TY - GEN
T1 - Based on central composite design method satellite mission design
AU - Deng, Li
AU - Han, Chao
AU - Cao, Jinbin
AU - Qi, Rui
PY - 2012
Y1 - 2012
N2 - In conceptual design phase, the goal of the satellite mission design is to gain a feasible solution. Satellite mission design involves many domains that are coupling with each other. Usually the domain factors are nonlinear and the interactive effects exist. Therefore, it is difficult to find the best solution if only analyzed one domain factors' main effect. Coupling relationship between the domains must be considered. During the satellite design process, the design team should determine which factors have main effects and which factors have interactive effects. According to the response surfaces, the design team can select the best feasible solution. In this paper, a central composite design method was described. The central composite design method is an optimization method based on statistical data analysis. And it is also a response surface design method. In this method, the design factors are divided into two subsets. One subset is used to estimate the linear and interactive effects. The other subset is used to estimate the curve effects. This method uses the minimum tests to gain the variables and variance information. And it can provide main effect, interactive effect in a graphical fashion. An earth observation satellite mission is as an example. The mission objectives include two points. One is to maximize the best observation days of a region, and the other is to minimize the cost. The simulation models are established on orbit prediction, the visible field, data transmission, and satellite cost. 8 design factors are selected and 145 tests are performed. The simulation results show the orbit variables have main effect and interactive effect on best observation days, but have extremely small effect on the cost. The payload aperture diameter has the main effect on the cost. However, the combination of a small aperture diameter and a high orbit altitude leads to the violation of the resolution constraint. The central composite design method is dependent for each domain design model. This method is able to steer the choices of the design team in a graphical fashion.
AB - In conceptual design phase, the goal of the satellite mission design is to gain a feasible solution. Satellite mission design involves many domains that are coupling with each other. Usually the domain factors are nonlinear and the interactive effects exist. Therefore, it is difficult to find the best solution if only analyzed one domain factors' main effect. Coupling relationship between the domains must be considered. During the satellite design process, the design team should determine which factors have main effects and which factors have interactive effects. According to the response surfaces, the design team can select the best feasible solution. In this paper, a central composite design method was described. The central composite design method is an optimization method based on statistical data analysis. And it is also a response surface design method. In this method, the design factors are divided into two subsets. One subset is used to estimate the linear and interactive effects. The other subset is used to estimate the curve effects. This method uses the minimum tests to gain the variables and variance information. And it can provide main effect, interactive effect in a graphical fashion. An earth observation satellite mission is as an example. The mission objectives include two points. One is to maximize the best observation days of a region, and the other is to minimize the cost. The simulation models are established on orbit prediction, the visible field, data transmission, and satellite cost. 8 design factors are selected and 145 tests are performed. The simulation results show the orbit variables have main effect and interactive effect on best observation days, but have extremely small effect on the cost. The payload aperture diameter has the main effect on the cost. However, the combination of a small aperture diameter and a high orbit altitude leads to the violation of the resolution constraint. The central composite design method is dependent for each domain design model. This method is able to steer the choices of the design team in a graphical fashion.
UR - http://www.scopus.com/inward/record.url?scp=84883536868&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84883536868
SN - 9781622769797
T3 - Proceedings of the International Astronautical Congress, IAC
SP - 9299
EP - 9304
BT - 63rd International Astronautical Congress 2012, IAC 2012
T2 - 63rd International Astronautical Congress 2012, IAC 2012
Y2 - 1 October 2012 through 5 October 2012
ER -