JP6951112B2 - 強力接着層を介して装飾層をパネルに結合するための方法及び装置 - Google Patents
強力接着層を介して装飾層をパネルに結合するための方法及び装置 Download PDFInfo
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Description
Claims (20)
- 壁、輸送手段、荷物入れ、ライニング又は調度品の表面を形成するように構成されたパネル(306)と、
前記パネル(306)に固着された強力接着層(302)と、
前記パネルに固着された前記強力接着層に固着されたライナー(308)と、
前記強力接着層(302)に固着された前記ライナーに、第2の接着層(310)を介して取り外し可能に結合された第1の装飾層(304)とを備える装置であって、
前記強力接着層が、ガスまたは蒸気のうちの少なくとも一方が前記パネル(306)から漏出することを阻害し、それによってガスまたは蒸気のうちの少なくとも一方が前記第1の装飾層(304)に対して圧力をかけることを抑止し、それによって前記第1の装飾層の一部が前記パネル(306)から剥離することを抑止する、装置。 - 前記第2の接着層(310)は前記ライナー(308)に取り外し可能に結合され、それによって前記第1の装飾層(304)及び前記第2の接着層(310)を前記ライナー(308)に対して再配置することを可能にする、請求項1に記載の装置。
- 前記第2の接着層(310)は前記ライナー(308)に取り外し可能に結合され、それによって前記第1の装飾層(304)及び前記第2の接着層(310)を、第2の装飾層及び第3の接着層と置換することを可能にし、前記第2の装飾層を前記第3の接着層を介して前記ライナーに結合することを可能にする、請求項1に記載の装置。
- 前記第2の装飾層(304)が、前記第1の装飾層とは異なる装飾パターンを含む、請求項3に記載の装置。
- 前記ライナー(308)が、前記第2の接着層が前記強力接着層(302)と係合することを抑止する、請求項1に記載の装置。
- 前記強力接着層(302)が、エポキシ系の半硬質材料からなる、請求項1に記載の装置。
- 前記強力接着層(302)が架橋材料からなる、請求項1に記載の装置。
- 前記ライナー(308)は、前記第2の接着層(310)が前記ライナーから結合解除されたときに、前記第2の接着層の残留物が前記ライナーに固着したままになることを抑止する材料からなる、請求項1に記載の装置。
- 前記ライナー(308)は、ポリエチレンテレフタラート、ポリビニリデンフルオライド、またはフッ化ビニル樹脂からなる、請求項1に記載の装置。
- 前記第2の接着層(310)が感圧接着剤からなる、請求項1に記載の装置。
- 前記第1の装飾層(304)及び前記第2の接着層(310)は、耐火材料からなり、前記パネル(306)は、航空機の表面の一部であって前記航空機に耐火性を提供する、請求項1に記載の装置。
- 壁、輸送手段、荷物入れ、ライニング又は調度品の表面を形成するように構成されたパネルと、
前記パネルに固着された第1の結合手段と、
前記パネルに固着された前記第1の結合手段に固着されたライニング手段と、
前記第1の結合手段に固着された前記ライニング手段に、第2の結合手段を介して取り外し可能に結合された第1のパネル装飾手段とを備える装置であって、
前記第1の結合手段が、ガスまたは蒸気のうちの少なくとも一方が前記パネルから漏出することを阻害し、それによってガスまたは蒸気のうちの少なくとも一方が前記第1のパネル装飾手段に対して圧力をかけることを抑止し、それによって前記第1のパネル装飾手段の一部が前記パネルから剥離することを抑止する、装置。 - 前記第2の結合手段は前記ライニング手段に取り外し可能に結合され、それによって前記第1のパネル装飾手段及び前記第2の結合手段を前記ライニング手段に対して再配置することを可能にする、請求項12に記載の装置。
- 前記第2の結合手段は前記ライニング手段に取り外し可能に結合され、それによって前記第1のパネル装飾手段及び前記第2の結合手段を、第2の装飾手段及び第3の結合手段と置換することが可能になり、前記第2の装飾手段を前記第3の結合手段を介して前記ライニング手段に結合することを可能にする、請求項12に記載の装置。
- 前記ライニング手段が、前記第2の結合手段が前記第1の結合手段と係合することを抑止する、請求項12に記載の装置。
- 強力接着層を、壁、輸送手段、荷物入れ、ライニング又は調度品の表面を形成するように構成されたパネルに固着することと、
ライナーを前記パネルに固着された前記強力接着層に固着することと、
第1の装飾層を、前記強力接着層に固着された前記ライナーに、第2の接着層を介して結合すること
を含む方法であって、
前記強力接着層が、ガスまたは蒸気のうちの少なくとも一方が前記パネルから漏出することを阻害し、それによってガスまたは蒸気のうちの少なくとも一方が前記第1の装飾層に対して圧力をかけることを抑止し、それによって前記第1の装飾層の一部が前記パネルから剥離することを抑止する、方法。 - 前記第2の接着層を前記ライナーから結合解除することをさらに含み、それによって前記第1の装飾層及び前記第2の接着層を前記ライナーに対して再配置することを可能にすることをさらに含む、請求項16に記載の方法。
- 前記第2の接着層を前記ライナーから結合解除し、それによって前記第1の装飾層を前記ライナーから取り外すことと、
第2の装飾層及び第3の接着層を前記ライナーに結合し、それによって第1の装飾層及び前記第2の接着層を前記第2の装飾層及び前記第3の接着層と置換することと
をさらに含む、請求項16に記載の方法。 - 前記ライナーを前記強力接着層に結合することが、前記第2の接着層が前記強力接着層と係合することを抑止する、請求項16に記載の方法。
- 前記第1の装飾層を前記パネルに結合することは、前記第1の装飾層を航空機の表面に結合することを含み、前記第1の装飾層及び前記第2の接着層は耐火材料からなり、前記航空機に耐火性を提供する、請求項16に記載の方法。
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