多高超声速导弹协同末制导律及可行初始位置域研究

针对多高超声速导弹以指定落角对目标进行饱和攻击的问题,提出一种具有攻击角度和攻击时间约束的末制导律,并基于此对导弹的末制导可行初始位置域进行研究。建立三维空间导弹运动模型,分别通过纵向通道和侧向通道制导指令实现落角和攻击时间控制,构成三维协同末制导律。考虑导弹过载和末速约束,采用上述制导律,以导弹末制导初始位置的坐标为设计变量,以实际攻击时间与理想攻击时间差为性能指标函数,建立并求解优化模型,得到导弹一维及二维可行末制导初始位置域。仿真结果表明:该三维协同制导律可使多导弹在同一指定时间以指定落角命中目标; 该位置域求解方法可求得给定约束条件下的各导弹末制导可行位置域。

Research on Cooperative Terminal Guidance Law and FeasibleInitial Position Domain for Multi-hypersonic Missiles

Aiming at the problem that multi-hypersonic missiles can realize saturation attack to the target with a specified impact angle,a terminal guidance law with constraints of impact angle and impact time was proposed,and the feasible initial position domain of terminal guidance of missiles was studied. A relative motion model of missiles in the three-dimensional space was established. The vertical and lateral guidance command was used to realize the impact angle control and the impact time control respectively,and a three-dimensional cooperative terminal guidance law was formed. Adopting the law,the constraints of final velocity and available overload of missiles were considered,and the initial position of terminal guidance of missiles was taken as a design variable,and the difference between the actual impact time and the ideal impact time was taken as the performance index function,and an optimization model was established. The model was solved to obtain one-dimensional and two-dimensional feasible initial position domains of terminal guidance of missiles. Simulation results show that the three-dimensional cooperative guidance law can make multiple-missiles hit the target at the designated impact time with the required impact angle,and the position domain solving-method can be used to obtain the feasible initial position domains for each missile under given constraints.