Multi-Stage Boost Aircraft Trajectory Optimization Strategy Based on Hp Adaptive Gauss Pseudo Spectral Method

In this paper, the single-stage boost climbing section for traditional booster-gliding aircraft is changed to multi-stage boost climbing section. In multi-stage boost section, the impulse is determined, but fuel ratio and thrust in all stage cannot be determined. More variables are introduced into the trajectory optimization strategy. On the one hand, the trajectory optimization problem becomes more complicated, and on the other hand, a better solution may be found. For above problems, this paper introduces the hp adaptive Gauss pseudo spectral method. and the multi-stage boost climbing section and the no-power reentry section are optimized at the same time. The simulation analysis shows the superiority of the hp adaptive Gauss pseudo spectral method.