Hangkong bingqi (Jun 2023)
An Artificial Celestial Observation Navigation System Using Star Sensor
Abstract
To solve the guidance error caused by inaccurately initial position of rapid launch in inertial navigation, a navigation method using a single satellite sensor to observe the near Earth communication satellite is proposed, which can correct the position of the aircraft through observing the position of satellite in inertial space and comparing with the computer simulation results. Taking a simulation trajectory as an instance, the paper conducts simulation experiments through Kalman filter integrated navigation. The results show that this navigation approach can realize the fast positioning of the observed satellite within 30 s and positioning accuracy of 350 m. In addition, it can realize the fast position correction without adding new navigation equipment, and improve the precision of integrated navigation of strapdown inertial navigation.
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