Deployment procedure for the Tetrahedron Constellation

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.