[en] The current paper presents and examines a general analytical solution to the optimal reconfiguration problem of satellite formation flying in an arbitrary eccentric orbit. The proposed approach does not use any simplifying assumptions regarding the eccentricity of the reference orbit. For the fuel optimal reconfiguration problem, continuous and variable low-thrust accelerations can be represented by the Fourier series and summed into closed-form solutions. Initial and final boundary conditions are used to establish the constraints on the thrust functions. The analytical solution can be implicated by the Fourier coefficients that minimize propellant usage during the maneuver. This analytical solution is very useful for designing a reconfiguration controller for satellite formation flying in a general elliptical orbit.
Disciplines :
Aerospace & aeronautics engineering
Author, co-author :
Cho, Hancheol ; Université de Liège > Département d'aérospatiale et mécanique > Laboratoire de structures et systèmes spatiaux
Park, Sang-Young; Yonsei University > Astronomy
Yoo, Sung-Moon; Korea Astronomy and Space Science Institute
Choi, Kyu-Hong; Yonsei University > Astronomy
Language :
English
Title :
Analytical Solution to Optimal Relocation of Satellite Formation Flying in Arbitrary Elliptic Orbits
Publication date :
February 2007
Event name :
AAS/AIAA Spaceflight Mechanics Meeting
Event organizer :
AAS (American Astronautical Society), AIAA (American Institute of Aeronautics and Astronautics)
Event place :
Sedona, United States
Event date :
from 28-01-2007 to 01-02-2007
Audience :
International
Main work title :
AAS/AIAA Spaceflight Mechanics Meeting, Sedona 28 January - 1 February 2007
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