Low-frequency microaccelerations are studied onboard an artificial Earth satellite designed for microgravity investigations in a low, near-circular orbit. The satellite has the shape of a cylinder with two solar-battery panels located in the same plane symmetrically relative to the longitudinal axis of a cylinder. The satellite moves relative to its center of mass in the solar orientation mode: the normal to the plane of solar-battery panels is directed toward the Sun, the angular velocity around this normal is low, and the longitudinal axis makes small oscillations with respect to the plane of the orbit. This mode is implemented with using the system of four controlling reaction wheels. A version of this mode is proposed with a limitation on the accumulation of the total angular momentum of a system of reaction wheels by means of controlling the satellite’s angle of rotation around the normal to the plane of solar-battery panels. The satellite motion relative to the center of mass in the mode of combination of gravitational and solar orientation is considered.
Estimation of Low-Frequency Microaccelerations Onboard an Artificial Earth Satellite in the Solar Orientation Mode
Cosmic Res
Cosmic Research ; 60 , 1 ; 38-50
2022-02-01
13 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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