Rocket Powered Flight as a Perturbation to the Two-Body Problem.

<p>The two body problem and the rocket equation <b>r&#776;</b> + &#8714; &#945; <b>r&#775;</b> + <em>k</em>/<em>r</em>³<b>r</b> = <b>0</b> 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.</p>

Name thesis:degree_name

MS (Master of Science)

Level thesis:degree_level

Thesis - unrestricted

Discipline thesis:degree_discipline

Mathematical Sciences

Year dc:date.issued

2005

Author dc:creator

• Clark, Clayton Jeremiah

• rocket flight
• perturbation
• two-body problem
• Applied Mathematics
• Non-linear Dynamics
• Physical Sciences and Mathematics

Statement dc:rights

• Copyright by the authors.

Repository record dc:identifier

https://dc.etsu.edu/etd/1045

OAI identifier oai:identifier

oai:dc.etsu.edu:etd-2202