JP6986194B2 - 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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- JP6986194B2 JP6986194B2 JP2020573564A JP2020573564A JP6986194B2 JP 6986194 B2 JP6986194 B2 JP 6986194B2 JP 2020573564 A JP2020573564 A JP 2020573564A JP 2020573564 A JP2020573564 A JP 2020573564A JP 6986194 B2 JP6986194 B2 JP 6986194B2
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- insulating
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- carbon fiber
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- Engineering & Computer Science (AREA)
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Description
この出願の発明に関連する先行技術文献情報としては、以下のものがある(国際出願日以降国際段階で引用された文献及び他国に国内移行した際に引用された文献を含む)。
(先行技術文献)
(特許文献)
(特許文献1) 米国特許出願公開第2002/0168184号明細書
(特許文献2) 米国特許第3,768,760号明細書
(特許文献3) 米国特許出願公開第2011/0168324号明細書
(特許文献4) 米国特許第5,059,377号明細書
(特許文献5) 米国特許出願公開第2013/0034684号明細書
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 (15)
- 複合航空機構造であって、
複数の長手方向に細長いスパーであって、その各々が、溶接ゾーンを形成する単一方向性または織物の炭素繊維強化熱可塑性材料の層を有した上方要素を有する、複数の長手方向に細長いスパーと、
前記複数のスパーと相互接続されてグリッドを形成する複数の細長いリブであって、各リブは、溶接ゾーンを形成する単一方向性または織物の炭素繊維強化熱可塑性材料の層を有した上方要素を有する、複数の細長いリブと、
前記スパーおよびリブのグリッドと連結された複合スキンであって、
炭素繊維強化熱可塑性材料の第1のプライであって、前記炭素繊維は第1の方向に配向された、第1のプライと、
炭素繊維強化熱可塑性材料の第2のプライであって、前記炭素繊維は前記第1の方向に配向され、前記第1のプライは当該第2のプライの上に重なりこれに直接連結された、第2のプライと、
炭素繊維強化熱可塑性材料の第3のプライであって、前記炭素繊維は、前記第1の方向を横断する第2の方向に配向された、第3のプライと、
炭素繊維強化熱可塑性材料の第4のプライであって、前記炭素繊維は前記第2の方向に配向され、前記第3のプライは当該第4のプライの上に重なりこれに直接連結された、第4のプライと、
炭素繊維強化熱可塑性材料の第5のプライであって、前記炭素繊維は、前記スパーおよび前記リブの前記上方要素の前記炭素繊維を横断する方向に配向された、第5のプライと、
電気絶縁材料で形成された複数の細長い絶縁要素であって、当該絶縁要素は、それぞれ長さおよび幅を有し、当該絶縁要素のうち少なくとも複数は、実質的に前記幅を超える長さを有し、当該絶縁要素は、当該絶縁要素が前記リブおよびスパーの前記上方要素の上に重なるよう、前記リブおよびスパーにより形成された前記グリッドと実質的に同様に構成されたグリッドを形成し、当該絶縁要素の前記グリッドは前記第2のプライと前記第3のプライ間に配置される、複数の細長い絶縁要素と
を有する複合スキンと
を有する複合航空機構造。 - 請求項1記載の航空機構造において、前記第1、第2、第3、第4、および第5のプライは、単一方向性の炭素繊維強化熱可塑性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、前記複合スキンは、炭素繊維強化熱可塑性材料の追加のプライを有し、前記絶縁要素のグリッドは第1のグリッドであり、前記複数の絶縁要素は、前記絶縁要素の第1のグリッドと実質的に同様に構成された第2のグリッドを形成し、前記第2のグリッドは、当該第2のグリッドが前記第1のグリッドに位置合わせされるよう、前記炭素繊維強化熱可塑性材料の追加のプライ間に配置され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、各絶縁要素は、熱可塑性材料のマトリックス内に埋め込まれたガラス繊維を有するものであり、前記航空機構造は、前記リブおよびスパーのグリッドと連結された第2の複合スキンを有するものである航空機構造。
- 請求項4記載の航空機構造において、各スパーおよびリブは、下方溶接ゾーンを形成する単一方向性の炭素繊維強化熱可塑性材料の層を有した下方要素を有するものである航空機構造。
- 請求項5記載の航空機構造において、前記第2のスキンは、前記リブおよびスパーの前記下方要素と連結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、前記絶縁要素は、前記第5のプライが誘導溶接ヘッドにより融点を超える温度に加熱された場合、前記第1〜第4のプライの熱可塑性材料が前記融点未満に保たれるよう構成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、前記第5のプライの前記熱可塑性材料は融点を有し、前記絶縁要素は、前記第5のプライが、当該第5のプライの一部を前記融点を超えて加熱するうえで十分な電磁場にばく露した場合、前記第2および第3のプライの前記融点を超える加熱を妨げるよう構成されるものである航空機構造。
- 複合航空機構造であって、
複数の長手方向に細長いスパーと、
前記複数のスパーと連結されてグリッドを形成する複数の細長いリブと、
複合スキンであって、
複数の構造的な層であって、その各々が炭素繊維強化熱可塑性薄膜で形成された、複数の構造的な層と、
電気絶縁材料で形成された複数の絶縁要素であって、当該絶縁要素は複数の絶縁グリッドを形成し、前記絶縁グリッドは互いに位置合わせされ、前記絶縁グリッドは前記構造的な層間に配置される、複数の絶縁要素と、
炭素繊維強化熱可塑性薄膜で形成される溶接層と
を有する複合スキンと、
単一方向性の炭素繊維強化熱可塑性材料の層を有する複数の連結要素であって、各連結要素は、前記スパーまたは前記リブの1つと連結される、複数の連結要素と
を有し、
前記溶接層の炭素繊維は第1の方向に配向され、前記連結要素の炭素繊維は、前記第1の方向を横断する第2の方向に配向され、
前記溶接層は前記連結要素の上に重なり、それと連結される
複合航空機構造。 - 請求項9記載の航空機構造において、各絶縁要素は、熱可塑性材料のマトリックス内に埋め込まれたガラス繊維を有するものである航空機構造。
- 請求項9記載の航空機構造において、前記絶縁要素は、前記スパーの上に重なる複数の細長いスパー絶縁体を有するものである航空機構造。
- 請求項11記載の航空機構造において、前記絶縁要素は、前記リブの上に重なる複数の細長いリブ絶縁体を有し、当該リブ絶縁体は、前記スパー絶縁体の長さより短い長さを有するものである航空機構造。
- 請求項12記載の航空機構造において、前記リブ絶縁体は、前記スパー絶縁体の上に実質的に重なることなく、前記スパー絶縁体間にわたり延長するものである航空機構造。
- 請求項12記載の航空機構造において、前記スパー絶縁体は互いに離間されるものである航空機構造。
- 請求項9記載の航空機構造において、前記構造的な層の前記熱可塑性材料は、ポリアリールエーテルケトン類の半結晶性の熱可塑性材料を有するものである航空機構造。
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