论文部分内容阅读
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.
In order to optimize the performance of air-to-air missile over a wide airspace, the idea of optimizing the design parameters of the solid rocket ramjet based on the missile’s comprehensive characteristics is proposed. Taking the air-to-air missile at 5, 10km and 15km And the overall performance parameters of flight speed and flight speed as objective function, the design parameters optimization model of solid rocket ramjet engine is established, and the design parameters of solid rocket ramjet engine are optimized by using genetic algorithm.The optimization results show that when the parameters are selected properly, Air-to-air missiles with non-constricted solid rocket ramjet engines also have excellent flight performance over a wide range of working envelopes, with air-to-air missiles flying at distances of 62.9, 89.2 km and 133.1 at altitudes of 5, 10 and 15 km km, the average flight speed of air-to-air missiles has also been raised.