신뢰도와 관성모멘트를 고려한 인공위성 구성품 배치 최적화
Optimizing Component Layout Design Considering Reliability and Inertia Moment of a Satellite
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Satellites, which are the most important and expensive resources in the space industry, are typically nonrepairable systems. Accordingly, reliability is a very important metric in satellite design and development, and the reliability of components is affected by the operating temperature, that is, the failure rate of components increases in high-temperature environments. Additionally, agile maneuvering and attitude control are essential for space missions; thus, the moment of inertia (MoI) of a satellite should be reduced. Therefore, this study proposes a mixed-integer programming (MIP) model to optimize the layout design of the components by considering the reliability and MoI of a satellite. The MIP model consists of an objective function for balancing reliability and the MoI and several constraints for the spatial limitations of satellites, which facilitate the estimation of the operating temperature of the components and compliance with the upper MoI l imit the design. The MIP model was validated using an experimental example, assuming a cubic satellite with ten components. The optimal solution for the experimental example, searched using IBM's ILOG CPLEX 12.8.0.0 (Community version) software, adequately applied all the constraints. Based on the results of a heat transfer analysis using the finite difference method (FDM), the components were arranged to reduce the operating temperature.
Abstract
Satellites, which are the most important and expensive resources in the space industry, are typically nonrepairable systems. Accordingly, reliability is a very important metric in satellite design and development, and the reliability of components is affected by the operating temperature, that is, the failure rate of components increases in high-temperature environments. Additionally, agile maneuvering and attitude control are essential for space missions; thus, the moment of inertia (MoI) of a satellite should be reduced. Therefore, this study proposes a mixed-integer programming (MIP) model to optimize the layout design of the components by considering the reliability and MoI of a satellite. The MIP model consists of an objective function for balancing reliability and the MoI and several constraints for the spatial limitations of satellites, which facilitate the estimation of the operating temperature of the components and compliance with the upper MoI l imit the design. The MIP model was validated using an experimental example, assuming a cubic satellite with ten components. The optimal solution for the experimental example, searched using IBM's ILOG CPLEX 12.8.0.0 (Community version) software, adequately applied all the constraints. Based on the results of a heat transfer analysis using the finite difference method (FDM), the components were arranged to reduce the operating temperature.
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