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。
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.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1997年第5期32-35,共4页
Journal of Propulsion Technology
关键词
火箭发动机
助推器
分离
气动装置
Solid propellant rocket engine, Takeoff booster, Booster separation, Pneumatic
