Analytical Low-Thrust Trajectory Design

Using the Simplified General Perturbations Model

Master thesis (2018)

Authors

J.G.P. de Jong Aerospace Engineering

Contributors

R. Noomen (supervisor 1)
Faculty
Aerospace Engineering
Copyright: © 2018 Hanneke de Jong
Astrodynamics Low-thrust SGP4
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Published Date

20-12-2018

Language

English

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Faculty

Aerospace Engineering

Abstract

An analytical low-thrust design tool for orbits around Earth has been developed which takes perturbations into account. The Simplified General Perturbations 4 model (SGP4) is combined with Edelbaum’s analytical low-thrust trajectory model. This resulted in the SGP4-LT tool which required an iterative version of SGP4. To obtain this iterative SGP4, an existing method was corrected and extended. A convergence rate of 99.5% was obtained for 17542 objects of the satellite catalogue. Convergence was not reached for combinations of inclinations smaller than 0.1° and eccentricities lower than 4e-6. SGP4-LT obtained expected results for orbit raising and non-coplanar orbit change. Altitude maintenance was performed which was based on the GOCE mission. SGP4-LT obtained a 14 % higher amount of propellant than GOCE had available.
SGP4-LT provides within seconds a first approximation solution for low-thrust transfer trajectories around Earth and is capable of calculating DeltaV budgets for altitude maintenance in low Earth orbits.