摘要
针对涡流阀式变推力发动机,初步建立了设计方法,并设计了长尾管和环形燃气发生器组合的集成式原理样机,开展了考核试验。实验结果表明,设计的原理发动机实现了设计要求;涡流阀式变推力发动机具有存在旋流损失,可实现推力调节比大于压强调节比的工作特性;实验推力调节比达到9∶1。
Design method of the thrust modulation SRM based on vortex valve was established in this paper. The principle prototype which has the tailpipe nozzle and annular gas generator was built to carry out variable thrust test. Experimental results meet design requirements. There exists vortex loss, and the characteristic which the ratio of thrust is more than the ratio of pressure is presented, moreover the ratio of thrust attains 9 in the test.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2011年第6期703-706,共4页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
变推力
涡流阀
原理样机
solid rocket motor
thrust regulation
vortex valve
principle prototype
