星载太阳辐射监测仪的太阳程控跟踪精度

杨东军; 方伟; 叶新; 宋宝奇

doi:10.3788/OPE.20152307.1813

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星载太阳辐射监测仪的太阳程控跟踪精度

辐射定标 | 更新时间：2020-08-12

- 星载太阳辐射监测仪的太阳程控跟踪精度
- Program-controlled sun-tracking precision of spaceborne solar irradiance monitor
- 光学精密工程 2015年23卷第7期页码：1813-1821
- 作者机构：
  
  中国科学院长春光学精密机械与物理研究所, 吉林长春 130033
- 作者简介：
- 基金信息：
  
  国家自然科学基金科学仪器基础研究专项基金资助项目(No.41227003)()
- DOI：10.3788/OPE.20152307.1813
  中图分类号： TP732;P111.41
- 收稿日期：2015-02-13，
  
  修回日期：2015-04-24，
  
  纸质出版日期：2015-07-25
- 稿件说明：
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杨东军, 方伟, 叶新等. 星载太阳辐射监测仪的太阳程控跟踪精度[J]. 光学精密工程, 2015,23(7): 1813-1821

YANG Dong-jun, FANG Wei, YE Xin etc. Program-controlled sun-tracking precision of spaceborne solar irradiance monitor[J]. Editorial Office of Optics and Precision Engineering, 2015,23(7): 1813-1821
杨东军, 方伟, 叶新等. 星载太阳辐射监测仪的太阳程控跟踪精度[J]. 光学精密工程, 2015,23(7): 1813-1821 DOI： 10.3788/OPE.20152307.1813.

YANG Dong-jun, FANG Wei, YE Xin etc. Program-controlled sun-tracking precision of spaceborne solar irradiance monitor[J]. Editorial Office of Optics and Precision Engineering, 2015,23(7): 1813-1821 DOI： 10.3788/OPE.20152307.1813.

摘要

为了避免太阳敏感器(DSS)指向故障导致星载太阳辐射监测仪(SIM)功能失效

为风云三号(FY-3(03))卫星的太阳辐射监测仪(SIM)设计了备份跟踪方式程控太阳跟踪并分析了其跟踪精度。利用星上儒略日时间和卫星轨道瞬根

基于类基准地表辐射网(BSRN)算法推导了轨道坐标系太阳矢量、俯仰角和偏航角。将计算结果与卫星给定指向数据进行了比较。结果表明:太阳矢量三轴偏差均小于0.1°

俯仰角平均偏差为0.024 6°

偏航角平均偏差为-0.080 4°。对利用程序计算的多轨道指向数据进行了太阳模拟跟踪控制实验

结果表明:SIM俯仰跟踪控制精度优于0.1°

偏航跟踪控制精度优于0.05°。为保证在轨跟踪精度

试验了俯仰零点角和偏航零点角

其分别为80.46°和-36.96°。最终分析结果表明

俯仰程控跟踪不确定度为±0.318°

偏航程控跟踪不确定度为±0.316°

满足SIM太阳跟踪精度±0.5°的要求。设计的太阳程控跟踪降低了SIM对光学指向器件的依赖

提高了在轨太阳跟踪的可靠性。

Abstract

To avoid the function failure of a solar irradiance monitor (SIM) caused by the pointing faults of the Digital Sun Sensor(DSS)

the program-controlled sun-tracking of SIM on the FY-3(03) satellite was explored as the backup sun-tracking

and its precision was analyzed. By using the Julian day time and the satellite orbital parameters

the sun vector in orbital coordinate system

pitch angle and the yaw angle were deduced on the basis of Baseline Surface Radiation Network(BSRN)-like algorithm. The calculated results were compared to that of the satellite-given sun-pointing data

it shows that the sun vector deviations in three axes are all less than 0.1°

and the average deviations of pitch angle and yaw angle are 0.024 6° and -0.080 4° respectively. Using the program-calibrated sun-pointing data of many orbits

a sun-tracking control simulation experiment was carried out

and the results show that the pitch tracking control precision is better than 0.1°

and the yaw tracking control precision is better than 0.05°. To guarantee the on-orbit tracking precision

the pitch zero-position angle and the yaw zero-position angle were measured

and they are 80.46° and -36.96° respectively. The final analysis results show that the pitch tracking uncertainty is ±0.318° and the yaw tracking uncertainty is ±0.316°

meeting SIM sun-tracking precision requirement of ±0.5°. The proposed program-controlled sun-tracking reduces the dependence on the optical pointing devices

and improves on-orbit sun-tracking reliability.

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references

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