摘要
利用引射火箭试验系统和固体火箭发动机燃气发生器,就不同结构的二次喷管对引射火箭的性能影响开展了试验和数值模拟研究。模拟计算和试验结果表明,二次喷管降低了发动机的引射系数,但改变了燃烧室的压强分布,使其推力特性得以改善。在文中所研究的引射燃烧室结构条件下,存在一个最佳二次喷管出口面积,它能使引射火箭的推力达到最大。
The utilization of rocket ejector is important to structural integration of RBCC, for it may decrease weight and complexity of the motor. Numerical simulation and experimental approaches are adopted in the paper to investigate the influence of secondary nozzle on the performance of rocket ejector. In the theoretical aspect, unstructured meshes are used in 3-D numerical simulation. The results indicate that along with decreasing exit area of secondary nozzle, the bypass ratio decreases, the static pressure in integrated ejector combustor increases. There exists an optimal exit area of secondary nozzle to result in a maximum thrust of rocket ejector in the light of the investigated ejector chamber structure.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2004年第2期108-110,共3页
Journal of Solid Rocket Technology
