Attitude Determination for NPS Three-Axis Spacecraft Simulator
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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.
The article of record as published may be found at http://dx.doi.org/10.2514/6.2004-5386
RightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, is not copyrighted in the U.S.
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