|
|||||
 |
|
|
|
|
|
Deployment procedure
for the Tetrahedron Constellation
Pedro A. Capó-Lugo and Peter M. Bainum |
|
Vol. 4 (2009), No. 5, 837–854
|
Abstract |
|
The NASA Benchmark Tetrahedron Constellation is a four-satellite formation that requires a nominal separation distance at every apogee point. The deployment procedure of a tetrahedron constellation is complex and depends on the separation distance between any pair of satellites within the constellation. In this paper, the deployment procedure of the tetrahedron constellation will be divided into two stages: the deployment from a circular parking orbit to an elliptical orbit, and the correction of the separation distance between pairs of satellites within the constellation. The solution of this problem will be implemented with a combination of Hohmann transfer maneuvers and the digital linear quadratic regulator control scheme showing a minimum consumption of fuel. In summary, the combination of these two techniques will provide a different approach to the deployment procedure of the NASA benchmark tetrahedron constellation. |
Keywords
discrete linear quadratic regulator, impulse maneuvers,
deployment procedure, tetrahedron constellation
|
Milestones
Received: 11 March 2008
Revised: 13 May 2009
Accepted: 17 May 2009
Published: 5 September 2009
|
Authors |
| Pedro A. Capó-Lugo | |
| Department of Mechanical
Engineering Howard University 2300 Sixth Street, NW Washington, DC 20059 United States |
EV41 Guidance, Navigation and Control Systems Design and Analysis Branch NASA Marshall Space Flight Center Huntsville, AL 35812 United States |
| Peter M. Bainum | |
| Department of Mechanical
Engineering Howard University 2300 Sixth Street, NW Washington, DC 20059 United States |
|
|
