主-从式多弹头协同攻击建模及输出一致性

随着反导系统拦截概率与拦截效率越来越高,单枚弹道导弹突破反导系统实现打击任务的概率在逐渐降低,多弹道导弹协同攻击应运而生.自由飞行段的多弹道导弹易于实现协同攻击,导弹在此阶段也称为弹头.为解决多弹道导弹自由飞行段多弹头协同攻击的建模及输出一致性问题,考虑多弹头协同攻击要求及特点,首先建立了多弹头自由飞行段三维空间运动非线性状态空间模型,详细分析了该模型的特点以及模型非线性动态对多弹头协同攻击带来的挑战.针对上述挑战,为实现主-从式多弹头协同攻击体系的输出一致性,应用输入输出反馈线性化控制方法,设计了一类从弹弹头协同加速度指令信号,并通过详实的数值仿真验证所设计指令信号的有效性.仿真结果表明,沿主弹弹头发射坐标系各轴向均实现了给定性能要求下的主-从式多弹头协同攻击体系的输出一致性,主弹弹头速度变化越快、收敛系数的实部模值越大,速度跟踪误差收敛速度便越快,速度跟踪误差也越小,输出一致性的性能也更好.

Modeling and output consensus of cooperative attack for leader-followers multiple warheads

As the interception probability and interception efficiency of anti-missile system consistently increased, the probability for a single ballistic missile breaking the anti-missile system to achieve the attack task is gradually decreasing, thereafter comes the strategy multi-ballistic missile cooperative attack. The cooperative attack of multi-ballistic missile during the free flight segment is easy to achieve, with the missile called warhead at this stage. To solve the problem of modeling and output consensus of cooperative attack for multiple warheads(hereinafter referred to as multi-warhead)in the free-flight segment of ballistic missile, a three-dimension nonlinear state space model for multi-warhead space motion in the free-flight segment is established. On this basis, the characteristic of the model and the challenges brought by the nonlinear dynamic of the model to the cooperative attack of multi-warhead receives detailed analysis. To deal with the above challenges and realize the output consensus of the cooperative attack architecture for leader-followers multi-warhead, a kind of cooperative acceleration command signal is designed for the followers by using the input-output feedback linearization control theory, and the effectiveness of the designed command signal is verified by detailed numerical simulation. The result of simulation shows that the output consensus of cooperative attack architecture for leader-followers multi-warhead is realized under the given performance requirement on all axes of the leader''s launch coordinate system. The faster the velocity of leader varies and the larger the real part modulus value of convergence coefficient is, the faster the convergence speed of velocity tracking error and the smaller the velocity tracking error will be. Finally, the performance of the output consensus will be even better.