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A robust filtering algorithm for integrated navigation system of aerospace vehicle in launch inertial coordinate

机译：惯性坐标系下航天器组合导航系统的鲁棒滤波算法

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摘要

In ordinary aircrafts, the geographic coordinate is usually taken as reference coordinate to build navigation systems. Changes of gravity field and radius caused by the non-perfect sphere and uneven mass distribution of the earth are ignored or simplified in navigation algorithm, which have little effect on the accuracy of the navigation system in a short-time and short-distance flight. As the Aerospace Vehicles (ASVs) have to complete long-term on-orbit maneuver over wide flight enveloping, ignoring changes of gravity field and radius will bring about cumulative navigation errors and result in the declined accuracy of the navigation system. Hence, this paper first proposes an inertial navigation algorithm in launch inertial coordinate for ASVs aimed at reducing the effects caused by the inaccurate earth model on the navigation system. Then, the model of INS/CNS/GPS integrated navigation system in launch inertial coordinate is built. Considering the uncertain noise in space, the performance of Kalman filter may be poor, a robust filtering algorithm based on extended Ho filter is designed to realize multi-sensors information fusion; The state model and measurement model in launch inertial coordinate are built. The simulation results show that the proposed method and algorithm can improve the accuracy and reliability of the integrated navigation system for ASVs. (C) 2016 Published by Elsevier Masson SAS.
机译：在普通飞机中，通常将地理坐标作为构建导航系统的参考坐标。导航算法忽略或简化了由非理想球体引起的引力场和半径变化以及地球质量分布不均的问题，这对短时短途飞行中导航系统的精度影响很小。由于航空飞行器（ASV）必须在宽广的飞行范围内完成长期的在轨机动，因此忽略重力场和半径的变化将带来累积的导航误差，并导致导航系统的精度下降。因此，本文首先提出了一种针对ASV的发射惯性坐标中的惯性导航算法，旨在减少不正确的地球模型对导航系统的影响。然后，建立了发射惯性坐标下的INS / CNS / GPS组合导航系统模型。考虑到空间中的不确定噪声，卡尔曼滤波器的性能可能较差，设计了一种基于扩展Ho滤波器的鲁棒滤波算法来实现多传感器信息融合。建立了发射惯性坐标的状态模型和测量模型。仿真结果表明，所提出的方法和算法可以提高ASV组合导航系统的准确性和可靠性。 （C）2016由Elsevier Masson SAS发布。

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  • 来源
    《Aerospace science and technology》 |2016年第11期|629-640|共12页
  • 作者

    Zhao Hui; Xiong Zhi; Shi Lijuan; Yu Feng; Liu Jianye;

  • 作者单位

    Nanjing Univ Aeronaut & Astronaut, Coll Automat Engn, Nanjing 210016, Jiangsu, Peoples R China;

    Nanjing Univ Aeronaut & Astronaut, Coll Automat Engn, Nanjing 210016, Jiangsu, Peoples R China;

    Nanjing Univ Aeronaut & Astronaut, Coll Automat Engn, Nanjing 210016, Jiangsu, Peoples R China;

    Nanjing Univ Aeronaut & Astronaut, Coll Automat Engn, Nanjing 210016, Jiangsu, Peoples R China;

    Nanjing Univ Aeronaut & Astronaut, Coll Automat Engn, Nanjing 210016, Jiangsu, Peoples R China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Aerospace Vehicles (ASVs); Launch inertial coordinate; Extended H-infinity filter; Integrated navigation system;

    机译：航空航天器（ASV）;发射惯性坐标;扩展H无穷大滤波器;集成导航系统;

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