F
Fei Niu
Researcher at China Academy of Launch Vehicle Technology
Publications - 7
Citations - 261
Fei Niu is an academic researcher from China Academy of Launch Vehicle Technology. The author has contributed to research in topics: Shell (structure) & Buckling. The author has an hindex of 5, co-authored 7 publications receiving 190 citations.
Papers
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Journal ArticleDOI
An integrated framework of exact modeling, isogeometric analysis and optimization for variable-stiffness composite panels
TL;DR: An integrated framework of exact modeling, isogeometric analysis and optimization for variable-stiffness panels is developed for the global optimum, and the proposed method is able to provide a more efficient optimum design with significant less computational cost compared to other traditional methods.
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Efficient Optimization of Cylindrical Stiffened Shells with Reinforced Cutouts by Curvilinear Stiffeners
TL;DR: In this article, an efficient optimization framework of cylindrical stiffened shells with reinforced cutouts by curvilinear stiffeners is proposed, where the numerical implementation asymptotic homogenization method is used to smear out the stiffeners in the far field.
Journal ArticleDOI
Buckling optimization of variable-stiffness composite panels based on flow field function
TL;DR: In this paper, the flow field function containing a uniform field and several vortex fields is used to represent the fiber path, and a bi-level optimization framework of variable-stiffness panels considering manufacturing constraints is then proposed.
Journal ArticleDOI
Simultaneous Buckling Design of Stiffened Shells with Multiple Cutouts
TL;DR: In this article, a multi-step optimization strategy for the integrated design of near and far fields away from cutouts is proposed, and the convergence criterion of buckling optimization is improved as a deformation-based index.
Patent
Efficient optimization method for variable stiffness composite material plate shell structure
TL;DR: In this article, a variable stiffness composite material plate shell structure based on an isogeometric method was proposed to reduce the development period of composite material structures in aerospace structures, and the buckling response of the composite material was analyzed.