基于非线性规划的中近距空空导弹增程弹道设计方法  

Trajectory Design for Extending Range of Medium and Short Range Air-to-air Missiles Based on Non-linear Programming

作　　者：王龙[1] 李斌[1] WANG Long;LI Bin(China Airborne Missile Academy,Henan Luoyang 471000,China)

机构地区：[1]中国空空导弹研究院,河南洛阳471000

出　　处：《弹箭与制导学报》2021年第6期76-81,共6页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：弹道设计是空空导弹的一项关键技术,合理的弹道设计可充分发挥空空导弹的作战性能。针对空空导弹的实际作战需求,以导弹末速为性能指标,以导弹攻角和侧滑角为控制输入,建立了空空导弹弹道设计问题的数学描述。基于伪谱法,对导弹运动状态方程和控制输入进行参数化逼近,将动态优化问题转化为非线性规划问题进行求解,并给出了求解方法。以某型空空导弹为对象进行了仿真验证,仿真结果表明,增程弹道设计方法能够精确计算空空导弹的拦截弹道,且导弹末速显著高于比例导引,可以适用于空空导弹的增程弹道设计。Trajectory design is one of the key technologies of air-to-air missiles,and proper trajecotry can improve the operational performance of air-to-air missiles significantly.Aiming at the actual operational requirement of air-to-air missiles,the mathematical description of trajecotry design problem is established,in which the missile’s terminal velocity is taken as the performance index and the angle of attack and sideslip angle are taken as the control input.Based on the pseudospectral methods,the states equations and control input of missile are approximated by parameterization and then the dynamic optimization problem is solved by nonlinear programming.Finally,simulation experiments are carried out to verify the validity of the trajectory design medthod.The simulation results show that the inerception trajectory of air-to-air missile can be calculated accurately by the proposed approach and the missile’s terminal velocity is higher than that of proportional guidance,thus the proposed approach can be used for extended range trajectory deisgn of air-to-air missile.

关 键 词：伪谱法 空空导弹 增程弹道设计 

分 类 号：TJ762.23[兵器科学与技术—武器系统与运用工程] TJ013.2