Second-order state transition for relative motion near perturbed,elliptic orbits |
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Authors: | Prasenjit Sengupta Srinivas R Vadali Kyle T Alfriend |
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Institution: | (1) Department of Aerospace Engineering, TAMU 3141, Texas A&M University, College Station, TX, 77843-3141, USA |
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Abstract: | This paper develops a tensor and its inverse, for the analytical propagation of the position and velocity of a satellite,
with respect to another, in an eccentric orbit. The tensor is useful for relative motion analysis where the separation distance
between the two satellites is large. The use of nonsingular elements in the formulation ensures uniform validity even when
the reference orbit is circular. Furthermore, when coupled with state transition matrices from existing works that account
for perturbations due to Earth oblateness effects, its use can very accurately propagate relative states when oblateness effects
and second-order nonlinearities from the differential gravitational field are of the same order of magnitude. The effectiveness
of the tensor is illustrated with various examples. |
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Keywords: | Formation flight Nonlinear relative motion State transition Nonsingular elements |
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