摘要
含翼槽发动机点火燃气填充过程对固体火箭发动机整个点火升压过程有着潜在影响。通过试验,测定在不同点火药量、不同堵片打开方式下,点火燃气填充过程中头部和尾部翼槽内的压强变化情况以及两翼槽内的压强响应时间间隔,并建立了模拟发动机的点火燃气填充过程计算模型,计算结果与实测数据吻合较好。结果发现,堵片的状况影响两翼槽内的压强变化情况,同时两翼槽内的压强响应时间间隔与燃烧室内主流燃气速度有关。
Ignition gas-filling process in the fin-slot region is of the potential influence on the behavior of the overall ignition transient. The pressure and the time interval between the fin-slots of simulating test motor during the gas-filling process was acquired during the test. And then a calculation model of the gas-filling of simulating test motors with fin-slot eonfigurated grain was developed and the calculated results agree with the test data. The result shows that the nozzle closure situation effects the pressurization process in the fin-slots. The time interval of pressurization in the fin-slots is correlated with the initial gas velocity.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2009年第3期258-261,共4页
Journal of Solid Rocket Technology
关键词
模拟固体火箭发动机
点火
翼槽
simulating solid rocket motor
ignition
fin-slots
