摘要
分析了小卫星捕获阶段的客观条件要求 ,重力梯度杆的指向要求 ,捕获阶段视为大角度机动问题 ,采用欧拉动力学和四元数方法描述 ,建立小卫星捕获阶段的动力学模型。控制器采用大角度机动拟 PD控制 ,拟PD控制器参数采用了简化分析和经验调试设计 ,同时分析设计了磁力矩器的磁偶极子 ,最后给出某小卫星姿态捕获仿真结果 ,经过几个轨道周期后可以实现一定精度的对地捕获 ,验证了本文的设计方法的可行性。
Small satellite attitude control system schemes often used gravity stability and active magnetic control with a bias wheel. Attitude can capture the Earth using active magnetic control for the global space and roll over. This paper studies the external request during small satellite acquisition, the gravity pole's pointing request. The acquisition phase is regarded as a large attitude maneuver problem, and a model is built with Euler dynamics and quaternion. The regulator was assimilated PD control, and the assimilated PD parameters design adopted predigest analysis and experience debug; at the same time, the magnetic pole is analyzed and designed. At last, the attitude acquisition simulation result is provided, which indicates that it can capture the earth after several orbit periods, and thus proves the method is valid in this paper.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2000年第2期142-145,共4页
Acta Aeronautica et Astronautica Sinica
关键词
小卫星
主动磁控
地球捕获
姿态控制
欧拉动力学
small satellite
active control
earth acquisition
attitude control
Euler dynamics and quaternion
