Attitude Control System Design of 3U CubeSat with Electrodynamic Tether for Post Mission Disposal Demonstration-Reference-Cited by-同舟云学术

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Attitude Control System Design of 3U CubeSat with Electrodynamic Tether for Post Mission Disposal Demonstration

Published:2022-01-09 Issue: Volume: Page:
ISSN:
Container-title:2022 IEEE/SICE International Symposium on System Integration (SII)
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Author:

Shiraishi Naoya,Sato Yuji,Shibuya Yoshihiko,Fujita Shinya,Kuwahara Toshinori,Suzuki Daisuke

Publisher

IEEE

Link

http://xplorestaging.ieee.org/ielx7/9708598/9708599/09708853.pdf?arnumber=9708853

Reference14 articles.

1. Ground Evaluation of the Attitude Control System of 3U-CubeSat IHI-SAT

2. Attitude determination and control system for nadir pointing using magnetorquer and magnetometer

3. A Quaternion Feedback Regulator for Spacecraft Eigenaxis Rotations;wie;Journal of Guidance Control and Dynamics,1989

4. Four Reaction Wheels Management: Algorithm Trade-Off and Tuning Drivers for PROBA-3 Mission;kron;IFAC-PapersOnLine,2014

5. Improvement and verification of satellite dynamics simulator based on flight data analysis

Cited by 1 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. High Accuracy Pointing Control Using a MEMS Mirror for a Micro Space Telescope;2024 IEEE/SICE International Symposium on System Integration (SII);2024-01-08

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