Maneuvering spacecraft, a state-of-art platform, is paid more and more attention on for the upcoming space exploring. The integration of CNS (Celestial Navigation System) and INS (Inertial Navigation System) is the promising autonomous navigation candidate for maneuvering spacecraft. However, the star image of CNS may be heavily degraded by the large attitude variation in the spacecraft maneuvering. The effect of the attitude variation on the star image is twofold: the enlarged areas and the reduced pixel gray value of the star image. Both of them will degrade the extracting accuracy of the star image center directly. Therefore, the feasibility of CNS for the maneuvering spacecraft mainly depends on the mitigation of the effect of the attitude variation on the star image. In this paper, the star image motion is modeled when the spacecraft attitude is maneuvering firstly. The pixel gray value of the star image is also formulated in the span of exposure according to the camera exposure model. Then, the motion compensation values for the star image are deduced with the INS angular velocity in the rolling, yaw, and pitch axes respectively. The compensated star image's center is extracted accurately in the following. Finally, the compensation method is validated by simulations. The simulation results prove that the star image center extraction is as accurate as 0.1 pixel with the aiding of a tactical INS even though the spacecraft angular velocity is as large as 30º/s.
INS-aided motion compensation for CNS images of maneuvering spacecraft
International Symposium on Photoelectronic Detection and Imaging 2011: Space Exploration Technologies and Applications ; 2011 ; Beijing,China
Proc. SPIE ; 8196
2011-08-15
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
INS-aided motion compensation for CNS images of maneuvering spacecraft [8196-106]
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