Magnetometer Compensation Scheme and Experimental Results on ZDPS-1A Pico-satellite  

作　　者：HAN Ke WANG Hao XIANG Tian JIN Zhonghe 

机构地区：[1]Department of Information Science and Electronic Engineering Zhejiang University,Hangzhou 310027,China

出　　处：《Chinese Journal of Aeronautics》2012年第3期430-436,共7页中国航空学报（英文版）

基　　金：Program for New Century Excellent Talents in University (NCET-06-0514);China Postdoctoral Science Foundation (20081458, 20080431306)

摘　　要：In a pico-satellite with small volume, measurements from on-board three-axis magnetometer （TAM） are not accurate, as it can be easily disturbed by other electronic systems. To improve its accuracy, a scheme of compensation methods is introduced in this article. The scheme is based on an improved meast, rement model of pico-satellite TAM, and it mainly consists of three steps. First, in satellite design stage, several techniques are recommended to simplify the afterwards compensations. Then after satellite assembly, TAM ground tests and pre-launch calibration with least-square batch filter are introduced to improve magnetometer performance. At the end, a post-launch calibration with unscented Kalman filter （UKF） is implemented with in-orbit data. The compensation scheme is used in the development of Chinese pico-satellite ZDPS-1A made by Zhejiang University. Results show that with the introduced compensation scheme, the maximum error of ZDPS-1A TAM can be reduced from 80 mG to 6 naG （1 G=10^-4T）.In a pico-satellite with small volume, measurements from on-board three-axis magnetometer （TAM） are not accurate, as it can be easily disturbed by other electronic systems. To improve its accuracy, a scheme of compensation methods is introduced in this article. The scheme is based on an improved meast, rement model of pico-satellite TAM, and it mainly consists of three steps. First, in satellite design stage, several techniques are recommended to simplify the afterwards compensations. Then after satellite assembly, TAM ground tests and pre-launch calibration with least-square batch filter are introduced to improve magnetometer performance. At the end, a post-launch calibration with unscented Kalman filter （UKF） is implemented with in-orbit data. The compensation scheme is used in the development of Chinese pico-satellite ZDPS-1A made by Zhejiang University. Results show that with the introduced compensation scheme, the maximum error of ZDPS-1A TAM can be reduced from 80 mG to 6 naG （1 G=10^-4T）.

关 键 词：pico-satellite MAGNETOMETERS calibration： least-square filter Kalman filter 

分 类 号：V474[航空宇航科学与技术—飞行器设计] TP212.1[自动化与计算机技术—检测技术与自动化装置]