Space Lander Descent Control System Design Considering Fuel Sloshing Under Microgravity

Yuji Tanaka; Mitsuhisa Baba; Masatsugu Otsuki; Kazuhisa Fujita; Takehiro Himeno; Takao Maeda; Masaki Takahashi

doi:10.1109/CDC51059.2022.9992643

Space Lander Descent Control System Design Considering Fuel Sloshing Under Microgravity

Yuji Tanaka, Mitsuhisa Baba, Masatsugu Otsuki, Kazuhisa Fujita, Takehiro Himeno, Takao Maeda, Masaki Takahashi

Department of System Design Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Abstract

This study proposes a descent control system for a space lander with a large amount of fuel, to protect the lander from overturning when landing on microgravity objects. As sloshing is a major problem during descent, it is desirable to construct a control system that considers the sloshing dynamics. We derive a model of the lander considering fuel dynamics, determine the fuel-optimal trajectory for guidance, design a fuel state estimator for navigation, and design a tracking controller. The effectiveness of the proposed method is evaluated using a physical simulator. The proposed method achieves simultaneous stabilization of the lander and fuel, and is shown to be effective in preventing overturning.

Original language	English
Title of host publication	2022 IEEE 61st Conference on Decision and Control, CDC 2022
Publisher	Institute of Electrical and Electronics Engineers Inc.
Pages	3092-3097
Number of pages	6
ISBN (Electronic)	9781665467612
DOIs	https://doi.org/10.1109/CDC51059.2022.9992643
Publication status	Published - 2022
Event	61st IEEE Conference on Decision and Control, CDC 2022 - Cancun, Mexico Duration: 2022 Dec 6 → 2022 Dec 9

Publication series

Name	Proceedings of the IEEE Conference on Decision and Control
Volume	2022-December
ISSN (Print)	0743-1546
ISSN (Electronic)	2576-2370

Conference

Conference	61st IEEE Conference on Decision and Control, CDC 2022
Country/Territory	Mexico
City	Cancun
Period	22/12/6 → 22/12/9

ASJC Scopus subject areas

Control and Systems Engineering
Modelling and Simulation
Control and Optimization

Access to Document

10.1109/CDC51059.2022.9992643

Cite this

Tanaka, Y., Baba, M., Otsuki, M., Fujita, K., Himeno, T., Maeda, T., & Takahashi, M. (2022). Space Lander Descent Control System Design Considering Fuel Sloshing Under Microgravity. In 2022 IEEE 61st Conference on Decision and Control, CDC 2022 (pp. 3092-3097). (Proceedings of the IEEE Conference on Decision and Control; Vol. 2022-December). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/CDC51059.2022.9992643

Space Lander Descent Control System Design Considering Fuel Sloshing Under Microgravity. / Tanaka, Yuji; Baba, Mitsuhisa; Otsuki, Masatsugu et al.
2022 IEEE 61st Conference on Decision and Control, CDC 2022. Institute of Electrical and Electronics Engineers Inc., 2022. p. 3092-3097 (Proceedings of the IEEE Conference on Decision and Control; Vol. 2022-December).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Tanaka, Y, Baba, M, Otsuki, M, Fujita, K, Himeno, T, Maeda, T & Takahashi, M 2022, Space Lander Descent Control System Design Considering Fuel Sloshing Under Microgravity. in 2022 IEEE 61st Conference on Decision and Control, CDC 2022. Proceedings of the IEEE Conference on Decision and Control, vol. 2022-December, Institute of Electrical and Electronics Engineers Inc., pp. 3092-3097, 61st IEEE Conference on Decision and Control, CDC 2022, Cancun, Mexico, 22/12/6. https://doi.org/10.1109/CDC51059.2022.9992643

Tanaka Y, Baba M, Otsuki M, Fujita K, Himeno T, Maeda T et al. Space Lander Descent Control System Design Considering Fuel Sloshing Under Microgravity. In 2022 IEEE 61st Conference on Decision and Control, CDC 2022. Institute of Electrical and Electronics Engineers Inc. 2022. p. 3092-3097. (Proceedings of the IEEE Conference on Decision and Control). doi: 10.1109/CDC51059.2022.9992643

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abstract = "This study proposes a descent control system for a space lander with a large amount of fuel, to protect the lander from overturning when landing on microgravity objects. As sloshing is a major problem during descent, it is desirable to construct a control system that considers the sloshing dynamics. We derive a model of the lander considering fuel dynamics, determine the fuel-optimal trajectory for guidance, design a fuel state estimator for navigation, and design a tracking controller. The effectiveness of the proposed method is evaluated using a physical simulator. The proposed method achieves simultaneous stabilization of the lander and fuel, and is shown to be effective in preventing overturning.",

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AB - This study proposes a descent control system for a space lander with a large amount of fuel, to protect the lander from overturning when landing on microgravity objects. As sloshing is a major problem during descent, it is desirable to construct a control system that considers the sloshing dynamics. We derive a model of the lander considering fuel dynamics, determine the fuel-optimal trajectory for guidance, design a fuel state estimator for navigation, and design a tracking controller. The effectiveness of the proposed method is evaluated using a physical simulator. The proposed method achieves simultaneous stabilization of the lander and fuel, and is shown to be effective in preventing overturning.

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Space Lander Descent Control System Design Considering Fuel Sloshing Under Microgravity

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