Near-minimum fulel guidance law of a lunar landing module

机译：月球着陆模块的近乎最小燃料制导律

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This paper proposes a new guidance law for a lunar landing module. The muidance law is derived from the minimum fuel path slved by the optimal contro theory. The attitude angle of a landing module is tiven to minimize the fuel consumption without iterative calculation. The information of thruster, thrust a nd specific impulse, is not necessary and only the data frm an inertial measurement unit is used. The numerical results sjhow that the guidance aw has a high robustness of not only terminal constraints but also optimality of fuel consumption.

机译：本文为登月舱提出了一种新的制导律。应急规则是从最优控制理论所节省的最小燃料路径中得出的。着陆模块的姿态角旨在在不进行迭代计算的情况下将燃油消耗降至最低。推力和特定冲量的推力器信息不是必需的，仅使用惯性测量单元的数据即可。数值结果表明，制导aw具有很高的鲁棒性，不仅具有终端约束，而且具有最佳的燃油消耗率。

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来源
《4th IFAC(International Federation of Automatic Control) Symposium on Automatic Control in Aerospace 1998 Seoul, Korea, 24-28 August 1998》|1998年|p.373-378|共6页
会议地点 Seoul(KR)
作者
Seiya Ueno; Yoshitake Yamaguchi;
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原文格式 PDF
正文语种 eng
中图分类航空、航天技术的研究与探索;
关键词
Optimal trajectory; Guidance system; Minimization; Flight control; Feedback control; Robustness; Optimality;

机译：最佳轨迹；制导系统；最小化飞行控制；反馈控制；坚固性最优性;

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专利

1. Enhancing the manoeuvring capabilities of a lunar landing module using predictive guidance algorithms [J] . Alexander I. Kozynchenko Acta astronautica . 2010,第3a4期

机译：使用预测制导算法增强月球着陆模块的机动能力
2. An Empirically Derived Erosion Law and Its Application to Lunar Module Landing [J] . CURTIS C MASON, EDWARD F NORDMEYER GSA Bulletin . 1969,第9期

机译：经验推导的侵蚀定律及其在登月舱着陆中的应用
3. Fuel near-optimal guidance law for the powered descending phase of a lunar module [J] . F Zhang, G Duan Proceedings of the Institution of Mechanical Engineers . 2012,第G1期

机译：月球舱动力下降阶段的燃料接近最佳制导律
4. Near-minimum fulel guidance law of a lunar landing module [C] . Seiya Ueno, Yoshitake Yamaguchi International Federation of Automatic Control symposium on automatic control in aerospace . 1999

机译：月球着陆模块的近乎最低燃料指导法
5. Near-optimal feedback guidance for an accurate lunar landing. [D] . Parsley, Joseph. 2012

机译：接近最佳的反馈指导，可准确进行登月。
6. A Distributed Radio Beacon/IMU/Altimeter Integrated Localization Scheme with Uncertain Initial Beacon Locations for Lunar Pinpoint Landing [O] . Rongjun Mu, Yuntian Li, Rubin Luo, 2020

机译：分布式无线电标灯/ IMU / Altimeter集成了本地化方案具有未确定的Lunar Pinpon Lavening的初始信标位置
7. Automatic Landing Guidance Law Design for Unmanned Aerial Vehicles based on Pursuit Guidance Law [O] . 2008

机译：基于追求指导法的无人空中车辆自动着陆指导法设计
8. Full-scale dynamic landing-impact investigation of a prototype lunar module landing gear [R] . Blanchard, U. J. 1969

机译：对原型月球模块起落架进行全面动态着陆 - 撞击调查

Near-minimum fulel guidance law of a lunar landing module

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