The Experts below are selected from a list of 51 Experts worldwide ranked by ideXlab platform
Xianjia Chen - One of the best experts on this subject based on the ideXlab platform.
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An sequential optimization and aeroelastic Constraint transformation method for Strength-aeroelastic comprehensive design
Journal of Fluids and Structures, 2020Co-Authors: Zesheng Zhang, Xiaojun Wang, Xianjia ChenAbstract:Abstract With the development of modern aircraft technology, aeroelasticity plays a more and more crucial role in aircraft structural design. However, low efficiency of present aeroelastic analysis and optimization methods makes it difficult to apply in engineering practice. This paper presents a sequential optimization and aeroelastic Constraint transformation method (SOACTM) for comprehensive design of airplane wings with Strength and aeroelastic Constraints. Optimization with structural Strength Constraint and aeroelastic Constraint is transformed into a serial of cycles of decoupled structural Strength sub-optimizations and aeroelastic sub-optimizations based on sequential optimization strategy. In structural Strength sub-optimization, structural Strength Constraint is translated along its normal direction to make optimal design point satisfying aeroelastic Constraint. And the goal of aeroelastic sub-optimization is to find the translational distance of structural Strength Constraint. Aeroelastic Constraint is transformed to equivalent structural Strength Constraint via above approach. In this way, number of aeroelastic analyses in SOACTM is less than that in traditional optimization method and total computational time decreases. SOACTM is verified based on two examples. Traditional optimization method is applied for the sake of validation. The results demonstrated the accuracy and efficiency of SOACTM for wing comprehensive optimization considering both structural Strength and aeroelastic Constraints.
Zesheng Zhang - One of the best experts on this subject based on the ideXlab platform.
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An sequential optimization and aeroelastic Constraint transformation method for Strength-aeroelastic comprehensive design
Journal of Fluids and Structures, 2020Co-Authors: Zesheng Zhang, Xiaojun Wang, Xianjia ChenAbstract:Abstract With the development of modern aircraft technology, aeroelasticity plays a more and more crucial role in aircraft structural design. However, low efficiency of present aeroelastic analysis and optimization methods makes it difficult to apply in engineering practice. This paper presents a sequential optimization and aeroelastic Constraint transformation method (SOACTM) for comprehensive design of airplane wings with Strength and aeroelastic Constraints. Optimization with structural Strength Constraint and aeroelastic Constraint is transformed into a serial of cycles of decoupled structural Strength sub-optimizations and aeroelastic sub-optimizations based on sequential optimization strategy. In structural Strength sub-optimization, structural Strength Constraint is translated along its normal direction to make optimal design point satisfying aeroelastic Constraint. And the goal of aeroelastic sub-optimization is to find the translational distance of structural Strength Constraint. Aeroelastic Constraint is transformed to equivalent structural Strength Constraint via above approach. In this way, number of aeroelastic analyses in SOACTM is less than that in traditional optimization method and total computational time decreases. SOACTM is verified based on two examples. Traditional optimization method is applied for the sake of validation. The results demonstrated the accuracy and efficiency of SOACTM for wing comprehensive optimization considering both structural Strength and aeroelastic Constraints.
Xiaojun Wang - One of the best experts on this subject based on the ideXlab platform.
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An sequential optimization and aeroelastic Constraint transformation method for Strength-aeroelastic comprehensive design
Journal of Fluids and Structures, 2020Co-Authors: Zesheng Zhang, Xiaojun Wang, Xianjia ChenAbstract:Abstract With the development of modern aircraft technology, aeroelasticity plays a more and more crucial role in aircraft structural design. However, low efficiency of present aeroelastic analysis and optimization methods makes it difficult to apply in engineering practice. This paper presents a sequential optimization and aeroelastic Constraint transformation method (SOACTM) for comprehensive design of airplane wings with Strength and aeroelastic Constraints. Optimization with structural Strength Constraint and aeroelastic Constraint is transformed into a serial of cycles of decoupled structural Strength sub-optimizations and aeroelastic sub-optimizations based on sequential optimization strategy. In structural Strength sub-optimization, structural Strength Constraint is translated along its normal direction to make optimal design point satisfying aeroelastic Constraint. And the goal of aeroelastic sub-optimization is to find the translational distance of structural Strength Constraint. Aeroelastic Constraint is transformed to equivalent structural Strength Constraint via above approach. In this way, number of aeroelastic analyses in SOACTM is less than that in traditional optimization method and total computational time decreases. SOACTM is verified based on two examples. Traditional optimization method is applied for the sake of validation. The results demonstrated the accuracy and efficiency of SOACTM for wing comprehensive optimization considering both structural Strength and aeroelastic Constraints.
Chen Xianjia - One of the best experts on this subject based on the ideXlab platform.
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An sequential optimization and aeroelastic Constraint transformation method for Strength-aeroelastic comprehensive design
ACADEMIC PRESS LTD- ELSEVIER SCIENCE LTD, 2020Co-Authors: Zhang Zesheng, Wang Xiaojun, Chen XianjiaAbstract:With the development of modern aircraft technology, aeroelasticity plays a more and more crucial role in aircraft structural design. However, low efficiency of present aeroelastic analysis and optimization methods makes it difficult to apply in engineering practice. This paper presents a sequential optimization and aeroelastic Constraint transformation method (SOACTM) for comprehensive design of airplane wings with Strength and aeroelastic Constraints. Optimization with structural Strength Constraint and aeroelastic Constraint is transformed into a serial of cycles of decoupled structural Strength sub-optimizations and aeroelastic sub-optimizations based on sequential optimization strategy. In structural Strength sub-optimization, structural Strength Constraint is translated along its normal direction to make optimal design point satisfying aeroelastic Constraint And the goal of aeroelastic sub-optimization is to find the translational distance of structural Strength Constraint. Aeroelastic Constraint is transformed to equivalent structural Strength Constraint via above approach. In this way, number of aeroelastic analyses in SOACTM is less than that in traditional optimization method and total computational time decreases. SOACTM is verified based on two examples. Traditional optimization method is applied for the sake of validation. The results demonstrated the accuracy and efficiency of SOACTM for wing comprehensive optimization considering both structural Strength and aeroelastic Constraints. (C) 2019 Elsevier Ltd. All rights reserved
T M Chao - One of the best experts on this subject based on the ideXlab platform.
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optimum design of laminated composite foam filled sandwich plates subjected to Strength Constraint
International Journal of Solids and Structures, 1999Co-Authors: Taiyan Kam, Fengmin Lai, T M ChaoAbstract:Abstract Optimum design of laminated composite sandwich plates with both continuous (core thickness) and discrete (layer group fiber angles and thicknesses) design variables subjected to Strength Constraint is studied via a two-level optimization technique. The Strength of a sandwich plate is determined in a failure analysis using the Tsai–Wu failure criterion and the finite element method which is formulated on the basis of the layerwise linear displacement theory. In the first level optimization of the design process, the discrete design variables are temporarily treated as continuous variables and the corresponding minimum weight of the sandwich plate is evaluated subject to the Strength Constraint using a constrained multi-start global optimization method. In the second level optimization, the optimal solution obtained in the first level optimization is used in the branch and bound method for solving a discrete optimization problem to determine the optimal design parameters and the final weight of the plate. Failure test of laminated composite foam-filled sandwich plates with different lamination arrangements are performed to validate the proposed optimal design method. A number of examples of the design of laminated composite foam-filled sandwich plates are given to demonstrate the feasibility and applications of the proposed method.
