| 摘要: |
| 针对小升阻比的火星探测器在火星大气进入过程中所面临的难点问题，对火星大气进入过程制导方法进行了研究。首先在确知探测器弹道系数和升阻比的前提下，考虑过程量及开伞条件约束，优化设计再入飞行的初始再入角。然后考虑非一致终端约束和飞行器的有限机动能力，设计参考轨迹剖面，并确保其能提供足够的裕度来应付各种参数不确定性。最后设计标准轨道法制导律，完成轨迹有效跟踪，并通过六自由度仿真验证了算法的合理性，为火星着陆项目中大气进入段制导方案设计提供参考。 |
| 关键词: 小升阻比探测器 非一致终端约束 初始状态设计 参考轨迹设计 大气进入制导 |
| DOI：10.15982/j.issn.2095-7777.2017.02.013 |
| 分类号:V448.2 |
| 基金项目:国家自然科学基金（61503023、61403030） |
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| On Guidance Algorithm for Martian Atmospheric Entry in Nonconforming Terminal Constraints |
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Guo Minwen, Li Maodeng, Huang Xiangyu, Wang Dayi
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Beijing Institute of Control Engineering, Beijing 100190, China
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| Abstract: |
| A method for Martian atmospheric entry guidance is researched in this paper,regarding the problems faced by Mars exploration vehicle with low lift-to-drag ratios. Firstly,with a certain ballistic coefficient and lift-to-drag ratios,the initial reentry angle is designed considering the process variable constrains and the parachute deployment constrains. Then the reference trajectory is developed for providing the sufficient margin to overcome the parameter uncertainties considering the nonconforming terminal constrains and the low control authority. Finally, the tracking guidance law is presented. The six degree of freedom simulation demonstrates the effectiveness of the approach,which provides references to the Mars exploration project. |
| Key words: vehicles with low lift-to-drag ratios nonconforming terminal constraints the initial state design reference trajectory planning atmospheric entry guidance |
