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公开(公告)号：WO2005008097A3
公开(公告)日：2005-03-31
申请号：PCT/GB2004002940
申请日：2004-07-08
Applicant: DUNLOP AEROSPACE LTD , JOHNSON DAVID CALLUM
Inventor： JOHNSON DAVID CALLUM
IPC: C04B35/563 , C04B35/573 , C04B35/83 , C04B41/50 , C04B41/87 , F16D69/02
CPC classification number: C04B41/5058 , B32B2315/02 , C04B35/563 , C04B35/573 , C04B35/83 , C04B37/005 , C04B37/006 , C04B41/009 , C04B41/5059 , C04B41/87 , C04B2111/00362 , C04B2111/00612 , C04B2235/3821 , C04B2235/421 , C04B2235/428 , C04B2235/5268 , C04B2235/614 , C04B2235/6581 , C04B2235/728 , C04B2235/77 , C04B2235/80 , C04B2237/04 , C04B2237/086 , C04B2237/123 , C04B2237/36 , C04B2237/365 , C04B2237/385 , F16D69/023 , F16D2200/0047 , C04B41/4523 , C04B41/4556
Abstract: A composite article (21) for use in an aircraft brake heat pack, the article comprises a core layer (22) having a face portion and a wear layer (23) attached to the face portion, wherein the wear layer (23) has a density lower than the core layer (22). The core layer (22) may be fabricated from compressed C-C or from C-C impregnated with boron and/or silicon. The wear layer (23) may be fabricated from C-C.
Abstract translation: 一种用于飞机制动加热包的复合制品（21），所述制品包括具有表面部分和附着于所述表面部分的耐磨层（23）的芯层（22），其中所述耐磨层（23）具有 密度低于芯层（22）。 芯层（22）可以由压缩的C-C或者由浸渍有硼和/或硅的C-C制成。 耐磨层（23）可以由C-C制造。
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公开(公告)号：WO2005008097A2
公开(公告)日：2005-01-27
申请号：PCT/GB2004/002940
申请日：2004-07-08
Applicant: DUNLOP AEROSPACE LIMITED , JOHNSON, David, Callum
Inventor： JOHNSON, David, Callum
IPC: F16D69/02
CPC classification number: C04B41/5058 , B32B2315/02 , C04B35/563 , C04B35/573 , C04B35/83 , C04B37/005 , C04B37/006 , C04B41/009 , C04B41/5059 , C04B41/87 , C04B2111/00362 , C04B2111/00612 , C04B2235/3821 , C04B2235/421 , C04B2235/428 , C04B2235/5268 , C04B2235/614 , C04B2235/6581 , C04B2235/728 , C04B2235/77 , C04B2235/80 , C04B2237/04 , C04B2237/086 , C04B2237/123 , C04B2237/36 , C04B2237/365 , C04B2237/385 , F16D69/023 , F16D2200/0047 , C04B41/4523 , C04B41/4556
Abstract: A composite article (21) for use in an aircraft brake heat pack, the article comprises a core layer (22) having a face portion and a wear layer (23) attached to the face portion, wherein the wear layer (23) has a density lower than the core layer (22). The core layer (22) may be fabricated from compressed C-C or from C-C impregnated with boron and/or silicon. The wear layer (23) may be fabricated from C-C.
Abstract translation: 一种用于飞行器制动器热封件的复合制品（21），所述制品包括具有面部分的芯层（22）和附着到所述面部部分的耐磨层（23），其中所述耐磨层（23）具有 密度低于芯层（22）。 芯层（22）可以由压缩的C-C或从浸渍有硼和/或硅的C-C制成。 耐磨层（23）可以由C-C制成。
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公开(公告)号：WO2003007661A1
公开(公告)日：2003-01-23
申请号：PCT/JP2002/006893
申请日：2002-07-08
Inventor： 伊藤 康隆
IPC: H05B3/74
CPC classification number: H05B3/143 , B32B18/00 , B32B38/145 , B32B2311/08 , C04B35/56 , C04B35/5626 , C04B35/565 , C04B35/581 , C04B35/6264 , C04B35/62655 , C04B35/63 , C04B35/6303 , C04B35/634 , C04B35/645 , C04B37/025 , C04B2235/3201 , C04B2235/3217 , C04B2235/3227 , C04B2235/3284 , C04B2235/3296 , C04B2235/3409 , C04B2235/3418 , C04B2235/365 , C04B2235/3821 , C04B2235/3826 , C04B2235/3865 , C04B2235/606 , C04B2235/94 , C04B2237/04 , C04B2237/40 , C04B2237/403 , C04B2237/408 , C04B2237/50 , C04B2237/62 , C04B2237/704 , C23C16/46 , H01L21/67103 , H01L21/6833
Abstract: A ceramic heater for heating the whole of a semiconductor wafer uniformly by supporting it stably without causing it to bend. The ceramic heater having a heating body on the surface of or inside a disk−shaped ceramic base and having through holes for passing lifter pins therethrough in the ceramic base is characterized in that the number of through holes is three or more, and the through holes are formed in an area at a distant from the center of the ceramic base, the distance being over 1/2 of the distance from the center of the ceramic base to the edge.
Abstract translation: 一种陶瓷加热器，用于通过稳定地支撑整个半导体晶片而不使其弯曲而均匀地加热。 具有加热体的陶瓷加热器，其在盘状陶瓷基体的表面或内部具有用于使提升销穿过其的陶瓷基座的通孔，其特征在于通孔数量为三个以上，并且通孔 形成在远离陶瓷基底的中心的区域中，该距离超过从陶瓷基底的中心到边缘的距离的1/2以上。
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