Minimum principle penetration guidance for hypersonic morphing vehicle with interior point constraints

When a hypersonic gliding vehicle with a variable-sweep wing attacks a target, considering the possibility of interception by a defense missile during the terminal guidance phase, a guidance method based on the minimum value principle with interior point constraints and a variable-shape switching strategy based on event-triggered mechanisms are designed. A penetration model under half-speed conditions is established. The miss distance of the defense missile is treated as an interior point constraint during the attack missile's flight process. And the optimal acceleration is analyzed and solved using the minimum value principle. Using the event-triggered principle, the optimal vehicle shape, required attack angle, and sideslip angle corresponding to the control quantities of the optimization algorithm are solved. Simulation results show that the guidance method can help the variant vehicle evade interception by the defense missile, and the switcher can achieve the optimal shape switch that enhances the landing speed, demonstrating the effectiveness of the algorithm, which is further verified for robustness through Monte Carlo simulations.