Analytical Solutions for J3, J4, J5 and Third Body Perturbations for Orbit Propagation

Dataset

Description

Analytical solutions to the motion of the spacecraft subject to J3, J4, J5 and third body perturbations, expressed in non-singular equinoctial orbital elements. The solutions are reported in MATLAB files.

Data to be made public at the discretion of the data creator.
Date made available10 Aug 2018
PublisherUniversity of Strathclyde

Research Output

Optimised GTO-GEO transfer using low-thrust propulsion

Di Carlo, M., Vasile, M. & Kemble, S., 3 Jun 2017. 10 p.

Research output: Contribution to conferencePaper

Open Access
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    Cite this

    Di Carlo, M. (Creator), Vasile, M. (Creator) (10 Aug 2018). Analytical Solutions for J3, J4, J5 and Third Body Perturbations for Orbit Propagation. University of Strathclyde. 10.15129/354f9b2a-d1d5-4f51-9545-e963251f1e40