Air-to-Ground Missile Handover Position Optimization and Terminal Guidance Design

This paper focuses on the handover position and terminal guidance design of a certain type of short-range axisymmetric air-to-ground missile. To guide the missile to the vicinity of the target area for target search, a performance-based evaluation function is established to comprehensively optimize the handover position. To meet the constraints of terminal impact angle, a comparative analysis is conducted between the sliding mode guidance law and the over-gravity compensation proportional guidance law, as well as the ballistic shaping guidance law. The results show that the sliding mode guidance law is more efficient in the context of this paper. Finally, a two-loop autopilot is established to obtain a complete guidance control system for simulation, and the effectiveness of the scheme is verified using Monte Carlo method simulation.