TY - GEN
T1 - The function approximation method applied in MEO and IGSO satellites optimal maneuver
AU - Tan, Wei
AU - Jen, Tien Chien
PY - 2008
Y1 - 2008
N2 - In the case of medium earth orbit (MEO) and inclined geosynchronous orbit (IGSO) satellites, the orbit maneuver mission, in order to ensure satellites to enter the theoretically designed orbit as soon as possible, must be finished in the limited number of revolutions around the earth with the restrained propellant. This requires rapidly optimizing the whole orbit control strategy in terms of the actual orbit characteristics of the launched satellite. So that the optimal initial and final points of each thrust arc for satellites to maneuver can be determined precisely. This paper describes a numerical optimization algorithm, which can be applied to the strategy optimization in the orbit maneuver of MEO and IGSO satellites. This is a type of functional approximation method (FAM), which is specially adapted to cope with the single variable and equality/inequality constraints. In this paper, the modeling of the method is introduced to describe the basic approach. Then, the applications of this method and the results from the simulations are discussed in details. Compared with the conventionally adopted multidimensional exhaust algorithm, this method has the advantages of simplicity, uniformity, less dependence on the initial parameter zone, and much less computational effort for the optimal maneuver strategy generation of the MEO and IGSO satellites.
AB - In the case of medium earth orbit (MEO) and inclined geosynchronous orbit (IGSO) satellites, the orbit maneuver mission, in order to ensure satellites to enter the theoretically designed orbit as soon as possible, must be finished in the limited number of revolutions around the earth with the restrained propellant. This requires rapidly optimizing the whole orbit control strategy in terms of the actual orbit characteristics of the launched satellite. So that the optimal initial and final points of each thrust arc for satellites to maneuver can be determined precisely. This paper describes a numerical optimization algorithm, which can be applied to the strategy optimization in the orbit maneuver of MEO and IGSO satellites. This is a type of functional approximation method (FAM), which is specially adapted to cope with the single variable and equality/inequality constraints. In this paper, the modeling of the method is introduced to describe the basic approach. Then, the applications of this method and the results from the simulations are discussed in details. Compared with the conventionally adopted multidimensional exhaust algorithm, this method has the advantages of simplicity, uniformity, less dependence on the initial parameter zone, and much less computational effort for the optimal maneuver strategy generation of the MEO and IGSO satellites.
UR - http://www.scopus.com/inward/record.url?scp=78149421537&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:78149421537
SN - 9781563479373
T3 - 46th AIAA Aerospace Sciences Meeting and Exhibit
BT - 46th AIAA Aerospace Sciences Meeting and Exhibit
T2 - 46th AIAA Aerospace Sciences Meeting and Exhibit
Y2 - 7 January 2008 through 10 January 2008
ER -