摘要

A new multi-constraint guidance law of explicit form used in the descending period of the air-launched cruise missiles (ALCM) is proposed in this paper. This guidance law can satisfy the requirements on terminal height, velocity, flight-path angle, angle of attack and the time derivative of the normal acceleration. Firstly, an optimal problem is posed with these requirements, where the time derivative of the normal acceleration is used as control. Then we make this problem analytically solvable by reasonably linearizing the equations of motion. By conducting the trajectory simulations with different launch altitudes while considering the aerodynamic dispersions, the feasibility and robustness of the guidance law is verified.