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成果報告書詳細
管理番号20170000000191
タイトル*平成28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2017/4/28
報告書年度2016 - 2016
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) FY2016 Annual Report

(1)Development of Simulator for Airframe Design

1) Multi-disciplinary optimization of the Aircraft Wing Design

To design high performance aircraft wing using CFRP for structural components, aerodynamics simulation and structural analysis were combined to evaluate the objective functions for multi-objective optimization. For the objective functions, flight range, structural weight, and safety margin function were considered. From this analysis, for the cases of applying CFRP and duralumin to the structural components, the advantage of applying CFRP was shown in the correlation of flight range and structural weight.

2) Development of the Finite Element Method Code using XFEM Elements

Geometrical nonlinear analysis functions were added to in-house FEM and XFEM codes using shell elements and they were verified and validated through static analyses of a CFRP stiffened plate.

3) Development of the Finite Element Method Code using S-FEM Method

A proto-type analysis code based on superposition version FEM (SFEM) was developed and several verification analyses were performed.

4) Validation of the Developed Tool

Validated the multi-disciplinary optimization tool through evaluation of the structural analysis models and the optimized solutions. Identified the flutter analysis validation target, and performed the detailed flutter analysis for comparison.

(2) Virtual Testing to Lessen the Cost of the Certification

1) Verification of the in-house CFRP progressive damage analysis XFEM code

A crack propagation code NLXP3D based on the eXtended finite element method (XFEM) was developed and validated with CFRP laminate open hole tension (OHT) tests.

2) Compression evaluation of impact damaged composite structure element

Compression of the C-shaped CFRP specimens with impact damages were evaluated experimentally and analytically.

(3)Development of a Simulator for Unsteady Aerodynamic Design with Icing

Three-dimensional clean wing and iced wing are analyzed by CFD simulations. The result shows good agreement with experiment in terms of the negative peak pressure seen at the vortex center, thus higher mesh resolution enables to simulate the vortex structure more clearly.

(4)Development and Experimental Verification of a Simulator for Designing Airframe Structures by Utilizing the Characteristics of Composites

In this fiscal year, assuming a tool of molding actually bent fiber bundle, (1) limit of fiber bending curve considering fiber breakage is set (2) fiber bundle width and fiber bundle interference are considered. As a result, the fracture stress after optimization improved by 7% over conventional CFRP, but it was lower than that of the last year's optimization result. It was necessary to change the width of the carbon fiber bundle to half of the current thickness. In addition, we developed simplified automated fiber placement machine for processing of tow-steered composites and conducted laminating verification tests for evaluating the effect of wrinkles. Moreover, the mechanical strength and their scatter of continuous-fiber reinforced CFRTP specimen produced using FDM type 3D printer was evaluated. The results elucidate that ineluctable fiber discontinuous inside the specimen has large effect on the strength.
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