silicon carbide fiber 中文意思是什麼
silicon carbide fiber
解釋
碳化硅纖維-
Continuous carbon fiber reinforced silicon carbide ceramic matrix composites ( cysic ) are considered as the most promising thermal structural candidate materials for aerospace, energy and nuclear technologies etc. as a key technology for improving high - temperature structural applications of the materials, oxidation protection with anti - oxidation coating system had being paid more and more attentions
連續碳纖維增強碳化硅陶瓷基復合材料（ c sic ）是一種極具潛力的高溫結構復合材料，在航空航天、能源及核技術等領域有著廣闊的應用前景。為了推進材料的高溫應用，對防氧化塗層已開展了廣泛的研究，但是對目前廣泛採用的cvdsic塗層的缺陷控制鮮有研究。 -
Focusing on serious damage of carbon fibers in ceramic matrix composites ( cmcs ) prepared by precursor infiltration pyrolysis ( pip ), and with emphasis on carbon fiber reinforced silicon carbide composites ( cf / sic ) derived from polycarbosilane ( pcs ), the influences of raw materials ( including carbon fibers and precursors, etc. ) and preparing conditions on carbon fiber damage during the preparation of cf / sic composites were investigated systemically. pyrolysis process, fiber - matrix interface and carbon fiber damage process were observed by sem, tem, ir, xrd, xps and tq etc. the characterization method of carbon fiber damage degree was established and the models for carbon fiber damage mechanism were also established. the carbon fiber coatings and unidirectional cf / sic composites with coated carbon fibers were prepared and studied
本文針對先驅體浸漬裂解工藝制備陶瓷基復合材料過程中碳纖維損傷嚴重的問題，以聚碳硅烷（ pcs ）制備cf / sic復合材料為重點，採用sem 、 tem 、 ir 、 xrd 、 xps 、 tg等表徵手段，分析了先驅體裂解過程、纖維基體界面和碳纖維損傷過程，系統地研究了原料（碳纖維、先驅體等）和制備工藝條件等在cf / sic復合材料制備過程中對碳纖維損傷的影響，建立了碳纖維損傷程度的表徵方法和損傷機理模型，制備了纖維表面塗層並利用塗層碳纖維制備了單向cf / sic復合材料。 -
Influence of matrix modification on microstructure and properties of carbon fiber reinforced silicon carbide composites
基體改性對碳纖維增韌碳化硅復合材料結構與性能的影響 -
Carbon fiber reinforced silicon carbide composite ( c / sic ) is one of the most promising thermal - structure materials up to 1650 for aero engines. it is very significant to deeply understand the oxidation mechanisms and establish the oxidation kinetic models for the design and application of c / sic composites
C sic復合材料是一種有希望滿足航空發動機熱端部件1650工作溫度需要的結構材料，深入了解其氧化機理並建立氧化動力學模型對c sic復合材料的設計和應用具有重要的指導意義。
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