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Inverse Transformation of Elliptical Relative State Transition Matrix

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DOI: 10.4236/ijaa.2014.43037    2,388 Downloads   2,848 Views  

ABSTRACT

A new set of relative orbit elements (ROEs) is used to derive a new elliptical formation flying model in previous work. In-plane and out-of-plane relative motions can be completely decoupled, which benefits elliptical formation design. In order to study the elliptical control strategy and perturbation effects, it is necessary to derive the inverse transformation of the relative state transition matrix based on relative orbit elements. Poisson bracket theory is used to obtain the linear transformations between the two representations: the relative orbit elements and the geocentric orbital frame. In this paper, the details of these transformations are presented.

Conflicts of Interest

The authors declare no conflicts of interest.

Cite this paper

Yin, J. , Rao, Y. and Han, C. (2014) Inverse Transformation of Elliptical Relative State Transition Matrix. International Journal of Astronomy and Astrophysics, 4, 419-428. doi: 10.4236/ijaa.2014.43037.

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