Attitude determination and control system for a small LEO satellite

被引：0

作者：

Jan, YW ^{[1
]}

Ting, LH ^{[1
]}

机构：

[1] Natl Space Program Off, Spacecraft Project, Hsinchu 300, Taiwan

来源：

MICROSATELLITES AS RESEARCH TOOLS | 1999年 / 10卷

关键词：

D O I：

暂无

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

This paper describes the Attitude Determination and Control System (ADCS) for ROCSAT-1. The nominal ROCSAT-1 ADCS mission scenario and an overview of the ADCS design are presented. This paper summarizes design considerations in selecting the hardware that can fulfill the ROCSAT-1 mission requirements. After separation from the launch vehicle (Athena-1, Lockheed Martin), the ROCSAT-1 satellite uses four one-pound thrusters to perform a sun acquisition in a 600 km, 35-degree inclination circular orbit. Then the satellite transits to Science Mode through Maneuver Mode, in which the spacecraft attitude is three-axis stabilized with the z-axis nadir-pointed. Upon reaching its Science Mode, a wheel-based control system is designed to keep the ROCSAT-1 instrument accurately nadir-pointed for four years. Two fail-safe modes add robustness to the design. This paper shows how a small LEO satellite can be implemented with proven sensors and actuators resulting in low power usage, low weight and affordability.

引用

页码：180 / 184

页数：5