| 基于欧拉角观测模型的航天器姿态确定方法 |
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| 引用本文： | 张力军,张士峰,杨华波,钱山.基于欧拉角观测模型的航天器姿态确定方法[J].国防科技大学学报,2012,34(6):84-88. |
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| 作者姓名： | 张力军 张士峰 杨华波 钱山 |
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| 作者单位： | 1. 国防科技大学航天与材料工程学院,湖南长沙,410073
2. 西安卫星测控中心宇航动力学国家重点实验室,陕西西安,710043 |
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| 基金项目： | 国家863计划资助项目，航天科技创新基金资助项目，国防科技大学优秀研究生创新资助项目 |
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| 摘 要： | 针对基于乘性误差四元数的EKF姿态确定技术,系统研究了姿态敏感器常用的欧拉角观测模型,从两个方面证明了目前许多文献中所构造的欧拉角误差相对于误差四元数矢部的测量灵敏度矩阵存在缺陷,从理论上剖析了这一问题的成因,并推导了正确的测量灵敏度矩阵形式,数值仿真进一步验证了本文的结论。
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| 关 键 词： | 航天器 姿态确定 欧拉角观测模型 乘性误差四元数 |
| 收稿时间： | 6/1/2012 12:00:00 AM |
Spacecraft attitude determination based on Euler angle measurement model |
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| ZHANG Lijun,ZHANG Shifeng,YANG Huabo and QIAN Shan.Spacecraft attitude determination based on Euler angle measurement model[J].Journal of National University of Defense Technology,2012,34(6):84-88. |
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| Authors: | ZHANG Lijun ZHANG Shifeng YANG Huabo and QIAN Shan |
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| Institution: | 1.College of Aerospace and Materials Engineering,National University of Defense Technology,Changsha 410073,China; 2.The State Key Laboratory of Astronautic Dynamics,Xi’an Satellite Control Center,Xi’an 710043,China) |
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| Abstract: | For the multiplicative quaternion-error attitude determination approach, the attitude sensors for Euler angle measurements are studied. Two different methods were used to demonstrate that the measurement sensitivity matrix of Euler angle error with respect to error quaternion solved in many references is false. The correct measurement sensitivity matrix is presented and the reason for this mistake is analyzed in detail, and the numerical examples are given for the validation and verification of the conclusions. |
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| Keywords: | spacecraft attitude determination Euler angle measurement model multiplicative error quaternion |
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