The second-order analytical state propagation under an arbitrary continuous thrust is proposed for relative motion in $J_{2}$-perturbed elliptic chief orbits. The mean relative orbital elements are used to describe the relative motion. The second-order relative motion equations are obtained by performing the Taylor expansion of the nonlinear relative motion equations about the chief orbit. The original thrust acceleration is approximated by a truncated Fourier series in terms of the eccentric anomaly of the chief orbit. Based on the first-order state propagation and the thrust acceleration Fourier-series expansion, the second-order propagation of the mean relative orbital elements is obtained. Numerical simulations show that the state propagation errors of the second-order solution are reduced by 1–2 orders of magnitude when compared with the first-order solution.
Second-Order State Propagation for Continuous-Thrust Relative Motion in $J_{2}$-Perturbed Elliptic Orbits
IEEE Transactions on Aerospace and Electronic Systems ; 59 , 3 ; 3201-3212
2023-06-01
1030486 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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