弱速度可控下的多飞行器时空协同制导方法研究

Aiming at the operational requirements of saturation strikes on high-value targets in the air during the terminal guidance phase of multi-air-to-air missiles, a multi-missile coordinated combat mode is adopted according to the characteristics of weak speed controllability of the missile flight process in the terminal guidance phase, so as to make up for the lack of maneuverability with the number advantage of missiles. This paper constructs a pulse rocket engine guidance model in three-dimensional space, and studies and designs the space-time coordinated guidance law under speed control constraints based on the sliding mode theory. First, the remaining flight time of the missile is estimated, and the line-of-sight guidance law is designed based on the integral sliding mode and super-helical approaching law according to the characteristics of weak speed controllability in the line-of-sight direction. Secondly, in the lateral plane and normal plane, by introducing angle constraints in the sliding mode surface and designing a fast approaching law to reduce the arrival time of the sliding mode surface, it is ensured that the remaining time of each missile in the three-dimensional space converges to the same before the strike, meeting the requirements of the combat mission. Finally, the guidance law designed in this paper is simulated and verified, which proves the feasibility and effectiveness of the guidance law.