Publication:
Attitude Determination for NPS Three-Axis Spacecraft Simulator

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Authors
Kim, J.-W.
Cristi, R.
Agrawal, B.N.
Subjects
Advisors
Date of Issue
2004
Date
August, 2004
Publisher
Language
Abstract
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.
Type
Description
The article of record as published may be found at http://dx.doi.org/10.2514/6.2004-5386
Series/Report No
Department
Department of Mechanical and Aerospace Engineering
Identifiers
NPS Report Number
Sponsors
Funder
Format
Citation
presented at the 2004 AIAA/AAS Astrodynamics Specialist Conference and Exhibit, Providence, RI, August, 2004, AIAA-21287.
Distribution Statement
Rights
This 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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