Near-Minimum Fuel Trajectories for Multi Spacecraft Interferometric Imaging Systems in Near-Earth Orbit

In this article a methodology to calculate near-minimum fuel maneuvers for multi spacecraft interferometric imaging systems subject to linear non-symmetric dynamics is proposed. The methodology consists of the coupling of a nonlinear programming problem and a linear quadratic tracker. The solutions are obtained with the purpose of describing the relationship between the quality of an image obtained by a multi-spacecraft interferometric imaging system and the dynamic requirements of the maneuvers in a near earth circular orbit. These maneuvers are intended for the design of a system capable of obtaining very high resolution pictures form a near Earth orbital location. The solutions account for the effects of near Earth orbit dynamics. In order to relate the fuel requirements with the image quality, the relationship between the image process and the error in the final picture is studied, and a quality factor is defined in order to relate the reliability of a picture to the trajectory of the spacecraft and consequently, the fuel usage. As an application, a mid IR imager system located at a GEO location is studied and features of the design of such maneuvers as well as their feasibility and requirements are described