Document Type

Conference Paper

Publication Date

2018

Journal Article Version

Accepted Manuscript

First Page

1

Last Page

20

Abstract

On-board targeting, guidance, and navigation relies on orbit propagation algorithms that must strike a balance between accuracy and computational efficiency. To better understand this balance, the performance of numerical propagation methods is analyzed for LEO, GEO, and Molniya orbits. A numerical propagator consists of a set of differential equations describing perturbed orbital motion whose solution is approximated using a numerical integration method. This paper compares Cowell, Encke-time, Encke-beta, and Equinoctial Elements formulations over a range of integration function evaluations for a given set of perturbations and integrators. Function evaluations are shown to be a reasonable approximation of normalized computation time. This comparison is conducted for three fixed-step integrators: a Runge-Kutta 4th order, a Nystrom-Lear 4th order, and a ¨ Runge-Kutta-Butcher 6th order. Fixed-step integration ensures the amount of time for each integration step is constant, a requirement for on-board propagation.

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