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首页> 外文会议>Cranfield Conference on Dynamica and Control of Systems and Structures in Space; 2004; Liguria; IT >Attitude Dynamics and Control of a Dual-Body Spacecraft using Variable-Speed Control Moment Gyros
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Attitude Dynamics and Control of a Dual-Body Spacecraft using Variable-Speed Control Moment Gyros

机译：变速控制力矩陀螺仪对双体航天器的姿态动力学和控制

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摘要

The dynamics equations of a spacecraft consisting of two bodies mutually rotating around an axis are derived. One body contains a cluster of single-gimbal variable-speed Control Moment Gyros. The equations include all the inertia terms and are written in a general form, valid for any cluster configurations and any numbers of actuators in the cluster. A non-linear control law is designed for the spacecraft attitude and joint rotation. An acceleration-based steering law is used for the variable-speed Control Moment Gyros. The analytical results are tested by numerical simulations. A three-axis test-bed was designed and is in the final set-up phase.
机译：推导了由两个相互绕轴旋转的物体组成的航天器的动力学方程。一个机体包含一簇单臂变速控制力矩陀螺仪。这些方程式包含所有惯性项，并以通用形式编写，对任何集群配置和集群中任何数量的执行器均有效。针对航天器的姿态和关节旋转设计了非线性控制律。基于加速度的转向定律用于变速控制力矩陀螺仪。分析结果通过数值模拟进行测试。设计了一个三轴试验台，该试验台处于最后的设置阶段。

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