摘要
针对宽马赫数固体火箭冲压发动机用二元进气道设计开展研究,提出了一种从低维到高维的逐步优化设计方法,即首先经过若干合理假设建立一维计算模型,利用遗传算法得到一个以总压恢复系数最大为目标的一维优化结果;在二维和三维设计中,选取关键影响因素进行详细分析以不断改善一维优化结果。最终给出一套完整、高效的亚燃冲压二元进气道设计方法。设计过程验证了一维计算模型和关键影响因素选取的合理性,给出了进气道性能随这些关键影响因素的变化规律。
In this paper the design of two-dimension solid-ramjet inlet operating over a wide range of flight Mach number is investigated. A step-by-step optimum design method from one-dimension to three-dimension is establishedo In the method an one-dimension computer model is estabhshed with several proper assumptions, and an one-dimension optimum result is obtained by adopting genetic algorithms and selecting total pressure recovery coefficient as performance objective function. Then, during the two-dimension and three-dimension designs, the key influencing factors are selected and analysised carefully, so as to improve the one - dimension optimum resuh. So a complete and efficient two-dimension ramjet inlet optimum design method is illustrated. The design process not only verifies the rationality of the one-dimension computer model and the selection of key influencing factors, but also gives many variation laws with these key influencing factors.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2008年第5期1577-1582,共6页
Journal of Astronautics
关键词
冲压发动机
二元进气道
优化设计
遗传算法
数值模拟
Ramjet
Two-dimension inlet
Optimum design
Genetic algorithms
Numerical simulation
