冲压发动机导弹爬升段和巡航段轨迹优化  

Ascent and cruise trajectory optimization for ramjet powered missile

作　　者：王治宇 李高春 韩永恒 徐伯起 夏成 WANG Zhiyu;LI Gaochun;HAN Yongheng;XU Boqi;XIA Cheng(College of Coast Defense Arm,Naval Aviation University,Yantai Shandong 264000,China;Military Representative Bureau of Naval Armament Department in Beijing Region,the Chinese People’s Liberation Amry,Beijing 100071,China)

机构地区：[1]海军航空大学岸防兵学院,山东烟台264000 [2]中国人民解放军海军装备部驻北京地区军事代表局,北京100071

出　　处：《航空动力学报》2021年第5期1103-1112,共10页Journal of Aerospace Power

摘　　要：为了研究冲压发动机导弹爬升段和高空巡航段的燃油最优弹道,提高射程,提出了较为通用的一体化优化设计方法。研究了冲压发动机、导弹气动力与弹道之间的耦合特性,建立了导弹动力学模型,将弹道的最优控制问题转化为参数优化问题。为求解该参数优化问题,针对传统粒子群(PSO)算法求解优化问题时存在的早熟收敛的不足,提出了一种算法结构,改善粒子群算法的性能,求其最优解。数值结果表明:改进的算法相对其他几种粒子群算法具备更优秀的性能。所优化弹道相比导弹试验数据,以飞行时间增加3.3%为代价,节约了4.46%燃油。多组高弹道的仿真结果表明,巡航高度应不超过动压边界前提下,高弹道巡航有利于节约燃油,增加导弹射程。In order to study the optimal trajectory of a ramjet missile’s climbing section and high altitude cruise section, save fuel and increase the range, an integrated optimization design method was proposed. The coupling characteristics between ramjet, missile aerodynamic force and trajectory were studied, and the missile dynamics model was established to transform the optimal control problem of trajectory into parameter optimization problem. To improve the performance of the traditional particle swarm optimization(PSO) algorithm, a new algorithm structure was proposed to solve the optimization problem. Numerical results showed that the improved algorithm had better performance than other PSO algorithms. Compared with the missile test data, the optimized one saved 4.46% fuel at 3.3% increased in flight time. The simulation results of multiple sets of high-ballistics show that high-ballistic cruise can save fuel and increase missile range, but the cruise height should be guaranteed not to exceed the boundary of dynamic pressure constraint.

关 键 词：弹道优化 粒子群(PSO)算法 冲压发动机 最小油耗 一体化优化设计 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]