In this article, a three-dimensional cooperative guidance problem for highly maneuvering targets is investigated under the assumption of perfect information. Inspired by the coverage strategy, the cooperative guidance problem is decomposed into one-on-one guidance problems against predictive interception points. To expand the coverage area of each missile, these one-on-one guidance problems are formulated as flight path angle tracking problems, and the optimal error dynamics is extended to derive the guidance law analytically. In addition, through the introduction of the coverage probability model, the dynamic coverage strategy is proposed. The predictive interception points are updated online by maximizing the coverage probability, which aims to achieve successful interception despite variations in target acceleration. Furthermore, a switching strategy of the guidance command is designed for collision avoidance. Simulation results demonstrate that the missile group can cooperatively intercept a highly maneuvering target under the proposed guidance law.

This paper concentrates on developing a missile terminal guidance law against a highly maneuvering target whose maneuvering acceleration is very close to that of the missile or even exceeds the missile normal acceleration in a finite period of time. A new saturated super-twisting algorithm is proposed and applied to the design of missile guidance law. The proposed algorithm has the advantages of simple structure, easy parameter tuning rules and a full utilization of the limit control input. The designed saturated super-twisting sliding mode guidance law is then employed in a missile guidance system. Simulation and its superior performance against strong maneuvering targets is demonstrated.

The design of optimal guidance law for intercepting a near-space hypersonic maneuvering target with bounded inputs is considered. Firstly, a maneuvering model for near-space hypersonic aircraft is given. Then, the aircraft acceleration prediction can be obtained using this model with two neural networks. By using the target acceleration prediction, which is taken into account when calculating the Zero Effort Miss (ZEM), an optimal sliding-mode guidance law is proposed to fulfill the guidance task. An adaptive sliding-mode switch term is designed to deal with actuator saturation and prediction errors. Finally, numerical simulations show that the proposed guidance law can reduce the energy consumption and the terminal acceleration command of the interceptor effectively.