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



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

Cite this