JP6887576B1 - 一体型の加熱要素を備えた複合航空機構造 - Google Patents
一体型の加熱要素を備えた複合航空機構造 Download PDFInfo
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Abstract
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2007/0298663号明細書
(特許文献2) 米国特許第4,177,376号明細書
(特許文献3) 中国特許出願公開第107355752号明細書
(特許文献4) 米国特許出願公開第2015/0184333号明細書
(特許文献5) 米国特許出願公開第2014/0070054号明細書
20...積層体
20...複合要素
20...被加熱積層体
22...下面
25...上側の構造的な層
26...下側の構造的な層
28...絶縁層
28...第1の絶縁層
28...第2の絶縁層
30...加熱アセンブリ
30...加熱層
40...抵抗要素
40a...第1の抵抗要素
40b...抵抗要素
40c...抵抗要素
42a...第1の端部
44a...第2の端部
50...入力電極
50...第1の電極
52...出力電極
52...第2の電極
60...電源
70...コントローラ
75...センサー
120...積層体
120...複合要素
121...頂部
122...上方の面
123...下方の面
125...上側の構造的な層
126...下側の構造的な層
128...上側の電気絶縁層
130...加熱層
140...抵抗要素
150...入力電極
152...出力電極
220...複合要素
225...上側の構造的な層
226...下側の構造的な層
230...加熱層
250...第1のゾーン
255...抵抗要素
255A〜255E...抵抗要素
257...リード
258...テール
260...本体部
260...本体
265...導電要素
265...電極
265...第1の導体
266...導電要素
266...電極
266...第2の導体
270...第2の加熱ゾーン
275A〜275E...抵抗要素
277...リード
280...本体
285...第3の導電要素
286...第4の導電要素
287...第5の導電要素
290...第3の加熱ゾーン
295A〜295E...抵抗要素
Claims (11)
- 被加熱航空機構造であって、
複合構造であって、
前記航空機構造の耐力要素を形成する強化熱可塑性の上層であって、当該上層の熱可塑性材料は第1のガラス転移点を有する、強化熱可塑性の上層と、
前記航空機構造の耐力要素を形成する強化熱可塑性の下層であって、当該下層の熱可塑性材料は第2のガラス転移点を有する、強化熱可塑性の下層と、
熱可塑性のヒーター層であって、当該ヒーター層の熱可塑性材料は第3のガラス転移点を有し、当該熱可塑性のヒーター層は、
複数の導電繊維と、
前記導電繊維に電気接続された第1の電極と、
第2の電極であって、前記導電繊維が前記第1の電極と当該第2の電極間に電気経路を提供するよう、前記導電繊維に電気接続された第2の電極と
を有し、
前記熱可塑性のヒーター層の前記導電繊維は、前記上層および前記下層の強化繊維と実質的に同様である
熱可塑性のヒーター層と、
前記ヒーター層と前記上層間に設けられた第1の繊維強化熱可塑性の絶縁層であって、当該第1の絶縁層の熱可塑性材料は第4のガラス転移点を有する、第1の繊維強化熱可塑性の絶縁層と、
前記ヒーター層と前記下層間に設けられた第2の繊維強化熱可塑性の絶縁層であって、当該第2の絶縁層の熱可塑性材料は第5のガラス転移点を有する、第2の繊維強化熱可塑性の絶縁層と
を有し、
前記第3のガラス転移点は、前記第1および第2のガラス転移点から25パーセント以内である
複合構造と、
前記上層上における氷の形成を示す特徴を検出するよう動作可能なセンサーと、
前記センサーおよび電源に接続されたコントローラであって、前記第1の電極に提供される電力を制御するコントローラと
を有し、
前記第1の電極および前記導電繊維は、前記第1の電極に供給される電力が前記導電繊維に伝わることにより、前記複合構造を加熱して前記複合構造上における氷の形成を妨げ若しくは前記複合構造上で形成された氷を除去するうえで十分な抵抗加熱をもたらすよう、接続される
被加熱航空機構造。 - 請求項1記載の被加熱航空機構造において、前記コントローラは、前記センサーから受信された信号に応答して、前記第1の電極に提供される電力を制御するよう動作可能である被加熱航空機構造。
- 請求項1記載の被加熱航空機構造において、前記ヒーター層の前記複数の導電繊維は、単一方向性の炭素繊維強化熱可塑性材料を有するものである被加熱航空機構造。
- 請求項3記載の被加熱航空機構造において、前記導電繊維は、前記第1の電極に電気接続された第1の端部と、前記第2の電極に電気接続された第2の端部とを有し、前記炭素繊維の実質的にすべては、前記第1の端部から前記第2の端部まで連続的に延長するものである被加熱航空機構造。
- 請求項4記載の被加熱航空機構造において、前記ヒーター層は、前記第1および第2の電極間に複雑な経路を有するものである被加熱航空機構造。
- 請求項4記載の被加熱航空機構造において、前記ヒーター層とは独立して操作可能な第2のヒーター層と、当該第2のヒーター層を前記ヒーター層から電気的に絶縁する第3の絶縁層とを有するものである被加熱航空機構造。
- 請求項4記載の被加熱航空機構造において、前記複合構造は、エアフォイルの一部を有するものである被加熱航空機構造。
- 請求項1記載の被加熱航空機構造において、前記上層は、複数の炭素繊維強化熱可塑性の薄膜を有するものである被加熱航空機構造。
- 請求項1記載の被加熱航空機構造において、前記ヒーター層、前記上層、および前記下層の各々の熱可塑性材料は、隣接する層の前記熱可塑性材料と融合するものである被加熱航空機構造。
- 請求項1記載の被加熱航空機構造において、前記第3のガラス転移点は、前記第4および第5のガラス転移点から25%以内である被加熱航空機構造。
- 請求項1記載の被加熱航空機構造において、前記ヒーター層と、前記上層および前記下層の少なくとも一方とは、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被加熱航空機構造。
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