### Abstract

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.

Original language | English |
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Title of host publication | American Astronautical Society - Space Flight Mechanics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting |

Pages | 153-179 |

Number of pages | 27 |

Publication status | Published - 2007 Dec 1 |

Event | 17th Annual Space Flight Mechanics Meeting - Sedona, AZ, United States Duration: 2007 Jan 28 → 2007 Feb 1 |

### Publication series

Name | Advances in the Astronautical Sciences |
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Volume | 127 PART 1 |

ISSN (Print) | 0065-3438 |

### Other

Other | 17th Annual Space Flight Mechanics Meeting |
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Country | United States |

City | Sedona, AZ |

Period | 07/1/28 → 07/2/1 |

### Fingerprint

### All Science Journal Classification (ASJC) codes

- Aerospace Engineering
- Space and Planetary Science

### Cite this

*American Astronautical Society - Space Flight Mechanics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting*(pp. 153-179). (Advances in the Astronautical Sciences; Vol. 127 PART 1).

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*American Astronautical Society - Space Flight Mechanics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting.*Advances in the Astronautical Sciences, vol. 127 PART 1, pp. 153-179, 17th Annual Space Flight Mechanics Meeting, Sedona, AZ, United States, 07/1/28.

**Analytical solution to optimal relocation of satellite formation flying in arbitrary elliptic orbits.** / Cho, Han Cheol; Park, Sang Young; Yoo, Sung Moon; Choi, Kyu Hong.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

TY - GEN

T1 - Analytical solution to optimal relocation of satellite formation flying in arbitrary elliptic orbits

AU - Cho, Han Cheol

AU - Park, Sang Young

AU - Yoo, Sung Moon

AU - Choi, Kyu Hong

PY - 2007/12/1

Y1 - 2007/12/1

N2 - 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.

AB - 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.

UR - http://www.scopus.com/inward/record.url?scp=55549112580&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=55549112580&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:55549112580

SN - 9780877035411

T3 - Advances in the Astronautical Sciences

SP - 153

EP - 179

BT - American Astronautical Society - Space Flight Mechanics 2007 - Advances in the Astronautical Sciences, Proceedings of the AAS/AIAA Space Flight Mechanics Meeting

ER -