Missile guidance law with impact angle constraint and acceleration saturation

Abstract

Based on backstepping control method, a nonlinear adaptive guidance law for missile to intercept large maneuvering target with impact angle constraint and acceleration saturation is presented in this paper. In the presence of acceleration saturation, the guidance law insures that the line-of-sight (LOS) angle converges to the desired angle and LOS angular rate asymptotical converges to zero. To deal with the acceleration of target which is seen as disturbance of the guidance system and improve the performance of the guidance system, an adaptive control technique is adopted to estimate the upper bound of the disturbance. To handle acceleration saturation of missile, an auxiliary system is constructed whose state is used for guidance law design and stability analysis. Moreover, based on Lyapunov stability theory, a detailed stability analysis of the resulting guidance system is carried out. Finally, the simulation comparison results are provided to illustrate the effectiveness of the proposed guidance law.