摘要
在分析了固体火箭冲压发动机的高度特性、壅塞式和非壅塞式固体火箭冲压发动机性能调节特性的基础上， 提出了燃气流量可以调节的燃气发生器， 尤其是非壅塞式固体火箭冲压发动机对贫氧推进剂的特殊要求。分析结果表明： 非壅塞式固体火箭冲压发动机要求贫氧推进剂具有高的燃速压强指数、低的可燃极限和足够好的燃烧稳定性。探讨了贫氧推进剂性能调节的途径。
On the basis of analysis of the height characteristics and the specific impulse characteristics of both choked and unchoked ram rocket, the requirements of the fuel rich propellant for adjustable fuel mass flow gas generator, especially for the unchoked gas generator were proposed. The fuel rich propellant used for the unchoked ram rocket should has high burning rate exponent, appropriate burning rate, low flammability limit and steady combustion properties. The methodology to modify the performance of the fuel rich propellant was studied.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1999年第5期95-98,共4页
Journal of Propulsion Technology
关键词
火箭冲压发动机
固体冲压发动机
贫氧
推进剂
Integral rocket ramjet,Ducted rocket engine,Flow control,Oxygen poor fuel rich propellant
