[en] The current paper presents and examines a general analytical solution to the optimal reconfiguration problem of satellite formation flying in an arbitrary elliptic 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 solution is found that compares favorably with numerical simulations. Also, this analytical solution is very useful for designing a reconfiguration controller for satellite formation flying in a general elliptic 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 > Department of Astronomy > Astrodynamics and Control Laboratory
Yoo, Sung-Moon; Korea Astronomy and Space Science Institute
Choi, Kyu-Hong
Language :
English
Title :
Analytical Solution to Optimal Relocation of Satellite Formation Flying in Arbitrary Elliptic Orbits
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