Geometrical methods for formation flying design based on the analytical solution to Hill's equations have been previously developed and used to specify desired relative motions in near circular orbits. By generating relationships between the vehicles that are intuitive, these approaches offer valuable insight into the relative motion and allow for the rapid design of satellite configurations to achieve mission specific requirements, such as vehicle separation at perigee or apogee, minimum separation, or a specific geometrical shape. Furthermore, the results obtained using geometrical approaches can be used to better constrain numerical optimization methods; allowing those methods to converge to optimal satellite configurations faster. This paper presents a set of geometrical relationships for formations in eccentric orbits, where Hill.s equations are not valid, and shows how these relationships can be used to investigate formation designs and how they evolve with time.
Analysis of Formation Flying in Eccentric Orbits Using Linearized Equations of Relative Motion
01.09.2004
Aufsatz (Konferenz)
Keine Angabe
Englisch
Formation Design in Eccentric Orbits Using Linearized Equations of Relative Motion
Online Contents | 2006
|Formation flying control in eccentric orbits
AIAA | 2001
|Spacecraft Formation-Flying in Eccentric Orbits
AIAA | 2003
|The study of relative dynamics for spacecraft formation flying in eccentric orbits
Emerald Group Publishing | 2003
|