膏体推进剂发动机试验

推进技术 ›› 2004, Vol. 25 ›› Issue (2): 173-175.

膏体推进剂发动机试验

沈铁华,杨敬贤,孙庆曼

上海新力动力设备研究所;上海200125;上海新风化工研究所 ;浙江湖州313002;上海新风化工研究所 ;浙江湖州313002

发布日期:2021-08-15

Experimental investigation of pasty propellant rocket engine

Shanghai Xinli Power Equipment Inst., Shanghai 200125, China;Shanghai Xinfeng Chemical Engineering Inst., Huzhou 313002, China;Shanghai Xinfeng Chemical Engineering Inst., Huzhou 313002, China

Published:2021-08-15

摘要/Abstract

摘要： 通过发动机试验系统,进行了膏体推进剂发动机热格栅点火试验和多次关机启动试验研究。试验发动机带有供料装置,供料压强为7 5MPa,推进剂流量为51g s,喷管喉径为7mm,燃烧室平均压强约1 7MPa,总工作时间大于136s。试验获得了膏体发动机多次点火的特性参数和进行多次关机启动的压强曲线。试验结果表明:选用的膏体推进剂具有很好的热格栅点火性能,点火参数分布较均匀;膏体发动机具有良好的能量可控性。

关键词: 触变推进剂火箭发动机;胶凝推进剂;再点火;点火试验;启动试验

Abstract: The pasty propellant rocket engine ignition of the heat grid and multi-stopping/starting have been tested. Multi-ignition characteristic parameter and multi-stopping / starting pressure curve of pasty rocket engine are obtained. Test result shows that tested pasty propellant has good ignition performance of the heat grid and good ignition parameter which distributes uniformly. Pasty rocket engine’ energy can be controlled.

Key words: Thixotropic propellant rocket engine;Gelled propellant;Reignition;Ignition test;Starting test

沈铁华,杨敬贤,孙庆曼. 膏体推进剂发动机试验[J]. 推进技术, 2004, 25(2): 173-175.