Analysis of Morphing Modes of Hypersonic Morphing Aircraft and Multiobjective Trajectory Optimization

Abstract

Aiming at improving the range of wing-body combination aircraft at hypersonic flow conditions and exploring the application of morphing technology in hypersonic aircraft, morphing aircrafts with different morphing modes have been proposed. The aerodynamic characteristics and wing efficiency of morphing aircraft with different morphing modes have been studied for a further application. In order to verify the significance of morphing technology on the trajectory, the trajectory of the glide phase has been optimized through multiobjective optimization method. Through a 3 degree-of-freedom dynamic model and a heat flux model, the range of glide trajectory and the total heat of the leading edge of the wing are calculated and selected as optimization objectives in the multiobjective optimization problem. The optimization variables include the Mach numbers when the aircraft is morphing (morphing timing) and the angle of attack of different phases. Based on the multiobjective evolutionary algorithm based on decomposition, the multiobjective trajectory optimization problem is solved and a uniform Pareto Front is obtained, and through the analysis of typical solutions, it can be seen that a compromise is made to balance the two objectives. Through the comparison of morphing and non-morphing aircraft, morphing aircraft can fly further with a smaller total heat of the leading edge of the wing. Also, it seems that the variable sweep wing morphing mode has a better overall performance. The result in this paper is a verification of the application prospects of the morphing technology under hypersonic environment, which will provide a reference for further application of morphing technology in hypersonic aircraft.