JP2020055447A - 複合材料製航空機用部品およびその製造方法 - Google Patents
複合材料製航空機用部品およびその製造方法 Download PDFInfo
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- JP2020055447A JP2020055447A JP2018187994A JP2018187994A JP2020055447A JP 2020055447 A JP2020055447 A JP 2020055447A JP 2018187994 A JP2018187994 A JP 2018187994A JP 2018187994 A JP2018187994 A JP 2018187994A JP 2020055447 A JP2020055447 A JP 2020055447A
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- composite material
- aircraft
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- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Manufacturing & Machinery (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Textile Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
Description
まず、本開示に係る複合材料製航空機用部品の一例について、図1(A)〜(C)を参照して具体的に説明する。
Tc=Wf/ρf/Vf ・・・ (1)
Vf=ρr×(1−Wr/100)/{ρf−(ρf−ρr)×(1−Wr/100)} ・・・ (2)
次に、本開示に係る複合材料製航空機用部品の製造方法について、図3(A),(B)および図4(A)〜(D)を参照して具体的に説明する。
次に、図5、図6(A),(B)、並びに図7(A)〜(C)を参照して、実際に製造した航空機用部品の一例について説明する。図5は、図1(C)に模式的に示す開切込部13bの実際の一例であり、このような開切込部は、図6(A)に示すT字状部材の基板部の表面、あるいは、図7(A)に示すL字状部材の表面に観察される。図5に示す例は、航空機用部品の表面に形成された開切込部13bの一例であり、本開示に係る航空機用部品の特徴的な構成である。
11:平板成形体
12:複合材料層
13a:切込部
13b:開切込部
14:強化繊維
15:接合部
20:航空機用部品
20a:基板部
20b:立設部
20c:凸部
20d:湾曲部
20e:薄板部
21,21A〜21D:T字状部材
22,22A,22B:凸状部材
23:湾曲部材
24:一次元湾曲部材
25:二次元湾曲部材
50:従来の航空機用部品
Claims (10)
- 強化繊維および樹脂組成物から少なくとも構成される複合材料層が複数積層された積層構造を有するとともに、立体構造として立設部、凸部および湾曲部の少なくともいずれかを有する、複合材料製航空機用部品であって、
それぞれの前記複合材料層では、前記強化繊維が、接合部を含まない単一の連続繊維で構成され、かつ、部分的な切込部を含み、
同一の積層構造を有し立体構造を有さない平板成形体の厚さを基準厚さとしたときに、前記積層構造を保持した状態で前記基準厚さよりも厚さが小さい薄板部を含み、
さらに、前記強化繊維には、前記切込部が開いた状態である開切込部が含まれていることを特徴とする、
複合材料製航空機用部品。 - 前記凸部が1つ以上存在することを特徴とする、
請求項1に記載の複合材料製航空機用部品。 - 前記湾曲部は、一次元の湾曲または二次元の湾曲を含むものであることを特徴とする、
請求項1または2に記載の複合材料製航空機用部品。 - 前記基準厚さを100%としたときに、前記薄板部の厚さは60%以上100%未満であることを特徴とする、
請求項1から3のいずれか1項に記載の複合材料製航空機用部品。 - 前記樹脂組成物は、熱硬化性樹脂または熱可塑性樹脂を含有するものであることを特徴とする、
請求項1から4のいずれか1項に記載の複合材料製航空機用部品。 - 前記強化繊維は炭素繊維であることを特徴とする、
請求項1から5のいずれか1項に記載の複合材料製航空機用部品。 - 前記基準厚さは、前記平板成形体における繊維体積含有率と、当該平板成形体の硬化前の複合材料積層体を構成する、硬化前のそれぞれの複合材料層における繊維目付と、を用いて算出された、当該平板成形体の算出厚さであることを特徴とする、
請求項1から6のいずれか1項に記載の複合材料製航空機用部品。 - 強化繊維および樹脂組成物から構成される複合材料層を複数積層して積層体を形成し、
当該積層体を成形型に設置して加熱加圧成形する、複合材料製航空機用部品の製造方法であって、
前記複合材料層として、部分的な切込部を複数含む切込領域を有し、かつ、接合部を含まない単一の強化繊維および樹脂組成物から少なくとも構成されるものが用いられ、
前記成形型として、雌型部およびこれに嵌合する雄型部を備え、前記雄型部および前記雌型部の間に形成されるキャビティには、立体構造として立設部、凸部および湾曲部の少なくともいずれかを形成するための領域が含まれ、
前記積層体を前記成形型に設置したときには、前記立体構造に対応する部位およびその隣接部位の少なくとも一方に前記切込領域が位置するように、当該切込領域を前記複合材料層に形成することを特徴とする、
複合材料製航空機用部品の製造方法。 - 前記切込領域を有する複合材料層を第一複合材料層としたときに、
前記複合材料層として、さらに、前記切込領域を有さず、接合部を含まない単一の強化繊維および樹脂組成物から構成される第二複合材料層が用いられることを特徴とする、
請求項8に記載の複合材料製航空機用部品の製造方法。 - 前記切込領域は、前記複合材料層の一部であるか、当該複合材料層全体に及んでいることを特徴とする、
請求項8または9に記載の複合材料製航空機用部品の製造方法。
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EP19868571.1A EP3736203A4 (en) | 2018-10-03 | 2019-10-02 | COMPOSITE COMPONENT FOR AIRCRAFT AND METHOD FOR MANUFACTURING IT |
PCT/JP2019/038887 WO2020071417A1 (ja) | 2018-10-03 | 2019-10-02 | 複合材料製航空機用部品およびその製造方法 |
US17/218,170 US20210229377A1 (en) | 2018-10-03 | 2021-03-31 | Composite-material aircraft part and method of manufacturing same |
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