载人飞船上升段轨道的Newton迭代设计法

Newton Iterative Design Approach for Manned Spacecraft Ascent Trajectory

本文对载人飞船上升段轨道的一种工程设计方法进行了探讨。该方法的特点是根据上升段飞行的特征,运用飞行力学原理选定其控制规律的数学模型,然后根据上升段轨道的中间约束条件和终端约束条件,利用Newton迭代法确定模型中的各待定参数。本文给出了该设计方法的流程图,并通过模拟计算论证了该设计方法的可行性。

In this paper, the engineering design approach of manned spacecraft ascent trajectory is described. The mathematical model of control law is selected based on ascent flight property and flight dynamics principle. All the undertermined parameters are determined by using Newton iterative method based on ascent trajectory intermediate and terminal constraint conditions. Its flow chart is given and its correctness is proved by analog computation.