| 基于惯导/天文高精度定姿方法 |
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| 引用本文： | 杨生,孙付平,陈坡,秦士琨. 基于惯导/天文高精度定姿方法[J]. 测绘学院学报, 2009, 0(2) |
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| 作者姓名： | 杨生 孙付平 陈坡 秦士琨 |
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| 作者单位： | 哈尔滨工业大学航天学院;信息工程大学测绘学院;96251部队;61081部队; |
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| 摘 要： | 研究了利用惯性导航系统与天文导航系统进行组合定姿的方法;构造了惯导/天文组合导航系统的状态方程和量测方程;采用卡尔曼滤波技术设计了惯导/天文组合定姿算法。设计飞行器的典型飞行轨迹,通过数学仿真对该算法的有效性进行了验证。结果表明,天文导航能够有效地补偿惯性导航因陀螺漂移带来的误差,非常适用于飞行器的高精度定姿。
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| 关 键 词： | 飞行器 惯导/天文 组合定姿 卡尔曼滤波 |
Precise Attitude Determination Based on INS/CNS |
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| YANG Sheng,SUN Fu-ping,CHEN Po,,QIN Shi-kun. Precise Attitude Determination Based on INS/CNS[J]. Journal of Institute of Surveying and Mapping, 2009, 0(2) |
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| Authors: | YANG Sheng SUN Fu-ping CHEN Po QIN Shi-kun |
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| Affiliation: | 1.School of Astronautics;Harbin Institute of Technology;Harbin 150001;China;2.Institute of Surveying and Mapping;Information Engineering University;Zhengzhou 450052;3.96251 Troops;Luoyang 471123;4.61081 Troops;Beijing 100094;China |
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| Abstract: | The method of integrated attitude determination based on inertial navigation system and celestial navigation system is researched in this paper,the state equation and measurement equation of integrated navigation systems were established.Thus the algorithm of integrated attitude determination is designed by kalman filtering technology.By designing a typical flight route of aerocraft,its mathematical simulation was made which proved the algorithm's effectivity and showed that the CNS can effectively compensa... |
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| Keywords: | aerocraft INS/CNS integrated attitude determination Kalman filter |
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