固体火箭技术
固體火箭技術
고체화전기술
JOURNAL OF SOLID ROCKET TECHNOLOGY
2015年
2期
291-294,300
,共5页
SiC-ZrC%陶瓷前驱体%合成%裂解%高温%耐氧化
SiC-ZrC%陶瓷前驅體%閤成%裂解%高溫%耐氧化
SiC-ZrC%도자전구체%합성%렬해%고온%내양화
SiC-ZrC%preceramic%synthesis%pyrolysis%ultra-high temperature%anti-oxidation
通过Wurz-Fittig共缩聚反应合成了锆含量可调的聚锆硅烷树脂，作为SiC-ZrC陶瓷单组分前驱体。聚锆硅烷树脂具有聚合物基复合材料的加工工艺性能，具有热固化性(热固化温度110~200℃)，在氩气气氛中于1000~1400℃高温裂解生成SiC-ZrC复相陶瓷(陶瓷产率>60%)。聚锆硅烷树脂适合陶瓷基复合材料的聚合物浸渍裂解致密工艺(PIP)。基于前驱体聚合物的锆基复相陶瓷在空气中具有突出的耐高温氧化性，可望应用于超高音速大气层飞行器的耐高温、耐氧化陶瓷材料。
通過Wurz-Fittig共縮聚反應閤成瞭鋯含量可調的聚鋯硅烷樹脂，作為SiC-ZrC陶瓷單組分前驅體。聚鋯硅烷樹脂具有聚閤物基複閤材料的加工工藝性能，具有熱固化性(熱固化溫度110~200℃)，在氬氣氣氛中于1000~1400℃高溫裂解生成SiC-ZrC複相陶瓷(陶瓷產率>60%)。聚鋯硅烷樹脂適閤陶瓷基複閤材料的聚閤物浸漬裂解緻密工藝(PIP)。基于前驅體聚閤物的鋯基複相陶瓷在空氣中具有突齣的耐高溫氧化性，可望應用于超高音速大氣層飛行器的耐高溫、耐氧化陶瓷材料。
통과Wurz-Fittig공축취반응합성료고함량가조적취고규완수지，작위SiC-ZrC도자단조분전구체。취고규완수지구유취합물기복합재료적가공공예성능，구유열고화성(열고화온도110~200℃)，재아기기분중우1000~1400℃고온렬해생성SiC-ZrC복상도자(도자산솔>60%)。취고규완수지괄합도자기복합재료적취합물침지렬해치밀공예(PIP)。기우전구체취합물적고기복상도자재공기중구유돌출적내고온양화성，가망응용우초고음속대기층비행기적내고온、내양화도자재료。
Novel polyzirconosilane resin was prepared by Wurtz-Fittig copolymerization of amine stablized zirconium chloride, methyldichlorosilane and trimethylchlorosilanes, for the application of single source precursor of SiC-ZrC multicomponent ceramic (zirconium content was easily tailored).The polyzirconosilane resin was viscous liquid at ambient conditions,and its rehology was readily tailored catering to the composite process of PIP technique(Precursor-Infiltration-and-Pyrolysis).The polyzirconosilane resin underwent thermal cure at 110~200℃ to form yellowish solid,and the cured polyzirconosilane was transformed to SiC-ZrC monolith at a yield of >60% at 1 000~1 400℃. The polyzirconosilane derived SiC-ZrC exhibits ultra-high thermo-oxidation resistance in air atmophere at high temperatures.The polyzirconosilane preceramic resin would be an ideal candidate for ultra-high temperature ce-ramics in the applications of oxidation conditions.
