Terminal trajectory optimization for morphing wing missile with multi-constraints

This paper investigates a fast and reliable method to optimize the terminal trajectory with multi-constraints for morphing-wing missile to enlarge the maximum final velocity, and ascertains the performance on increasing the terminal velocity of morphing wing missile in comparison with fixed wing missile. The effect of morphing-wing missile with flying and varying parameters on aerodynamic characteristics is analyzed under the steady and unsteady condition respectively, and trajectory optimization model for maximum final velocity is established with multi-constraints. Then a solving strategy for trajectory optimization is proposed and described in detail based on hp-adaptive pseudo-spectral method. Finally, the terminal trajectory optimization simulation is performed with the presented optimal method. The simulation results suggest that it is feasible for the given morphing wing missile via changing the swept angle to increase final velocity by 13.8% over with the fixed wing missile, the effectiveness of the proposed method is confirmed on solving the optimal control problem with multiple constraints.