摘要
整体式冲压发动机导弹一体化设计,是把导弹与整体式液体冲压发动机作为一个系统,以系统性能最佳为目标,同时优选导弹和发动机的参数,文中以中程超音速飞航导弹为算例,针对整体式冲压发动机的特点,研究了导弹/整体式冲压发动机的一体化设计问题。对总体参数和发动机设计参数在中、低空巡航两种情况下进行优选,使导弹的射程达到了最佳,并分析、探讨了为适应不同巡航高度要求,选择导弹和发动机参数的有关问题。
Integrated design of integral liquid fuel ramjet (ILER) is regarded as a system of the combination of missile and ILFR, which aims at obtaining the optimum performance of the system and optimizing the parameters of both missile and ramjet. In this paper, supersonic cruise missile of medium range is taken as a calculation example. In accordance with the features of integrated ramjet, the integrated design of missile andintegral ramjet are discussed here. Missile configuration and ramjet parameters are optimized and then the maxmum range is obfained based on two typical cases in medium and low height-cruising. Some problems related to choosing missile and ramjet parameters are also discussed and analyzed for application in different cruise heights.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1993年第2期15-21,共7页
Journal of Propulsion Technology
关键词
巡航导弹
设计
火箭发动机
Cruise missile, Integrate rocket ramjet, Design, Parameter optimization
