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.
|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|
|Number of pages||27|
|Publication status||Published - 2007|
|Event||17th Annual Space Flight Mechanics Meeting - Sedona, AZ, United States|
Duration: 2007 Jan 28 → 2007 Feb 1
|Name||Advances in the Astronautical Sciences|
|Volume||127 PART 1|
|Other||17th Annual Space Flight Mechanics Meeting|
|Period||07/1/28 → 07/2/1|
Bibliographical noteFunding 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
- Space and Planetary Science