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首页> 外文期刊>The Journal of Navigation >A High-accuracy SINS/CNS Integrated Navigation Scheme Based on Overall Optimal Correction
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A High-accuracy SINS/CNS Integrated Navigation Scheme Based on Overall Optimal Correction

机译：基于整体最优校正的高精度SINS / CNS组合导航方案

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摘要

In order to utilise the position and attitude information of a Celestial Navigation System (CNS) to aid a Strapdown Inertial Navigation System (SINS) and make it possible to achieve long-range and high-precision navigation, a new SINS/CNS integrated navigation scheme based on overall optimal correction is proposed. Firstly, the optimal installation angle of the star sensor is acquired according to the geometric relationship between the refraction stars area and the star sensor's visual field. Secondly, an analytical method to determine position and horizontal reference is introduced. Thirdly, the mathematical model of the SINS/CNS integrated navigation system is established. Finally, some simulations are carried out to compare the navigation performance of the proposed SINS/CNS integrated scheme with that of the traditional gyro-drift-corrected integration scheme. Simulation results indicate that in the proposed scheme, without the aid of SINS, CNS can provide attitude and position information and the errors of the SINS are able to be estimated and corrected efficiently. Therefore, the navigation performance of the proposed SINS/CNS scheme is superior to that of a more traditional scheme in long-range flight.
机译：为了利用天体导航系统（CNS）的位置和姿态信息来辅助捷联惯性导航系统（SINS）并实现远程和高精度导航，新的SINS / CNS集成导航方案提出了基于整体最优校正的方法。首先，根据折射星面积与恒星传感器视场之间的几何关系，获取恒星传感器的最佳安装角度。其次，介绍了一种确定位置和水平基准的分析方法。第三，建立了SINS / CNS组合导航系统的数学模型。最后，进行了一些仿真，以比较提出的SINS / CNS集成方案与传统陀螺漂移校正的集成方案的导航性能。仿真结果表明，在所提出的方案中，无需借助SINS，CNS可以提供​​姿态和位置信息，并且可以有效地估计和校正SINS的误差。因此，在远距离飞行中，所提出的SINS / CNS方案的导航性能优于传统方案的导航性能。

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