摘要
为使空空导弹在较宽的空域范围内获得优化的综合性能,提出了以导弹综合特性为目标函数来优化固体火箭冲压发动机设计参数的思路,以空空导弹在飞行高度分别为5,10km和15km的飞行距离和飞行速度的综合性能参数为目标函数,建立了固体火箭冲压发动机设计参数优化模型,利用遗传算法进行了固体火箭冲压发动机设计参数的优化.优化的结果表明:当参数选择适当时,采用非壅塞固体火箭冲压发动机的空空导弹在较宽的工作包线内也能够具有优秀的飞行性能,在高度为5,10km和15km时,空空导弹的飞行距离分别达到了62.9,89.2km和133.1km,空空导弹的平均飞行速度也得到了提高.
To obtain high overall performance of airborne missile in a broad flight envelope,the method with overall performance of airborne missile as object of optimization and the design parameters of unchoked air-ducted rocket（ADR）as variables had been proposed.The integrated performance of the airborne missile at height of 5km,10 km and 15 km was used as the objective function to establish the optimization model for ADR design.Genetic algorithms（GA）was introduced to obtain optimized ADR parameters.Numerical results show that reasonable performance can be achieved for the airborne airborne missile with unchoked ADR as the power system in a broad flight envelope.At the height of 5km,10 km and 15 km,the corresponding airborne missile range are 62.9km,89.2km and 133.1km.At the same time,the average flight velocity has been increased.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2015年第8期2018-2024,共7页
Journal of Aerospace Power
