成果報告書詳細
管理番号20160000000724
タイトル*平成27年度中間年報 次世代構造部材創製・加工技術開発 研究開発項目(5) 航空機用構造設計シミュレーション技術開発
公開日2016/9/21
報告書年度2015 - 2015
委託先名国立大学法人東北大学
プロジェクト番号P15006
部署名材料・ナノテクノロジー部
和文要約
英文要約Title: Development of Technologies for Next-Generation Structure Component Creation and Processing, Development of Structure Design Simulation Technologies for Aircrafts (FY2015-2017) FY2015 Annual Report

(1) Development of Simulator for Airframe Design 1) An in-house finite volume code for solving the full potential equation is developed to obtain transonic flowfields for a rapid estimation of wing flutter boundary. 2) A numerical simulation tool, which combines aero-dynamics simulation with structural analysis, was developed to evaluate the performance of the various wing shapes. 3) A multi-objective optimization method for an appropriate wing structure was developed. 4) An in-house finite element code using shell and beam elements referred to as NLFEASTR was developed. The code can perform static, eigenvalue for natural frequency and buckling load, and transient analyses. 5) Defined the tool requirements such as design parameters, constraints and objective functions. Defined the verification concepts for individual and overall analytical results using aerodynamic and structural analyses typically used in the aircraft development. (2) Virtual Testing to Lessen the Cost of the Certification 1) An analysis tool based on explicit dynamic finite element method for open-hole tensile tests of CFRP laminate was developed. Simulated stress-strain relationship and tensile strength agree well with experimental data. 2) An analytical solution of the response of laminated composites against low velocity and large mass impact is derived based on Mindlin plate theory. 3) The damage initiation and growth mechanisms at the stress concentration sites are experimentally and numerically studied to establish reliable numerical methods for damage prediction. 4) Crack propagation codes based on the eXtended finite element method (XFEM) for 2D and quasi-3D problems referred to as NLXT2D and NLXP3D, respectively, were developed. The paper regarding the developed codes has been published in Computers and Structures. 5) Defined the tool requirements such as design parameters, constraints and objective functions. Defined the step-by-step concept of verifying the simulation based on the structural coupon to component level tests. (3) Development of a Simulator for Unsteady Aerodynamic Design with Icing. The clean airfoil and the iced airfoil of NACA23012 have been analyzed by CFD. Comparing the clean airfoil and the iced airfoil, icing decreased the lift and the stall angle of attack. (4) Development and Experimental Verification of a Simulator for Designing Airframe Structures by Utilizing the Characteristics of Composites. To develop a simulator for designing airframe structures by utilizing the characteristics of composites, we investigated an optimized composite structure by using tow-steering tape layup and a streamline model in an ideal fluid. In addition, we designed and assembled a lay-up machine for the tow-steered composites and investigated its layup accuracy by fabricating a unidirectional specimen.
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