Modeling and attitude control of CubeSat utilizing moving mass actuators

被引：3

作者：

Lu, Zhengliang ^{[1
]}

Hu, Yuandong ^{[1
]}

Liao, Wenhe ^{[1
]}

Zhang, Xiang ^{[1
]}

机构：

[1] Nanjing Univ Sci & Technol, Sch Mech Engn, 200 Xiaolingwei St, Nanjing 210094, Jiangsu, Peoples R China

来源：

ADVANCES IN SPACE RESEARCH | 2021年 / 67卷 / 01期

基金：

中国国家自然科学基金;

关键词：

CubeSat; Solid rocket motor; Attitude control; Moving mass; Backstepping; Sliding mode control;

D O I：

10.1016/j.asr.2020.09.027

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Any vehicle propelled by solid rocket motors (SRMs) must include an attitude control system capable of dealing with the torque generated by thrust misalignment. In order to expand the application of SRMs on CubeSats, an attitude control system utilizing moving mass actuators is discussed. The present research develops an eight-degree-of-freedom simulation model of a 2U CubeSat with two moving mass actuators. That model also considers the influence of propellant combustion processes. By analyzing the model disturbance source and systematic coupling, the key layout parameters are designed and a simplified control model is proposed. The controller is derived based on a combination of backstepping and sliding mode techniques. An orbit maneuver from 300 km circular orbit to 300 and 500 km elliptical orbit using this attitude control system is verified. (C) 2020 COSPAR. Published by Elsevier Ltd. All rights reserved.

引用

页码：521 / 530

页数：10

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