軌道姿勢制御装置、人工衛星、軌道姿勢制御方法及びプログラム

Japanese Patent JP7204987

B2

In an orbital attitude control device (1150), an ideal thrust axis direction calculator (1505) calculates an ideal thrust axis direction based on information of a predetermined orbit, an ideal attitude calculator (1506) calculates an ideal attitude of the satellite based on the ideal thrust axis direction and a solar direction, and a control torque calculator (1510) calculates a control torque to control the attitude control actuator based on an estimation attitude of the satellite, the solar direction, a preset drive constraint, and the ideal attitude. The control torque calculator (1510) calculates an ideal control torque that makes the attitude of the satellite follow the ideal attitude and a torque restraint plane in which the solar direction is orthogonal to a rotational axis of the solar array panel, defines an evaluation function obtained by weighting a distance from the ideal control torque and a distance from the torque restraint plane and then summing the weighted distances, and calculates the control torque that allows the drive constraint to be satisfied and the evaluation function to be minimized.

Kenji Kitamura
Takeya Shima
Katsuhiko Yamada

JP2022502650A

January 16, 2023

February 26, 2020

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Mitsubishi Electric Corporation

B64G1/24; B64G1/26; B64G1/40

JP2017137040A
JP2000247298A

WO2016111317A1
US20150001345
US7464898

Kimura Mitsuru
Koji Yashima
Hideki Mie
Yukio Watanabe
Ryohei Miyawaki
Shiro Tatsutake

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