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Analysis of Formation Flying in Eccentric Orbits Using Linearized Equations of Relative MotionGeometrical 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.
Document ID
Acquisition Source
Goddard Space Flight Center
Document Type
Conference Paper
Lane, Christopher
(Colorado Univ. Boulder, CO, United States)
Axelrad, Penina
(Colorado Univ. Boulder, CO, United States)
Date Acquired
August 23, 2013
Publication Date
September 1, 2004
Publication Information
Publication: Proceedings from the 2nd International Symposium on Formation Flying Missions and Technologies
Subject Category
Spacecraft Design, Testing And Performance
Funding Number(s)
Distribution Limits
Public Use Permitted.
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