Predict Correct Terminal Guidance Algorithm Based on Additional Angle of Attack

This paper introduces a novel multi-constraint terminal guidance algorithm for enhancing the precision control of landing corner velocity during targeted attacks on terminal locations by hypersonic gliders. The proposed algorithm incorporates an additional angle of attack prediction correction to optimize the control process. Building upon a precise angle of attack proportional guidance law, an energy control profile is devised to incorporate an additional line of sight angular rate altitude, thereby generating extra angle of attack and pitch angle maneuver commands. The online prediction of the final velocity is achieved through a numerical integration algorithm, and the Newton iteration method is employed to solve the energy control profile parameters for real-time correction of additional maneuvering instructions. Monte Carlo simulations demonstrate the algorithm's effectiveness in mitigating final velocity dispersion issues arising from initial position and velocity deviations, as well as uncertainties in projectile parameters. The algorithm exhibits strong robustness and engineering feasibility.