JP2007504049A - 樹脂が注入された透明な外皮パネルおよびその製造方法 - Google Patents
樹脂が注入された透明な外皮パネルおよびその製造方法 Download PDFInfo
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- JP2007504049A JP2007504049A JP2006525435A JP2006525435A JP2007504049A JP 2007504049 A JP2007504049 A JP 2007504049A JP 2006525435 A JP2006525435 A JP 2006525435A JP 2006525435 A JP2006525435 A JP 2006525435A JP 2007504049 A JP2007504049 A JP 2007504049A
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- 229910052751 metal Inorganic materials 0.000 claims abstract description 51
- 239000002184 metal Substances 0.000 claims abstract description 51
- 239000000835 fiber Substances 0.000 claims abstract description 40
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 3
- 239000010936 titanium Substances 0.000 claims description 3
- 229910052719 titanium Inorganic materials 0.000 claims description 3
- 239000004593 Epoxy Substances 0.000 claims description 2
- 125000001931 aliphatic group Chemical group 0.000 claims description 2
- 239000013306 transparent fiber Substances 0.000 claims 6
- 239000004844 aliphatic epoxy resin Substances 0.000 claims 3
- 239000004744 fabric Substances 0.000 claims 2
- 239000011248 coating agent Substances 0.000 claims 1
- 238000000576 coating method Methods 0.000 claims 1
- 239000003365 glass fiber Substances 0.000 claims 1
- 239000000463 material Substances 0.000 description 4
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
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- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
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Abstract
Description
この発明は、透明な航空機外皮パネルに関し、より特定的には、樹脂が注入された透明な外皮パネルと、航空機および航空宇宙の応用例において用いるために特に十分に適合された当該樹脂が注入された透明な外皮パネルを製造する方法とに関する。
大抵の民間航空機の客席窓の大きさは比較的小さい。これは、一つには、現在の透明な窓材料の特性が制限されていること、さらに、航空機のフレーム内でこれらの窓を支持するのに必要な支持構造が重くて複雑であることによる。
移動プラットフォームにおいて用いるための透明な外皮パネルが提供される。透明な外皮パネルは複数の金属板を含む。繊維強化樹脂は、繊維金属積層板を形成する複数の金属板を少なくとも部分的に囲む。繊維強化樹脂は透明である。複数の金属板の各々の内部に切欠きが形成される。切欠きは、透明な外皮パネルにおける窓に対応する。
定するようには意図されないことが理解されるはずである。
以下の好ましい実施例の説明は、本質的に単に例示的なものであり、この発明、その応用例または用途を限定することを意図するものではない。
Claims (19)
- 移動プラットフォームにおいて用いるための透明な外皮パネルであって、
少なくとも1つの金属板と
前記少なくとも1つの金属板を少なくとも部分的に囲む繊維強化樹脂とを含み、前記繊維強化樹脂は透明であり、前記透明な外皮パネルはさらに、
前記少なくとも1つの金属板内に規定される開口部を含み、前記透明な樹脂は、前記開口部を充填して前記透明な外皮パネルにおいて窓を形成する、透明な外皮パネル。 - 少なくとも1つの金属板は、その中に形成される複数の穿孔を含み、前記穿孔は前記繊維強化樹脂が充填される、請求項1に記載の透明な外皮パネル。
- 前記金属板はアルミニウムで構成される、請求項1に記載の透明な外皮パネル。
- 前記金属板はチタンで構成される、請求項1に記載の透明な外皮パネル。
- 前記繊維強化樹脂は前記少なくとも1つの金属板を完全に覆う、請求項1に記載の透明な外皮パネル。
- 前記繊維強化樹脂は、互いの上に重なった複数の繊維網板を含む、請求項1に記載の透明な外皮パネル。
- 構造パネルを形成する方法であって、
フレーム構造を形成するために少なくとも1つの金属板を用いるステップを含み、前記フレーム構造は開口部を規定し、前記方法はさらに、
実質的に透明な繊維強化樹脂を前記金属板に塗布して、前記金属板を少なくとも部分的にコーティングし、前記開口部を充填するステップを含み、
前記実質的に透明な繊維強化樹脂が透明窓を形成する、方法。 - 前記実質的に透明な繊維強化樹脂を前記金属板に塗布するステップは、プリフォームを有する実質的に透明な樹脂を塗布するステップを含み、前記プリフォームは複数の繊維を含む、請求項7に記載の方法。
- 前記実質的に透明な繊維強化樹脂を塗布するステップは、脂肪族エポキシ樹脂を塗布するステップを含む、請求項8に記載の方法。
- 少なくとも1つの金属板を用いるステップは、アルミニウム板を用いるステップを含む、請求項7に記載の方法。
- 実質的に透明な繊維強化樹脂を塗布するステップは、繊維の織物を有する脂肪族エポキシ樹脂を塗布するステップを含み、前記繊維は、前記樹脂の屈折率と一致する屈折率を有する、請求項7に記載の方法。
- 実質的に透明な繊維強化樹脂を塗布するステップは、脂肪族エポキシ樹脂を塗布するステップを含む、請求項7に記載の方法。
- 透明な外皮パネルを製造する方法であって、
型を設けるステップと、
複数の繊維で構成されるプリフォームを設けるステップと、
複数の穿孔が中に形成されている金属板を設けるステップと、
前記金属板および前記プリフォームが互いの上に重なって整列するように前記プリフォームおよび前記金属板を前記型に挿入するステップと、
樹脂が前記金属板の前記穿孔を通って流れ、前記金属板および前記プリフォームを少なくとも部分的に覆うように前記樹脂を前記型に注入するステップとを含み、前記樹脂と前記繊維のプリフォームとは、前記外皮パネルにおける透明窓部分を形成するよう実質的に透明である、方法。 - 前記繊維のプリフォームはガラス繊維の織物を含む、請求項13に記載の、透明な外皮パネルの製造方法。
- プリフォームを設けるステップと、金属板を設けるステップと、前記プリフォームおよび前記金属板を前記型に挿入するステップとは、プリフォームと金属板とが交互になっている一連の層を作り出すよう繰返される、請求項13に記載の、透明な外皮パネルの製造方法。
- 前記繊維のプリフォームは前記樹脂の屈折率と一致する屈折率を有する、請求項13に記載の、透明な外皮パネルの製造方法。
- 前記樹脂は脂肪族エポキシを含む、請求項13に記載の、透明な外皮パネルの製造方法。
- 前記金属板はアルミニウムで構成される、請求項13に記載の、透明な外皮パネルの製造方法。
- 前記金属板はチタンで構成される、請求項13に記載の、透明な外皮パネルの製造方法。
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US10/655,257 US7300693B2 (en) | 2003-09-04 | 2003-09-04 | Resin infused transparent skin panel and method of making same |
PCT/US2004/028549 WO2005056383A2 (en) | 2003-09-04 | 2004-09-02 | A resin infused transparent skin panel and method of making same |
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JP4638434B2 JP4638434B2 (ja) | 2011-02-23 |
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US (3) | US7300693B2 (ja) |
EP (1) | EP1663776B1 (ja) |
JP (1) | JP4638434B2 (ja) |
CA (1) | CA2537945C (ja) |
WO (1) | WO2005056383A2 (ja) |
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US9751608B2 (en) | 2011-02-04 | 2017-09-05 | Mitsubishi Heavy Industries, Ltd. | Composite material structure, and aircraft wing and aircraft fuselage provided therewith |
JP2018158482A (ja) * | 2017-03-22 | 2018-10-11 | アイシン高丘株式会社 | 複合構造体の製造方法 |
Also Published As
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WO2005056383A2 (en) | 2005-06-23 |
US20050053765A1 (en) | 2005-03-10 |
CA2537945A1 (en) | 2005-06-23 |
US20070034743A1 (en) | 2007-02-15 |
WO2005056383A3 (en) | 2005-12-08 |
CA2537945C (en) | 2010-11-23 |
US7651756B2 (en) | 2010-01-26 |
WO2005056383A9 (en) | 2005-08-11 |
US7300693B2 (en) | 2007-11-27 |
US20080131661A1 (en) | 2008-06-05 |
EP1663776B1 (en) | 2012-11-07 |
JP4638434B2 (ja) | 2011-02-23 |
EP1663776A2 (en) | 2006-06-07 |
US7968170B2 (en) | 2011-06-28 |
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