航天器进入制导方法综述

doi:10.7527/S1000-6893.2021.25048

综述

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航天器进入制导方法综述

胡军^1,2, 李毛毛^1,2

1. 北京控制工程研究所, 北京 100190;
2. 空间智能控制技术重点实验室, 北京 100190

收稿日期:2020-12-02 修回日期:2021-01-06 发布日期:2021-04-21
通讯作者: 胡军 E-mail:hujunbice@126.com

Review of spacecraft entry guidance method

HU Jun^1,2, LI Maomao^1,2

1. Beijing Institute of Control Engineering, Beijing 100190, China;
2. Science and Technology on Space Intelligent Control Laboratory, Beijing 100190, China

Received:2020-12-02 Revised:2021-01-06 Published:2021-04-21

摘要/Abstract

摘要： 航天器制导系统的设计至关重要，直接关乎航天器能否安全返回地球或着陆行星表面指定区域。在给出航天器进入动力学模型的基础上，首先分析了进入制导问题建立及难点，然后综述了航天器进入制导方法的研究现状，分析了各类进入制导方法的优缺点。作为统一或通用方法，介绍了实际应用于中国航天工程再入返回的自适应预测校正制导方法。面向未来发展亟待解决的问题，在线快速规划可行轨迹的重要性凸显，分析了在线轨迹规划方法所需要解决的问题以及今后进入制导方法的发展方向。

关键词: 航天器, 进入制导方法, 预测校正, 轨迹规划, 通用制导方法

Abstract: The design of guidance system is essential for safe reentry or landing of the spacecraft at the specified region. In this paper, the spacecraft entry models are first summarized. Then, the establishment and difficulty of entry guidance are analyzed, and the research status of spacecraft entry guidance methods is reviewed. The advantages and disadvantages of various entry guidance methods are analyzed. The adaptive predictor-corrector guidance method which has been applied to reentry of China's spacecraft is introduced, which can be used as a general guidance method. Facing the urgent problems needed to be solved for the future development, the importance of fast online feasible trajectories planning is highlighted. The problems needed to be solved for online trajectory planning are analyzed, and possible development directions of spacecraft entry guidance method are also given.

Key words: spacecraft, entry guidance method, predictor-corrector, trajectory planning, general guidance method

中图分类号:

V448.235

胡军, 李毛毛. 航天器进入制导方法综述[J]. 航空学报, 2021, 42(11): 525048-525048.

HU Jun, LI Maomao. Review of spacecraft entry guidance method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(11): 525048-525048.

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航天器进入制导方法综述

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