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首页> 外文会议>Sixth International Conference on Electronic Measurement amp; Instruments (ICEMI '2003) Vol.1; Aug 18-21, 2003; Taiyuan, China >Study of the Method for the Spacecraft Autonomous Celestial Navigation Based on the Kalman Filter
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Study of the Method for the Spacecraft Autonomous Celestial Navigation Based on the Kalman Filter

机译：基于卡尔曼滤波的航天器自主天体导航方法研究

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摘要

The high positioning precision can be obtained by the autonomous navigation method based on indirectly sensing horizon by stellar atmospheric refraction. Because of the finite space-time resolving power of the stratosphere density model, large instantaneous error will occur in the horizon sensed by this method. In this case, the performance of the navigation filter will degrade, even diverge. In this paper, the Fuzzy Inference System (FIS) is applied to the autonomous celestial navigation to resolve this problem. The navigation filter can obtain the adaptive ability when the observation is exceptional. The results of the computer simulation demonstrate the validity of this method.
机译：通过基于恒星大气折射间接感知地平线的自主导航方法，可以获得较高的定位精度。由于平流层密度模型的时空分辨能力有限，因此用这种方法检测到的地层会出现较大的瞬时误差。在这种情况下，导航过滤器的性能将下降，甚至发散。本文将模糊推理系统（FIS）应用于自主天体导航以解决这一问题。当观察异常时，导航过滤器可以获得自适应能力。计算机仿真结果证明了该方法的有效性。

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