不同攻角约束下空空导弹敏捷转弯过程弹道优化  

Trajectory Optimization for Air-to-Air Missile's Agile Turn with Different Angle of Attack Constraints

作　　者：彭继平[1] 霍鑫[1] 杨宝庆[1] 董继鹏[2] 张金鹏[2] 

机构地区：[1]哈尔滨工业大学控制与仿真中心,哈尔滨150080 [2]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2017年第1期39-44,共6页Aero Weaponry

基　　金：国家自然科学基金项目(61203191;61104193;61174001);航空科学基金项目(20140177006)

摘　　要：为考察攻角约束对直气复合控制的导弹实现越肩发射的影响,首先针对一个反作用喷气系统安装在尾部的敏捷导弹建立了俯仰通道四阶动态模型,然后利用高斯伪谱法获得时间-燃料最优解,并对不同攻角约束下的最优解进行了分析和比较。仿真结果说明攻角约束越严格,敏捷转弯过程的转弯半径越大,时间越长,燃料消耗越多。In order to investigate the influence of the angle of attack constraint on the launch of the missile realized by the direct gas combined control, a four-order dynamic model is established for a missile which reaction-jet control system （RCS） is arranged in the tail. Then by utilizing Gauss pseudospectral method （GPM）, time-fuel optimal solutions are obtained, and the optimal results with different angle of attack constraints are compared and analyzed. The simulation results show that stricter angle of attack con- straint causes larger turning radius, longer time cost and more fuel consumption.

关 键 词：敏捷转弯 攻角约束 高斯伪谱法 弹道优化 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]