Terminal hypersonic trajectory modeling and optimization for maneuvering penetration and precision strike

Aimed at the maneuvering penetration and precision strike problem of hypersonic vehicle terminal trajectory, an optimal maneuvering trajectory optimization method considering the dynamic characteristics of intercepting was proposed from the viewpoint of optimal control, so as to obtain the maximum maneuverability of hypersonic vehicles. In this paper, the intercepting missile model was introduced into the model of penetration trajectory optimization, and a constraint was imposed to restrict the intercepting missile to fly according to the proportional guidance law. The trajectories were divided into phases according to the different missions and trajectory characteristics of the belligerents. The penetration performance index and the precision strike performance index are put forward according to the task and characteristics of each phase, and by the weighting function the independent and contradictory performance indicators are unified. Thus a multi-object, multi-phase and multi-constrained maneuvering penetration trajectory optimization model was established. And multiphase Radau pseudospectral method (MRPM) was used to solve the problem. Due to the initial sensitivity and narrow feasible region of the problem, a series of trajectory optimization strategies were proposed to improve the convergence rate and the precision of the solution. Finally, the optimal maneuvering trajectory was obtained, and the optimality of the solution was verified based on the principle of costate mapping. The results show that the method can give full play to the maneuverability of the hypersonic vehicle, and obtain the penetration trajectory which satisfies the terminal accuracy. Compared with the existing method, the miss distance is increased by 1-2 orders of magnitude. Sensitivity analysis shows that the trajectory is insensitive to the launch time of the interceptor.