Abstract

The NASA benchmark tetrahedron constellation is a proposed satellite formation that requires a nominal separation distance at every apogee point. To maintain these separation distance constraints between any pair of satellites within the constellation, an open-loop scheme was developed based on the orbital elements. For a particular size of the NASA benchmark tetrahedron problem, the constellation maintains the separation distance conditions without perturbations. On the other hand, with perturbations, the constellation maintains the separation distance criteria for a limited number of orbits.

This scheme does not maintain the constellation together for the complete mission period. For this reason, the Tschauner–Hempel (TH) equations are used to maintain the separation distance criteria. Two control schemes are used to maintain the separation distance conditions of the tetrahedron constellation and are compared with each other to determine which one provides for minimum time and consumption.

Keywords

tetrahedron constellation, linear quadratic regulator, elliptical orbits

Authors