整体式固体火箭冲压发动机飞行试验  

Flight test investigation for an integrated ducted rocket

作　　者：顾炎武[1] 

机构地区：[1]北京动力机械研究所,北京100074

出　　处：《推进技术》2008年第1期75-78,共4页Journal of Propulsion Technology

摘　　要：在地面试验基础上进行了整体式固体火箭冲压发动机飞行试验,以验证发动机的工作可靠性和飞行性能。飞行试验结果表明：试飞发动机和试飞器总体设计合理;发动机性能良好;主级在余气系数0.8-2.3范围内能够稳定工作;最大比冲为6.62 kN.s/kg。达到了试验的目的。Flight tests for an integrated ducted rocket were carried out successfully following ground tests in order to investigate the performance of the ducted rocket. The data obtained have shown that the performance of the ducted rocket is satisfactory. The ducted rocket worked well with excess oxidizer coefficient ranging from 0. 8 to 2. 3. Its maximum specific impulse is 6.62 kN · s/kg . It demonstrated that the design for both the engine and vehicle is correct.

关 键 词：整体式火箭冲压发动机 飞行试验 发动机试验 发动机性能参数 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]