Integrated multiple objectives optimal robust guidance with angular constraint

In order to fulfill high precision guidance with terminal angular constraint for missile under environment and model uncertainties and other multiple constraints, a guidance approach was proposed. Robust guidance law design and guidance law parameters optimization were solved separately as two sub-problems. Geometry relationship between missile and target was derived and robust guidance law based on L2 gain performance theory was presented. The guidance law parameters were optimized using genetic algorithm with the weighted square sum of terminal angular error, position error and control variables as the optimal performance function. Simulation results show that the proposed approach is an effective way to design guidance law with terminal angular constraint while satisfying multiple objectives.