Cooperative Guidance for Multi-Missile Interception Against Maneuvering Targets: Predefined-Time-Based Design

A novel cooperative guidance law is proposed in this paper for achieving multi-missile interception against maneuvering targets. We design guidance law based upon the predefined-time-based approach. Specifically, it is comprised of two terms: missile acceleration components along and normal to the (LOS). The term along the LOS is constructed based upon the predefined-time stability theory to guarantee the times-to-go of all missiles tend to be consistent. Furthermore, the term normal to the LOS is designed via a novel predefined-time sliding mode method, so that the LOS angle rates of all missiles reach the origin and the LOS angles of all missiles converges to the desired ones within a predefined time, respectively. Finally, We validate the effectiveness of the designed guidance law through simulation.