| GPS/SINS/CNS 组合导航在航天器上的应用 |
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| 引用本文： | 吕家旺,杨军,周春庆.GPS/SINS/CNS 组合导航在航天器上的应用[J].兵工自动化,2011,30(3):11-13. |
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| 作者姓名： | 吕家旺 杨军 周春庆 |
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| 作者单位： | 西北工业大学,航天学院,西安,710072 |
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| 摘 要： | 针对传统的惯性导航误差模型推导不适合空间应用以及GPS信号传输修正能力有限等问题,提出一种基于GPS/SINS/CNS的组合导航系统总体设计方案。在导航仿真系统中增加组合导航系统性能评估模块,推导了基于J2000坐标系的惯性导航误差模型,给出GPS、SINS与CNS的数学模型,利用扩展的卡尔曼滤波设计组合导航系统,对连续信号和信号中断两种模式进行了仿真。仿真结果表明,该导航系统能很好地满足航天器在轨运行的导航性能要求,能够为航天器提供高精度的测量与导航信息。
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| 关 键 词： | 组合导航 GPS/SINS/CNS 航天器 |
| 收稿时间： | 2013/1/16 0:00:00 |
Application of GPS/SINS/CNS Integrated Navigation in Spacecraft |
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| Lu Jiawang,Yang Jun,Zhou Chunqing.Application of GPS/SINS/CNS Integrated Navigation in Spacecraft[J].Ordnance Industry Automation,2011,30(3):11-13. |
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| Authors: | Lu Jiawang Yang Jun Zhou Chunqing |
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| Affiliation: | Lu Jiawang,Yang Jun,Zhou Chunqing(College of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China) |
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| Abstract: | Traditional inertial navigation error models based on the earth coordinate system are not suitable for space applications.An overall design of integrated navigation system for space applications is given.The inertial navigation error model is derived based on the inertial coordinate system(J2000),The Integrated navigation system is designed by the mathematical model of GPS,SINS with CNS and the extended Kalman filter.There are two simulation in interruption of continuous signals and signal simulation of two... |
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| Keywords: | GPS/SINS/CNS |
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