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R. Funase, E. Takei, Yuya Nakamura, Masaki Nagai, A. Enokuchi, C. Yuliang, K. Nakada, Y. Nojiri, F. Sasaki, Tsukasa Funane, Takeshi Eishima, S. Nakasuka (2007)
Technology demonstration on University of Tokyo's pico-satellite “XI-V” and its effective operation result using ground station networkActa Astronautica, 61
T. Inamori, N. Sako, S. Nakasuka (2011)
Magnetic dipole moment estimation and compensation for an accurate attitude control in nano-satellite missions ☆Acta Astronautica, 68
T. Inamori, S. Nakasuka, N. Sako (2009)
In-orbit magnetic disturbance estimation and compensation using UKF in nano-satellite mission
N. Sako, Y. Hatsutori, Takashi Tanaka, T. Inamori, S. Nakasuka (2007)
Nano-JASMINE: A Small Infrared Astrometry Satellite
Eric Caillibot, C. Grant, D. Kekez, R. Zee (2005)
Formation Flying Demonstration Missions Enabled by CanX Nanosatellite Technology
K. Carroll, S. Rucinski, R. Zee (2004)
Arc-Minute Nanosatellite Attitude Control: Enabling Technology for the BRITE Stellar Photometry Mission
R. Lancaster, C. Underwood (2000)
The SNAP-1 Machine Vision System
Stuart Eagleson, K. Sarda, Stephen Mauthe, T. Tuli, R. Zee (2006)
Adaptable, Multi-Mission Design of CanX Nanosatellites
S. Nakasuka, N. Sako, H. Sahara, Yuya Nakamura, Takashi Eishima, Mitsuhito Komatsu (2010)
Evolution from education to practical use in University of Tokyo's nano-satellite activitiesActa Astronautica, 66
Purpose – This paper aims to present an attitude determination and control system for a nano‐astrometry satellite which requires precise angular rate control. Focus of the research is methods to achieve the requirement. Design/methodology/approach – In order to obtain astrometry data, the satellite attitude should be controlled to an accuracy of 0.05°. Furthermore, attitude spin rate must be controlled to an accuracy of 4×10 −7 rad/s during observation. In this paper the following unique ideas to achieve these requirements are introduced: magnetic disturbance compensation and rate estimation using star blurred images. Findings – This paper presents the feasibility of a high accurate attitude control system in nano‐ and micro‐satellite missions. Practical implications – This paper presents a possibility of the application of nano‐satellites to remote‐sensing and astronomy mission, which requires accurate attitude control. Originality/value – Originalities of the paper are the methods to achieve the high accurate attitude control: magnetic disturbance compensation and angular rate estimation using star images.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Jul 5, 2011
Keywords: Nano‐ and micro‐satellite; Attitude control; Attitude determination; Astronomy; Satellite; Aerospace
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