CARBON FIBER-REINFORCED COMPOSITE MATERIAL AND PREPREG
To provide a carbon fiber composite material which has characteristics of controlling the size of a structure of a conductive nano-filler, and is suitable as a structural material of an aircraft body having excellent resistance to lightning, and a prepreg which is an intermediate base material for o...
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| creator | OCHI TAKASHI HIRANABE RYUICHIRO |
| description | To provide a carbon fiber composite material which has characteristics of controlling the size of a structure of a conductive nano-filler, and is suitable as a structural material of an aircraft body having excellent resistance to lightning, and a prepreg which is an intermediate base material for obtaining the same.SOLUTION: A carbon fiber-reinforced composite material contains the following components [A], [BCDc], [Ec] and [Fc], wherein in a distribution curve obtained from a free volume radius obtained by a position annihilation lifetime measuring method and its presence probability, a difference between a maximum value and a minimum value of a pore radius is 0.09 nm or more, and the structure size of [Fc] is 0.6 μm or more. [A]: carbon fiber, [BDCc]: matrix resin, [Ec]: thermoplastic resin particles, and [Fc]: conductive nanofiller.SELECTED DRAWING: Figure 2
【課題】本発明は、導電性ナノフィラーのストラクチャーのサイズを制御することに特徴があり、優れた耐雷性を有する航空機機体の構造材料として好適な炭素繊維複合材料およびそれを得るための中間基材であるプリプレグを提供することを課題とする。【解決手段】次の構成要素［Ａ］、［ＢＣＤｃ］、［Ｅｃ］および［Ｆｃ］を含み、陽電子消滅寿命測定法で得られる自由体積半径とその存在確率から得られる分布曲線において、孔半径の最大値と最小値の差が０．０９ｎｍ以上であり、［Ｆｃ］のストラクチャーサイズが０．６μｍ以上である、炭素繊維強化複合材料。［Ａ］：炭素繊維［ＢＣＤｃ］：マトリックス樹脂［Ｅｃ］：熱可塑性樹脂粒子［Ｆｃ］：導電性ナノフィラー【選択図】図２ |
| format | Patent |
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【課題】本発明は、導電性ナノフィラーのストラクチャーのサイズを制御することに特徴があり、優れた耐雷性を有する航空機機体の構造材料として好適な炭素繊維複合材料およびそれを得るための中間基材であるプリプレグを提供することを課題とする。【解決手段】次の構成要素［Ａ］、［ＢＣＤｃ］、［Ｅｃ］および［Ｆｃ］を含み、陽電子消滅寿命測定法で得られる自由体積半径とその存在確率から得られる分布曲線において、孔半径の最大値と最小値の差が０．０９ｎｍ以上であり、［Ｆｃ］のストラクチャーサイズが０．６μｍ以上である、炭素繊維強化複合材料。［Ａ］：炭素繊維［ＢＣＤｃ］：マトリックス樹脂［Ｅｃ］：熱可塑性樹脂粒子［Ｆｃ］：導電性ナノフィラー【選択図】図２</description><language>eng ; jpn</language><subject>AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F,C08G ; CHEMISTRY ; COMPOSITIONS BASED THEREON ; GENERAL PROCESSES OF COMPOUNDING ; METALLURGY ; ORGANIC MACROMOLECULAR COMPOUNDS ; THEIR PREPARATION OR CHEMICAL WORKING-UP ; WORKING-UP</subject><creationdate>2023</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20231013&DB=EPODOC&CC=JP&NR=2023147961A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20231013&DB=EPODOC&CC=JP&NR=2023147961A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>OCHI TAKASHI</creatorcontrib><creatorcontrib>HIRANABE RYUICHIRO</creatorcontrib><title>CARBON FIBER-REINFORCED COMPOSITE MATERIAL AND PREPREG</title><description>To provide a carbon fiber composite material which has characteristics of controlling the size of a structure of a conductive nano-filler, and is suitable as a structural material of an aircraft body having excellent resistance to lightning, and a prepreg which is an intermediate base material for obtaining the same.SOLUTION: A carbon fiber-reinforced composite material contains the following components [A], [BCDc], [Ec] and [Fc], wherein in a distribution curve obtained from a free volume radius obtained by a position annihilation lifetime measuring method and its presence probability, a difference between a maximum value and a minimum value of a pore radius is 0.09 nm or more, and the structure size of [Fc] is 0.6 μm or more. [A]: carbon fiber, [BDCc]: matrix resin, [Ec]: thermoplastic resin particles, and [Fc]: conductive nanofiller.SELECTED DRAWING: Figure 2
【課題】本発明は、導電性ナノフィラーのストラクチャーのサイズを制御することに特徴があり、優れた耐雷性を有する航空機機体の構造材料として好適な炭素繊維複合材料およびそれを得るための中間基材であるプリプレグを提供することを課題とする。【解決手段】次の構成要素［Ａ］、［ＢＣＤｃ］、［Ｅｃ］および［Ｆｃ］を含み、陽電子消滅寿命測定法で得られる自由体積半径とその存在確率から得られる分布曲線において、孔半径の最大値と最小値の差が０．０９ｎｍ以上であり、［Ｆｃ］のストラクチャーサイズが０．６μｍ以上である、炭素繊維強化複合材料。［Ａ］：炭素繊維［ＢＣＤｃ］：マトリックス樹脂［Ｅｃ］：熱可塑性樹脂粒子［Ｆｃ］：導電性ナノフィラー【選択図】図２</description><subject>AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F,C08G</subject><subject>CHEMISTRY</subject><subject>COMPOSITIONS BASED THEREON</subject><subject>GENERAL PROCESSES OF COMPOUNDING</subject><subject>METALLURGY</subject><subject>ORGANIC MACROMOLECULAR COMPOUNDS</subject><subject>THEIR PREPARATION OR CHEMICAL WORKING-UP</subject><subject>WORKING-UP</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2023</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDBzdgxy8vdTcPN0cg3SDXL19HPzD3J2dVFw9vcN8A_2DHFV8HUMcQ3ydPRRcPRzUQgIcgUidx4G1rTEnOJUXijNzaDk5hri7KGbWpAfn1pckJicmpdaEu8VYGRgZGxoYm5pZuhoTJQiAFihKEw</recordid><startdate>20231013</startdate><enddate>20231013</enddate><creator>OCHI TAKASHI</creator><creator>HIRANABE RYUICHIRO</creator><scope>EVB</scope></search><sort><creationdate>20231013</creationdate><title>CARBON FIBER-REINFORCED COMPOSITE MATERIAL AND PREPREG</title><author>OCHI TAKASHI ; HIRANABE RYUICHIRO</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_JP2023147961A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; jpn</language><creationdate>2023</creationdate><topic>AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F,C08G</topic><topic>CHEMISTRY</topic><topic>COMPOSITIONS BASED THEREON</topic><topic>GENERAL PROCESSES OF COMPOUNDING</topic><topic>METALLURGY</topic><topic>ORGANIC MACROMOLECULAR COMPOUNDS</topic><topic>THEIR PREPARATION OR CHEMICAL WORKING-UP</topic><topic>WORKING-UP</topic><toplevel>online_resources</toplevel><creatorcontrib>OCHI TAKASHI</creatorcontrib><creatorcontrib>HIRANABE RYUICHIRO</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>OCHI TAKASHI</au><au>HIRANABE RYUICHIRO</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>CARBON FIBER-REINFORCED COMPOSITE MATERIAL AND PREPREG</title><date>2023-10-13</date><risdate>2023</risdate><abstract>To provide a carbon fiber composite material which has characteristics of controlling the size of a structure of a conductive nano-filler, and is suitable as a structural material of an aircraft body having excellent resistance to lightning, and a prepreg which is an intermediate base material for obtaining the same.SOLUTION: A carbon fiber-reinforced composite material contains the following components [A], [BCDc], [Ec] and [Fc], wherein in a distribution curve obtained from a free volume radius obtained by a position annihilation lifetime measuring method and its presence probability, a difference between a maximum value and a minimum value of a pore radius is 0.09 nm or more, and the structure size of [Fc] is 0.6 μm or more. [A]: carbon fiber, [BDCc]: matrix resin, [Ec]: thermoplastic resin particles, and [Fc]: conductive nanofiller.SELECTED DRAWING: Figure 2
【課題】本発明は、導電性ナノフィラーのストラクチャーのサイズを制御することに特徴があり、優れた耐雷性を有する航空機機体の構造材料として好適な炭素繊維複合材料およびそれを得るための中間基材であるプリプレグを提供することを課題とする。【解決手段】次の構成要素［Ａ］、［ＢＣＤｃ］、［Ｅｃ］および［Ｆｃ］を含み、陽電子消滅寿命測定法で得られる自由体積半径とその存在確率から得られる分布曲線において、孔半径の最大値と最小値の差が０．０９ｎｍ以上であり、［Ｆｃ］のストラクチャーサイズが０．６μｍ以上である、炭素繊維強化複合材料。［Ａ］：炭素繊維［ＢＣＤｃ］：マトリックス樹脂［Ｅｃ］：熱可塑性樹脂粒子［Ｆｃ］：導電性ナノフィラー【選択図】図２</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F,C08G CHEMISTRY COMPOSITIONS BASED THEREON GENERAL PROCESSES OF COMPOUNDING METALLURGY ORGANIC MACROMOLECULAR COMPOUNDS THEIR PREPARATION OR CHEMICAL WORKING-UP WORKING-UP |
| title | CARBON FIBER-REINFORCED COMPOSITE MATERIAL AND PREPREG |
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