Rocket powered flight as a perturbation to the two-body problem.

摘要

The two body problem and the rocket equation r¨ +&egr; alpha r˙+ kr3 r = 0 have been expressed in numerous ways. However, the combination of the rocket equation with the two body problem has not been studied to any degree of depth due to the intractability of the resulting non-linear, non-homogeneous equations. The goal is to use perturbation techniques to approximate solutions to the combined two body and rocket equations.