| 基于UKF的导弹SINS/CNS姿态估计方法 |
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| 引用本文： | 邓红,刘光斌,陈昊明,邓春林. 基于UKF的导弹SINS/CNS姿态估计方法[J]. 系统工程与电子技术, 2010, 32(9): 1987-1990. DOI: 10.3969/j.issn.1001-506X.2010.09.42 |
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| 作者姓名： | 邓红 刘光斌 陈昊明 邓春林 |
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| 作者单位： | 第二炮兵工程学院， 陕西 西安 710025 |
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| 摘 要： | 针对中远程弹道导弹的特点，在分析研究捷联惯性导航系统/天文导航系统(strapdown inertial navigation system/celestial navigation system, SINS/CNS)组合导航测量修正方案的基础上，建立了导弹四元数运动学方程、陀螺测量模型，星敏感器测量模型等系统方程，将无轨迹卡尔曼滤波(unscented Kalman filter, UKF)算法应用于主动段关机点环境，通过对陀螺常值漂移、一阶漂移的在线估计，达到高精度导弹姿态的实时输出。与EKF、QUEST、MLS和捷联惯性迭代递推算法比较，仿真结果表明了UKF算法具有更高的精度，收敛快，适于在无控飞行阶段的工程应用。
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| 关 键 词： | 无轨迹卡尔曼滤波 姿态确定 星敏感器 SINS/CNS组合导航 |
Application of missile attitude estimation based on UKF algorithm |
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| DENG Hong,LIU Guang-bin,CHEN Hao-ming,DENG Chun-lin. Application of missile attitude estimation based on UKF algorithm[J]. System Engineering and Electronics, 2010, 32(9): 1987-1990. DOI: 10.3969/j.issn.1001-506X.2010.09.42 |
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| Authors: | DENG Hong LIU Guang-bin CHEN Hao-ming DENG Chun-lin |
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| Affiliation: | The Second Artillery Engineering Inst., Xi’an 710025, China |
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| Abstract: | Aiming at the characteristics of intermediate-long-range ballistic missiles, the system equations, namely quaternion kinematics equation, gyro measuring model and satellite sensor measuring model, etc., are established on the basis of analyzing the revised measurement scheme of SINS/CNS combined navigation. The UKF algorithm is applied to the environment of the powered phase shutdown point, so that the output value of missile’s attitude achieves a high accuracy by on-line estimating the value of gyro drifts. Simulation results show that the UKF algorithm possesses a higher accuracy compared with EKF, QUEST, MLS and inertia iterative algorithms. |
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| Keywords: | unscented Kalman filter (UKF) missile attitude estimation star sensor strapdown inertial navigation system/celestial navigation system (SINS/CNS) integrated guidance system |
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