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- W2392079053 abstract "This paper discusses the problem in theory how to select the optimal or satisfying one among many sets of initial orbital elements,which are obtained from different kinds of facilities during spacecraft injection phase,and presents a new approach about optimization of initial orbital elements,which is based on the TOPSIS(Technique for Order Preference by Similarity to Ideal Solution) method.The design idea and six basic solution step of TOPSIS are described.According to the feature of spacecraft initial orbit,a decision-making mathematical model on optimization of initial orbital is established successfully by assuming the normal orbit as ideal solution and the bias orbit as negative-ideal solution.A optimization procedure of initial orbital elements is illustrated by a typical sun-synchronous satellite,and then the rationality and correctness of the mathematical model and optimizing method are verified." @default.
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- W2392079053 date "2006-01-01" @default.
- W2392079053 modified "2023-09-25" @default.
- W2392079053 title "An Approach to Optimizing the Initial Orbital Elements of Spacecraft Base on TOPSIS Method" @default.
- W2392079053 hasPublicationYear "2006" @default.
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