This paper presents the attitude determination method for the Bifocal Relay Mirror Spacecraft Simulator. The simulator simulates three-axis motion of a spacecraft and has an optical system emulating a bifocal space telescope. The simulator consists of three control moment gyroscopes, rate gyros, two-axis analog sun sensor, and two inclinometers. The five-foot diameter platform is supported on a spherical air bearing to offer a low-torque environment. This paper demonstrates two attitude determination methods employing the measurements from a two-axis analog IR sensor, two inclinometers, and a triaxial gyroscope. The first method implements the conventional Kalman filter algorithm. The second method uses a nonlinear observer derived from the Lyapunov s direct method. Analytical and experimental results are presented to validate the proposed algorithm.
Attitude Determination for NPS Three-Axis Spacecraft Simulator
2004
12 pages
Report
No indication
English
AIAA-2004-5386 Attitude Determination for NPS Three-Axis Spacecraft Simulator
British Library Conference Proceedings | 2004
|Spacecraft spin axis attitude determination
IEEE | 1992
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