摘要
针对使用固体火箭发动机进行立方体卫星快速变轨机动过程中存在的姿态翻转问题,创新性地提出应用质量矩控制技术实现其姿态稳定。首先推导了完整的八自由度动力学模型,并深入分析了质量矩控制机理;然后利用仿真手段对质量块移动产生的附加扰动力矩以及系统耦合进行了研究,并指导了执行机构的布局优化设计;最后提出的双对称执行机构保证了附加扰动小的同时还大幅降低了通道间耦合。仿真表明该系统具有良好的操纵性。
A new technique named mass moment attitude control is proposed, on the issue that the attitude is not stable when a CubeSat is carrying out a fast orbit maneuver using the solid rocket motor. At first, the whole 8 freedom degrees dynamic equations are derived and deeply analyzed to clarify how it works. Then the additional disturbance torque and systematic coupling with the mass block moving are studied utilizing the simulation. Finally, the above conclusions provide a guideline for designing the actuator layout parameters. The proposed double symmetrical actuators turn out a little disturbance torque and a weak systematic coupling. Simulation results indicate that the attitude control system has a good maneuverability.
作者
陆正亮
张翔
于永军
莫乾坤
廖文和
LU Zhengliang ZHANG Xiang YU Yongjun MO Qiankun LIAO Wenhe(School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China)
出处
《系统工程与电子技术》
EI
CSCD
北大核心
2017年第3期599-605,共7页
Systems Engineering and Electronics
基金
江苏省高校优势学科建设项目
南京理工大学自主科研专项(30916011101)资助课题
关键词
快速机动
立方体卫星
质量矩
姿态控制
fast orbit maneuver
CubeSat
mass moment control
attitude control