曲线、分离剪切力Fτ－t曲线和分离时间的预示结果，并通过真实发动机试验获得验证。计算与试验结果为分离机构设计与分析提供了依据。

关键词: 固体推进剂火箭发动机;起飞助推器;助推器分离;气动装置

Abstract: Some numerical simulation and experiments are carried out for studing the workingprocess of pneumatic separation apparatus. The mass flow rate of nonisentropic throttle flow isdiscussed in details. The predicted results of internal ballistic pressure, piston pressure, thrust force,shearing force and separation time are validated by full-scale solid rocket motor experiment, andprovide reliable information for the design and analysis of pneumatic separation apparatus.

Key words: Solid propellant rocket engine;Takeoff booster;Booster separation;Pneumatic

江兴宏,周士喆,汪浩平,门举先. 发射发动机气动分离机构设计与试验[J]. 推进技术, 1997, 18(5): 32-35.