一种针对直接入轨飞行器的主动段轨道快速实现方案

A Rapid Trajectory Implementation Method for Directly Injecting Rocket

在直接入轨飞行器允许较宽交班范围的情况下,采用离线优化设计轨道保障参数、射前根据发射点和射向对程序角进行修正的方案,将传统的单发设计转化为适应性强的通用设计,减少了轨道设计计算量,缩短了飞行器的射前准备时间。仿真结果表明,所提出的轨道快速实现方法对点位和射向具有较强的适应性,能够有效减小交班点的偏差范围,同时相比优化设计的轨道,终端速度差异较小,在具有一定优化指标的同时可保证在线实施。

A rapid trajectory implementation method is proposed for directly injecting rocket.In case of directly injecting rocket which allows coarse intersection disperse,trajectory can be designed by off-line optimization to satisfy constrains,and flight program angle can be corrected based on real launch point and launching direction.This improves traditional single launch design into strong robust universal design,and not only effectively reduces the computational cost,but also reduces launch preparation time.Simulation results demonstrate that the proposed method is quite flexible for launch point and launching direction,and can effectively reduce intersection deviation while maintaining a terminal speed close to the optimization result,which provides an on-board sub-optimization solution.