航天器进入制导方法综述综述  

Review of spacecraft entry guidance method

作　　者：胡军[1,2] 李毛毛[1,2] HU Jun;LI Maomao(Beijing Institute of Control Engineering,Beijing 100190,China;Science and Technology on Space Intelligent Control Laboratory,Beijing 100190,China)

机构地区：[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

出　　处：《航空学报》2021年第11期73-88,共16页Acta Aeronautica et Astronautica Sinica

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。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.

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 

分 类 号：V448.235[航空宇航科学与技术—飞行器设计]