Analytical solution to optimal relocation of satellite formation flying in arbitrary elliptic orbits

Hancheol Cho, Sang Young Park, Sung Moon Yoo, Kyu Hong Choi

Research output: Contribution to journalArticlepeer-review

13 Citations (Scopus)


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.

Original languageEnglish
Pages (from-to)161-176
Number of pages16
JournalAerospace Science and Technology
Issue number1
Publication statusPublished - 2013 Mar

Bibliographical note

Funding Information:
This work was supported by the Korea Science and Engineering Foundation (KOSEF) through the National Research Lab. Program funded by the Ministry of Science and Technology (No. M10600000282-06J0000-28210 ).

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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