摘要
卫星在轨运行需要卫星太敏与动量轮之间的精确角度值作为控制参数,卫星在振动试验前后该角度的精度变化是考核卫星结构设计的重要指标。运用由多台高精度电子经纬仪组合而成非接触式测量系统,结合卫星结构的复杂性及动量轮和太敏安装位置的特殊性,测量某微小卫星太敏与动量轮之间的夹角在振动试验前、后的变化值。该测量系统能有效运用于卫星角度测量,测试精度满足要求,测试数据可以作为卫星在轨姿态控制参数。
The angle between Sun Sensor and the Momentum Wheel on a satellite is an important parameter used in the control system of a satellite. The amount of the angle change before and after the vibration test is important to assess the satellite＇s structural design. This paper presents a non-contact measurement and method which is based on a measure- ment system consisting of multiple high-precision electronic theodolites. Using this method, the amount of the angle change before and after a vibration test can be measured as well as the complexity of the satellite structure, the particular- ity of the Sun Sensor and the Momentum Wheel locations can be determined. The method can be effectively applied in measuring the angles between the satellite components. The accuracy of the measurement is suitable for the design-requirement and the test data can be used as the parameters for the behavior of the control system of the satellite.
出处
《国外电子测量技术》
2013年第3期36-38,42,共4页
Foreign Electronic Measurement Technology
关键词
航天器
精度测量
微小卫星
经纬仪
spacecraft ~ precision measurement
microsatellite ~ theodolite
