成果報告書詳細
管理番号20160000000727
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 次世代構造部材創製・加工技術開発事業の周辺技術・関連課題における小規模研究開発の実施 複合材構造合わせ部自動隙間埋め材料と工法の開発
公開日2016/10/7
報告書年度2015 - 2015
委託先名三菱重工業株式会社
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 material for filling gaps between bonding composites parts and processing(FY2015-FY2016)FY2015 Annual Report

The mechanical fasteners are used to assemble airframe composite parts in current aircraft structures. Recently, adhesive bonding instead of the mechanical joints is expected. However, material for filling gaps between bonding parts in bonding joints which has enough strength does not exist. As a result, much work hour for adjustment of the gap is needed and mechanical joint is used together to ensure the adhesiveness, and the required cost and weight saving are not achieved. The purpose of this research is to develop the material and to establish the basic of usability, to achieve the cost & weight saving and establish the high reliability adhesive bonding instead of current mechanical joints. Especially, to solve the following two subjects are main targets of this research. (1) To develop the material which has same level strength and stiffness as airframe composite material grade. (2) To define the required condition on assembly for stable hardening of the material. In the 2015, we performed the basic investigation of following two subjects to resolve the above targets. 1).Evaluation tests for candidate material. The evaluation tests for candidate material which is mixed chopped-carbon fiber and adhesive was performed. Data acquisition was performed by some trial material with setting carbon-fiber length, adhesives mixed ratio and method to the parameter for development of the material which satisfies the required properties. 2) Definition of required properties of the material. Simulation model with FEM (Finite Element Method) was created to define the required properties for the material. In the 2016, we will define the required properties for the material by simulation and actual assembly data, and advanced evaluation and improvements for candidate material. 1) Evaluation tests for candidate material. Evaluation and improvement for candidate material will be advanced because the usability is also important property of the material in addition to strength and stiffness. 2) Definition of required properties of the material. In this research, it is expected that the material will be used in wing structures between spars. Therefore, investigation with Wing FE model about deformation of entire model, applied loads and stresses at the bonding location will be performed. After investigation of the results, following steps will be performed. (1) Create the detail FE model of wing structures between spars with the material. (2) Define the target properties and specification (Strength, Stiffness) for development materials by investigation of the FE analysis results (load, forced displacement at bonding joint) and set corresponding material properties as parameter.
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