摘要
通过冷吹风试验的方法对多单元直排圆转方塞式喷管的高度补偿特性进行了研究。试验表明,多单元直排圆转方塞式喷管具有一定的高度补偿效益,但其性能低于理论塞式喷管。其性能损失主要是由于塞锥截短、圆转方单元推力室以及塞锥底部不封闭等原因造成的。
A cold flow test to the linear clustered plug nozzle with round-to-square thruster units is carried out to investigate altitude compensation characters of the nozzle. The test results show that plug nozzle is capable of altitude compensation, though its performance is lower than that of theoretic plug nozzle. The loss of performance is mainly caused by the cut-off plug, the round-to-square thruster chamber and the opened base of plug.
出处
《导弹与航天运载技术》
北大核心
2006年第2期32-36,共5页
Missiles and Space Vehicles
基金
国家863-2资助项目
项目编号为2004AA722020
关键词
推力室
塞式喷管
冷流试验
Thrust chamber
Plug nozzle
Cold flow test
