This paper considers the simultaneous attack of a stationary target by multiple missiles. A novel fixed-time distributed guidance law based on the proportional navigation (PN) guidance law is designed by integrating a consistent control technique into the guidance strategy. This guarantees that the time-to-go of the missile becomes consistent. The guidance law adopts a discrete design, and a compensation item driven by normal acceleration is added to tangential acceleration. This eliminates the potential singularity problem when the heading angle is zero before the consistency is obtained, and thus the multiple missile system still converges in fixed time. In addition, the proposed guidance law can be applied to both undirected and directed graphs. Furthermore, two improved guidance laws are proposed to improve the robustness of the system against adverse effects caused by input delays and topology switching failures and to provide a theoretical proof. Finally, a simulation is used to verify the performance of the distributed guidance law and its robustness against the above failures.

本文考虑多枚导弹同时攻击一个静止目标。通过将一致性控制技术集成到制导策略中，设计了一种基于比例导航（PN）制导律的新型固定时间分布式制导律。这保证了导弹的起飞时间变得一致。制导律采用离散设计，在切向加速度上增加了法向加速度驱动的补偿项。这消除了在获得一致性之前航向角为零时潜在的奇异问题，因此多导弹系统仍然在固定时间内收敛。此外，所提出的指导律可以应用于无向图和有向图。此外，提出了两种改进的制导律，以提高系统对输入延迟和拓扑切换故障引起的不利影响的鲁棒性，并提供理论证明。最后，通过仿真验证分布式制导律的性能及其对上述故障的鲁棒性。