Aiming at designing the guidance law for attacking maneuvering targets with impact angle constraint,a guidance law with impact angle and convergence time control was proposed by using sliding mode control theory,arbitrary convergence time control method and disturbance observer.According to the relative motion relationship of the missile and the target,the state equation of guidance system considering impact angle constraint was constructed,and the target maneuver and modeling errors were regarded as the disturbance.The performance of the arbitrary convergence time control method in the case of interference was analyzed.The sliding mode control and disturbance observer were used to improve the robustness of arbitrary convergence time control method.The method was applied to the design of sliding mode surface and approach law,and the disturbance observer was used to estimate the system disturbance.Based on the sliding mode control theory combined with the state equation of the guidance control system,a sliding mode guidance law with convergence time and impact angle control was derived.Compared with the finite-time convergence guidance law,the convergence time and impact angle of the guidance law can be set directly without the calculation of guidance parameters.By setting up different target maneuvers,different impact angles and convergence times,numerical simulations under various cases were carried out.The results show that the proposed guidance law can control impact angle and convergence time effectively and hit the target accurately.At the same time,the guidance performance is better than that of the existing guidance law.
missileguidance lawimpact angle constraintconvergence time controlsliding mode controlarbitrary time convergence
维普
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