Optimal Satellite Formation Reconfiguration
Abstract
The use of swarms of small satellites operating in a formation is receiving more and more attention. Such formations can potentially replace large, monolithic satellites and reduce costs and improve survivability, as well as enabling new missions. Assuming a circular reference orbit and motion about a spherical Earth the best known formations are leader‐follower or string of pearls, 2x1 in‐plane ellipse, circular and projected circular. If the reference orbit is eccentric similar formations exist. The circular and projected circular formations involve motion out of the reference orbit plane and this out‐of‐plane motion is created by a combination of a differential right ascension and differential inclination. Relative motion in the orbit plane is created with a combination of a differential eccentricity and argument of latitude phase difference. Thus, formation reconfigurations involve changes in these orbital parameters. Given a set of desired formations about a circular reference orbit this research will focus on determining the sequence of reconfigurations that minimizes the total amount of fuel required to achieve the set of reconfigurations. The Earth oblateness, depending on the differential orbital parameters of the formation, can cause the formation to slowly distort and this effect may need to be controlled or negated with fuel. In this research the oblateness effects will not be considered.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Aug 01, 2019
- Source ID
- N002441910013
Entities
People
- Kyle Alfriend
Organizations
- Texas Engineering Experiment Station
- United States Air Force