升力式再入弹道拉起段近似解研究

Study on approximate solution of lift reentry trajectory pull-up phase

针对现有方法在求解升力式再入弹道拉起段时的不足,考虑再入平面动力学模型中的引力项、离心力项的影响,推导了拉起段的速度、高度、航程变化量的近似解。通过与数值仿真校验和现有方法的对比,验证了近似解在估计精度上的改善效果。研究结果可用于升力式再入飞行器的设计评估与制导算法的设计。

The approximate solutions of the pull-up phase trajectories for the reentry or boost-glide vehicles are studied in this paper. To be more accurate,the gravity and centrifugal terms are both included when the solutions of height,velocity,range are derived from the planar entry equations. By comparing to numerical solution and the present method it is confirmed that it can improve the precision of estimation. The solutions can be used in performace evaluation and guidance design of lift reentry vehicles.