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Proceedings Paper

Line-of-sight pointing accuracy/stability analysis and computer simulation for small spacecraft
Author(s): Marcelo C. Algrain; Richard M. Powers
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Paper Abstract

This paper presents a case study where a comprehensive computer simulation is developed to determine the driving factors contributing to spacecraft pointing accuracy and stability. The simulation is implemented using XMATH/SystemBuild software from Integrated Systems, Inc. The paper is written in a tutorial manner and models for major system components are described. Among them are spacecraft bus, attitude controller, reaction wheel assembly, star-tracker unit, inertial reference unit, and gyro drift estimators (Kalman filter). THe predicted spacecraft performance is analyzed for a variety of input commands and system disturbances. The primary deterministic inputs are desired attitude angles and rate setpoints. The stochastic inputs include random torque disturbances acting on the spacecraft, random gyro bias noise, gyro random walk, and star-tracker noise. These inputs are varied over a wide range to determine their effects on pointing accuracy and stability. The results are presented in the form of trade-off curves designed to facilitate the proper selection of subsystems so that overall spacecraft pointing accuracy and stability requirements are met.

Paper Details

Date Published: 7 June 1996
PDF: 15 pages
Proc. SPIE 2739, Acquisition, Tracking, and Pointing X, (7 June 1996); doi: 10.1117/12.241943
Show Author Affiliations
Marcelo C. Algrain, Univ. of Nebraska/Lincoln (United States)
Richard M. Powers, Univ. of Nebraska/Lincoln (United States)


Published in SPIE Proceedings Vol. 2739:
Acquisition, Tracking, and Pointing X
Michael K. Masten; Larry A. Stockum, Editor(s)

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