Microsatellite Attitude Determination and Control Subsystem Design and Implementation: Software-in-the-Loop Approach

作     者：Shou, Ho-Nien 

作者机构：Air Force Inst Technol Dept Aviat & Commun Elect Kaohsiung 820 Taiwan 

出 版 物：《MATHEMATICAL PROBLEMS IN ENGINEERING》 (Math. Probl. Eng.)

年 卷 期：2014年第2014卷第1期

页      面：1-12页

核心收录：

学科分类：08[工学] 0701[理学-数学] 

基　　金：ROC National Science Council [NSC101-2221-E-344-002] ROC National Space Organization Academic Research Grants [NSPO-S-099135] Air Force Command of Academic Research Grants 

主　　题：ARTIFICIAL satellite attitude control systems COMPUTER software PULSE-width modulation ANGULAR velocity KALMAN filtering 

摘      要：The paper describes the development of a microsatellite attitude determination and control subsystem (ADCS) and verification of its functionality by software-in-the-loop (SIL) method. The role of ADCS is to provide attitude control functions, including the de-tumbling and stabilizing the satellite angular velocity, and as well as estimating the orbit and attitude information during the satellite operation. In Taiwan, Air Force Institute of Technology (AFIT), dedicating for students to design experimental low earth orbit micro-satellite, called AFITsat. For AFITsat, the operation of the ADCS consists of three modes which are initialization mode, detumbling mode, and normal mode, respectively. During the initialization mode, ADCS collects the early orbit measurement data from various sensors so that the data can be downlinked to the ground station for further analysis. As particularly emphasized in this paper, during the detumbling mode, ADCS implements the thrusters in plus-wide modulation control method to decrease the satellite angular velocity. ADCS provides the attitude determination function for the estimation of the satellite state, during normal mode. The three modes of microsatellite adopted Kalman filter algorithm estimate microsatellite attitude. This paper will discuss using the SIL validation ADCS function and verify its feasibility.