摘要
综合导弹和整体式冲压发动机的相互影响，从导弹总体设计的观点出发，对整体式液体冲压发动机的性能进行了研究，分析讨论了设计参数对发动机性能的影响及发动机设计的特殊问题。本方法可用于导弹总体方案设计阶段参数的选择和性能分析。
In China's development of the highly promising integrated liquid ramjet engine, its dynamic propertics need to be quite well understood. The authors' research results are presented in graphical form.Thrust coefficient CR and specific impulse is arc given graphically under various conditions in Figs.2, 3 and 4. CR and is arc dependent on altitude H, excess air coefficient a, and combustion efficiency n.' etc.In Fig.2, α=2 and ηr=0.95. In Fig.3, H=1000 m and α= 1.5. In Fig.4, H=1000 m and ηr = 0.95. Figs.2,3 and 4 show the variations of CR and Is with M for different values of H, α and ηr In addition to the results gvien in Figs 2,3 and 4, the authors find that:(1) Engine performance can be improved when total pressure recovery coefficient is increased.(2) When cruising Mach number for optimal performance is determined from figures like Figs.2,3and 4, a suitable nozzle expansion rate must be chosen to ensure optimal performance.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
1995年第1期125-128,共4页
Journal of Northwestern Polytechnical University
关键词
动力特性
发动机
液体冲压发动机
导弹
设计
integrated ramjet engine, dynamic property, optimal performance
