北京航空航天大学学报 ›› 2021, Vol. 47 ›› Issue (2): 398-405.doi: 10.13700/j.bh.1001-5965.2020.0318

• 论文 • 上一篇    下一篇

一种短航程再入解析预测校正制导方法

周亮, 张洪波   

  1. 国防科技大学 空天科学学院, 长沙 410073
  • 收稿日期:2020-07-04 发布日期:2021-03-08
  • 通讯作者: 张洪波 E-mail:zhanghb1304@nudt.edu.cn
  • 作者简介:周亮,男,硕士研究生。主要研究方向:飞船再入动力学;张洪波,男,博士,教授,博士生导师。主要研究方向:飞行动力学与控制。

An analytical predictor-corrector guidance method designed for spacecraft reentry with short range

ZHOU Liang, ZHANG Hongbo   

  1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
  • Received:2020-07-04 Published:2021-03-08

摘要: 针对载人探月飞船高速再入返回问题,提出了一种短航程低过载的再入解析预测校正制导方法。引入大升阻比航天器滑翔式再入的概念,通过设定再入过程中滑翔段轨迹形式,利用轨迹参数描述滑翔段轨迹,推导出预测航程的解析公式。为使终端误差满足要求,通过试位法校正轨迹参数,并换算得到倾侧角制导指令。在偏差条件下进行仿真,实现了飞船2100km任务航程下400~450s内以低于6.5g0的过载再入,结果表明,所提制导方法具有较高的精度和较强的鲁棒性,为载人探月飞船应急快速返回提供了参考思路。

关键词: 探月飞船, 滑翔再入, 应急返回, 解析预测校正, 短航程

Abstract: For the manned lunar return spacecraft reentry problem, an analytical predictor-corrector guidance method for short range reentry is proposed. Firstly, the concept of glide reentryis introduced, which has been studied in the trajectory design of high lift-to-drag ratio vehicle.In order to pre-design the reentry trajectory,a trajectory parameter is chosen to describe the analytic trajectory form,and then the analytical formula to predict the range-to-go is derived. The false position method is used to modify the trajectory parameter and finally converts to the command bank angle,eventually satisfying the terminal precision requirements. The proposed analytical method succeeds in achieving spacecraft reentry with a mission range of 2 100km in 400-450 seconds. During the entire reentry phase, the loads are under a level of 6.5 g0, which is beneficial to manned spacecraft emergency return situation. Simulation has proved that this method has relatively high accuracy and robustness.

Key words: lunar spacecraft, glide reentry, emergency return, analytical predictor-corrector, short range

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