| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 5472558 | Acta Astronautica | 2017 | 8 Pages |
Abstract
Attitude motion of a satellite equipped with magnetic control system is considered. System comprises of three magnetorquers and one three-axis magnetometer. Satellite is stabilized in orbital reference frame using PD controller and extended Kalman filter. Three-axis attitude is analyzed numerically with advanced assumptions: inertia tensor uncertainty, disturbances of unknown nature, magnetometer errors are taken into account. Stabilization and determination accuracy dependence on orbit inclination is studied.
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Physical Sciences and Engineering
Engineering
Aerospace Engineering
Authors
D.S. Ivanov, M.Yu. Ovchinnikov, V.I. Penkov, D.S. Roldugin, D.M. Doronin, A.V. Ovchinnikov,