JP2023103253A - 局所化されたプライ絶縁を伴う熱可塑性航空機構造および航空機構造を形成する方法 - Google Patents
局所化されたプライ絶縁を伴う熱可塑性航空機構造および航空機構造を形成する方法 Download PDFInfo
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- JP2023103253A JP2023103253A JP2023068907A JP2023068907A JP2023103253A JP 2023103253 A JP2023103253 A JP 2023103253A JP 2023068907 A JP2023068907 A JP 2023068907A JP 2023068907 A JP2023068907 A JP 2023068907A JP 2023103253 A JP2023103253 A JP 2023103253A
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- aircraft structure
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- laminate
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Abstract
Description
2...訳
10...複合航空機構造、航空機構造、アセンブリ
15...支持構造
20...前部スパー
22...上面
24...下面
25...後部スパー
27...上面
30...第1の端部リブ、第2の端部リブ
32...上面、上方フランジ
34...下方フランジ
35...中間リブ
37...上面、上方フランジ
38...下方フランジ
39...連結要素
40...上側のスキン、カバー、積層体
50...構造的な層
50a...構造的な層、第1の層
50b...構造的な層、第2の層
52...構造的な層
52a...構造的な層、第3の構造的な層
52b...構造的な層、第4の構造的な層
54...構造的な層
54a...構造的な層、第5の構造的な層
54b...構造的な層、第6の構造的な層
56...構造的な層
56a...構造的な層、第7の構造的な層
56b...構造的な層、第8の構造的な層
58...構造的な層
58a...構造的な層、最下層
58b...構造的な層、最下層
60...複数の絶縁要素
60a...第1の絶縁層
60b...第2の絶縁層
60c...第3の絶縁層
60d...第4の絶縁層
70...スパー絶縁要素
70...第2のスパー絶縁要素
80...端部リブ絶縁要素
82...絶縁要素、第1のセグメント
84...第2のセグメント
100...誘導溶接ヘッド、溶接ヘッド
Claims (21)
- 内部に配置された筐体を有する航空機構造であって、複合材料から形成されたスキンを含み、前記スキンは内部に前記筐体を提供するための形状および構成を有し、前記複合材料は、少なくとも1つの第1の材料層および少なくとも1つの第2の材料層の結合層を含み、前記第1の材料層は一方向炭素繊維強化熱可塑性材料を含み、前記第2の材料層は電気絶縁材料を含むものである、航空機構造。
- 請求項1記載の航空機構造において、前記少なくとも1つの第1の材料層は、複数の第1の材料層を含み、前記少なくとも1つの第2の材料層は、複数の第2の材料層を含み、前記第1の材料層と前記第2の材料層の選択された層が交互層のスタックとして配置されているものである、航空機構造。
- 請求項2記載の航空機構造において、複数の第1の材料層は、第1の方向に配向された前記一方向炭素繊維を有する第1の層と、前記第1の方向とは異なる第2の方向に配向された前記一方向炭素繊維を有する第2の層とを含むものである、航空機構造。
- 請求項3記載の航空機構造において、第1および第2の方向は、互いに対して0度の方向を向いているものである、航空機構造。
- 請求項3記載の航空機構造において、第1および第2の方向は、互いに対して45度の方向を向いているものである、航空機構造。
- 請求項3記載の航空機構造において、第1および第2の方向は、互いに対して90度の方向を向いているものである、航空機構造。
- 請求項2記載の航空機構造において、前記交互層のスタックは、前記スタックの第1の側に近接して印加される電磁場が、前記スタックの第1の側で一方向炭素繊維強化熱可塑性材料の選択された第1の層を溶融することなく、前記第1の側に対向する前記スタックの第2の側に位置する一方向炭素繊維強化熱可塑性材料の選択された第1の材料層を溶融できるように構成されている、航空機構造。
- 請求項2に記載の航空機構造において、前記交互層のスタックは、前記電気絶縁材料と、前記スタックの第1の側に近接して印加される電磁界との間の協働により、前記スタックの第1の側で一方向炭素繊維強化熱可塑性材料の選択された第1層を溶融することなく、前記第1の側に対向する前記スタックの第2の側に配置された一方向炭素繊維強化一方向炭素繊維の選択された第1の材料層を溶融できるように構成されている、航空機構造。
- 請求項1記載の航空機構造において、前記一方向炭素繊維が、前記第1の材料層を含む平面内にあるものである、航空機構造。
- 請求項1記載の航空機構造において、前記筐体内に配置された支持構造を備えるものである、航空機構造。
- 請求項10記載の航空機構造において、前記スキンは、前記支持構造の周りを包み込んで閉鎖型支持アセンブリを形成するものである、航空機構造。
- 請求項10記載の航空機構造において、前記支持構造は、スパー、リブ、またはそれらの組み合わせを備えるものである、航空機構造。
- 請求項1記載の航空機構造において、前記電気絶縁材料がガラスを含むものである、航空機構造。
- 請求項1記載の航空機構造において、前記スキンは、別個の上側スキン片と別個の下側スキン片が互いに接合されたものを含み、筐体を内部に配置した前記スキンが提供されるものである、航空機構造。
- 請求項1記載の航空機構造において、前記一方向炭素繊維強化熱可塑性材料は、プリプレグ材料である、航空機構造。
- 請求項1記載の航空機構造において、前記炭素繊維強化熱可塑性材料が、ポリアリールエーテルケトン(PAEK)系のポリマーを含むものである、航空機構造。
- 請求項1記載の航空機構造において、少なくとも1つの第1の材料層と少なくとも1つの第2の材料層との結合層が統合された積層体の形態で提供されるものである、航空機構造。
- 請求項1記載の航空機構造において、前記電気絶縁材料が、前記一方向炭素繊維強化熱可塑性材料と加熱溶融できる材料を含むものである、航空機構造。
- 請求項1記載の航空機構造において、前記第2の材料層が、加熱されることが意図された前記スキンの部分に対応するパターンを形成するように構成されるものである、航空機構造。
- 請求項19記載の航空機構造において、前記パターンが複数の開口部を有するものである、航空機構造。
- 請求項1記載の航空機構造において、前記第2の材料層がガラステープであるものである、航空機構造。
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- 2019-05-03 JP JP2020573564A patent/JP6986194B2/ja active Active
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JP2022025099A (ja) | 2022-02-09 |
BR122023020216A2 (pt) | 2024-01-16 |
WO2019213529A1 (en) | 2019-11-07 |
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US20200001569A1 (en) | 2020-01-02 |
EP3787965A4 (en) | 2022-05-04 |
KR102356284B1 (ko) | 2022-02-09 |
US10449749B1 (en) | 2019-10-22 |
US11440288B2 (en) | 2022-09-13 |
BR112020022321A2 (pt) | 2021-02-23 |
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US20230166478A1 (en) | 2023-06-01 |
US20190337261A1 (en) | 2019-11-07 |
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