Line-of-sight pointing accuracy/stability analysis and computer simulation for small spacecraft

Marcelo C. Algrain; Richard M. Powers

doi:10.1117/12.241943

7 June 1996 Line-of-sight pointing accuracy/stability analysis and computer simulation for small spacecraft

Marcelo C. Algrain, Richard M. Powers

Proceedings Volume 2739, Acquisition, Tracking, and Pointing X; (1996) https://doi.org/10.1117/12.241943
Event: Aerospace/Defense Sensing and Controls, 1996, Orlando, FL, United States

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.

Citation Download Citation

Marcelo C. Algrain and Richard M. Powers "Line-of-sight pointing accuracy/stability analysis and computer simulation for small spacecraft", Proc. SPIE 2739, Acquisition, Tracking, and Pointing X, (7 June 1996); https://doi.org/10.1117/12.241943

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