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The Orbital Error Analysis and Study of Space Vehicle Active Phase
Abstract:
In this paper we solve the three-dimensional coordinate that the satellite is relative to the geocentric coordinate under certain conditions, making use of the satellite orbit standard trajectory differential equations. By means of the method of tri-parametric equation fitting, we confirm the three-dimensional trajectory function of target flying object to geocentric coordinate in double satellites observation conditions, and analyze theoretical errors.
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594-600
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Online since:
October 2014
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© 2014 Trans Tech Publications Ltd. All Rights Reserved
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