| 发射惯性坐标系下误差角与数学平台失准角的推导与仿真 |
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| 引用本文： | 邓红,刘光斌,陈昊明,刘志国.发射惯性坐标系下误差角与数学平台失准角的推导与仿真[J].宇航学报,2011,32(4). |
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| 作者姓名： | 邓红 刘光斌 陈昊明 刘志国 |
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| 作者单位： | 第二炮兵工程学院,西安,710025 |
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| 摘 要： | 基于状态空间法的捷联惯性/天文组合导航系统(SINS/CNS)需要数学平台失准角作为观测值参与滤波估计,工程实际只能得到SINS、CNS二者的姿态误差角.以弹道导弹为背景,在发射惯性坐标系下分别推导了四元数和欧拉角形式的姿态误差角与数学平台失准角之间的相互转换矩阵.建立了弹道导弹SINS/CNS数学模型,并采用EKF和UKF算法验证了该转换矩阵.仿真结果表明误差转换矩阵的正确性.
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| 关 键 词： | 姿态误差角 数学平台失准角 EKF滤波 UKF滤波 SINS/CNS组合导航 |
Deduction and Simulation of Angular Error Relationship in "SINS/CNS" Integrated Navigation System |
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| DENG Hong,LIU Guang-bin,CHEN Hao-ming,Liu Zhi-guo.Deduction and Simulation of Angular Error Relationship in "SINS/CNS" Integrated Navigation System[J].Journal of Astronautics,2011,32(4). |
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| Authors: | DENG Hong LIU Guang-bin CHEN Hao-ming Liu Zhi-guo |
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| Institution: | DENG Hong,LIU Guang-bin,CHEN Hao-ming,Liu Zhi-guo(The Second Artillery Engineering College,Xi'an 710025,China) |
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| Abstract: | In order to gain high accuracy navigation parameters,the attitude transformation matrix between attitude angular error and mathematic platform angular error is derived for a ballistic missile in this paper and is deduced in forms of both quaternion and Euler angles.The method of State of Space is often used to estimate navigation parameters,in which the mathematic platform angular error is the observation value involved in the observation equation of SINS/CNS integrated navigation system for ballistic missi... |
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| Keywords: | Attitude error Platform angles error EKF UKF SINS/CNS integrated guidance system |
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