| Satellite formation flying is a very promising field for future space missions as it holds many advantages over the common monolithic satellite. However, in order for the formations to be effective, a formation maintenance scheme is required to overcome perturbations arising from different sources. In this thesis the effect of atmospheric drag on a formation is examined. To do so the Schweighart and Sedwick equations, which describe the motion of a spacecraft, called deputy spacecraft, relative to another spacecraft, referred to as the chief spacecraft, placed in a circular orbit, are modified to account for atmospheric drag. The modified equations keep the effects arising from the oblateness of the Earth, known as the J2 effects, which were included in the model proposed by Schweighart and Sedwick. A similar set of equation is then developed for satellite formations placed in orbits of small eccentricity. A formation maintenance scheme which uses differential atmospheric as a means of control is then introduced. Numerical simulation results showing the evolution of formations through time with and without active control are also provided. |
