| 固推约束下的火星表面起飞上升制导律设计 |
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| 引用本文： | 郭敏文,李琨,黄翔宇,郭延宁.固推约束下的火星表面起飞上升制导律设计[J].宇航学报,2022,43(11):1479-1486. |
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| 作者姓名： | 郭敏文 李琨 黄翔宇 郭延宁 |
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| 作者单位： | 1. 北京控制工程研究所，北京 100094；2. 哈尔滨工业大学航天学院控制科学与工程系，哈尔滨 150001 |
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| 基金项目： | 国家自然科学基金（61973100, 61903032, 61903245） |
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| 摘 要： | 针对受固推约束的火星上升器(MAV)起飞上升问题，设计了上升段、无动力滑行段、入轨段三段式火星表面起飞上升全过程制导策略。首先，根据实际任务需求进行了上升器标称轨迹优化。其次，在上升段引入了阿波罗制导方法，通过类攻角和类侧滑角的控制实现对标称轨迹的跟踪。为减少上升段末端偏差对无动力滑行段与标称轨迹间误差的影响，提出了一种通过调整倾侧角改变上升器所受气动力进而控制飞行轨迹的技术路线，并设计了相应的滑模制导律。另外，兼顾固推发动机的能量管理需求，针对入轨段设计了Lambert制导策略，并参考标称控制量对其进行修正，使得上升器能够在控制能力有限的情况下完成较高精度的入轨。最后，通过典型场景火星表面起飞上升全过程数值仿真验证了所设计策略的有效性和鲁棒性。
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| 关 键 词： | 火星上升器 阿波罗制导 轨迹跟踪制导 滑模制导 Lambert制导 |
| 收稿时间： | 2022-05-24 |
Guidance Design of a Mars Ascent Vehicle with Solid Motor |
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| GUO Minwen,LI Kun,HUANG Xiangyu,GUO Yanning.Guidance Design of a Mars Ascent Vehicle with Solid Motor[J].Journal of Astronautics,2022,43(11):1479-1486. |
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| Authors: | GUO Minwen LI Kun HUANG Xiangyu GUO Yanning |
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| Affiliation: | 1. Beijing Institute of Control Engineering, Beijing 100094, China;
2. Department of Control Science and Engineering, School of Astronautics, Harbin Institute of Technology, Harbin 150001, China |
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| Abstract: | To solve the take off and ascent difficulties of the Mars ascent vehicle (MAV) with solid propulsion constraints, a three phase guidance strategy for the whole process of take off and ascent from the surface of Mars is designed, including ascending, coasting and orbiting phases. Firstly, the nominal trajectory of the MAV is optimized according to the mission requirements. Secondly, the Apollo guidance law is introduced in the ascending phase, and the nominal trajectory is tracked through the control of the angle of attack and the sideslip angle. In order to reduce the influence of the deviation of the end of the ascending phase on the error between the coasting phase and the nominal trajectory, a technical route is proposed to control the flight trajectory by adjusting the bank angle to change the aerodynamic force of the MAV, and the corresponding sliding mode guidance law is designed. In addition, taking into account the energy management requirements of the solid propulsion engine, the Lambert guidance strategy is designed for the orbiting phase, and it is corrected according to the nominal control, so that the MAV can complete the orbiting phase with high precision under the condition of limited control ability. Finally, the effectiveness and robustness of the designed strategy are verified by numerical simulation of the whole process of take off and ascent on the surface of Mars in a typical scenario. |
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| Keywords: | Mars ascent vehicle Apollo guidance Trajectory tracking guidance Sliding mode guidance Lambert guidance |
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