摘要
用双室串并固体火箭发动机测定由于喷管倒置引起的损失,以及用吸气式流动试验观察燃烧室内囚喷管倒置形成的流动特点。对于用双基药的实验发动机,喷管倒置150°引起的推力损失约1.8%。气流在燃烧室内有很大扰动,在倒置喷管进口附近有涡流和分离现象。
With a special test motor,the loss of thrust caused by inverse nozzle has been measured.It is about 1.8% in the test motor with 150° inverse nozzle angle and double-base propellant.With a suck-type flow test system the flow pattern formed by in- verse nozzle is observed.The flow in chamber is disturbed and there are eddies and air-seperation from wall in the entrance of inverse nozzle.
出处
《固体火箭技术》
EI
CAS
CSCD
1993年第1期6-10,共5页
Journal of Solid Rocket Technology
关键词
火箭发动机
喷管
气流
效率
Solid rocket engine
Nozzle flow
Nozzle efficiency
