Date of Award
6-2024
Degree Name
Doctor of Philosophy
Department
Mechanical and Aerospace Engineering
First Advisor
Kapseong Ro, Ph.D.
Second Advisor
Jennifer Hudson, Ph.D.
Third Advisor
Peter Gustafson, Ph.D.
Fourth Advisor
Damon Miller, Ph.D.
Keywords
Continuous thrust, orbital mechanics, relative orbital elements, satellite relative motion
Abstract
A model for modifying the relative orbit of a deputy satellite with respect to a chief satellite in a near-circular orbit using continuous periodic thrust is presented. This model is built on the Lovell-Spencer relative orbital elements (ROEs). The four linear ROEs (xr, yr, ar, and Az) can be linearly modified. The two angular ROEs (Er and ) can be set to advance at a desired, constant rate. Each ROE can be modified individually but may cause intra-orbit variations in other ROEs which return to their original values at the end of a thrust cycle. A method to easily calculate the periodic thrust parameters is developed. The NASA General Mission Analysis Tool (GMAT) is used to demonstrate how each ROE can be linearly modified, both individually and simultaneously for a coordinated rendezvous. Additionally, results from the model are compared to published maneuvers with favorable results and approximate limits of applicability are determined. Finally, an alternate model using a modified square wave is presented for future development.
Access Setting
Dissertation-Open Access
Recommended Citation
Hittepole, Philip Alan, "A Model for Spacecraft Relative Motion Using Continuous Periodic Thrust" (2024). Dissertations. 4086.
https://scholarworks.wmich.edu/dissertations/4086