基于太阳矢量的皮卫星姿态角测量误差分析  

Error analysis of pico-satellite attitude angle measurement based on sun vector

作　　者：郁发新[1] 孙琳琳[2] 

机构地区：[1]浙江大学信息与电子工程系,杭州310027 [2]浙江大学浙江加州国际纳米技术研究院,杭州310029

出　　处：《吉林大学学报（工学版）》2008年第4期976-980,共5页Journal of Jilin University:Engineering and Technology Edition

基　　金：“973”国家重点基础研究发展规划项目(G1999033110);高等学校全国优秀博士学位论文作者专项基金项目(200035);教育部科学技术研究重点项目(104096)

摘　　要：分别分析计算了皮卫星姿态角测量的两大误差源:太阳矢量实际测量误差和轨道模型演化计算的太阳矢量误差。首先针对皮卫星体积小、重量轻、功耗低的特点,采用设计的微型太阳敏感器测量太阳矢量,与轨道演化计算获得太阳矢量相比,该方法更适合获取皮卫星姿态角度信息。通过分析获得太阳入射角——光电流非理想的余弦特性、光电流的噪声起伏、处理电路非线性、A/D采样非线性、温度测量不确定性等因素导致的太阳矢量实际测量误差为5.74°。由于皮卫星自身的特点不允许采用复杂的轨道演化模型,基于Kepler轨道模型计算获得的太阳矢量误差为0.1°。因此,基于太阳矢量的皮卫星姿态角测量总误差为5.84°。The error of pico-satellite attitude angle measurement consists of sun vector measurement error and sun vector calculation error, which are analyzed and calculated respectively. The picosatellite is characterized by small volume, light weight and low power consumption. Based on these characteristics, a designed micro sun sensor is used to measure the sun vector which is then compared with the sun vector calculated from the orbit propagator. In such a way the pico-satellite attitude angle can be obtained. It is determined that the sun vector measurement error is about 5.74° which is caused by many factors, such as the non-ideal cosine curve between incident angle and photocurrent, the photocurrent noise, the nonlinearity of the analog circuit and the A/D converter, and the temperature inaccuracy etc. The limited resource of pico-satellite constrains itself to adopt simple Kepler orbit propagator only to calculate the sun vector and its error which is about 0. 1°. Thus the total attitude angle error is about 5.84°.

关 键 词：光电子技术与激光技术 皮卫星 太阳矢量 太阳敏感器 姿态角 角度误差分析 

分 类 号：TN216[电子电信—物理电子学]