固体火箭技术
固體火箭技術
고체화전기술
JOURNAL OF SOLID ROCKET TECHNOLOGY
2007年
6期
529-533
,共5页
刘红林%金志浩%郝志彪%曾晓梅
劉紅林%金誌浩%郝誌彪%曾曉梅
류홍림%금지호%학지표%증효매
炭/炭复合材料%低成本%沉积
炭/炭複閤材料%低成本%沉積
탄/탄복합재료%저성본%침적
carbon/carbon composites%low cost%deposition
简述了制备炭/炭复合材料的新工艺--化学液相沉积(CLD)的沉积原理.利用工业燃油作为裂解炭前驱体,炭纤维毡作为增强体,通过工艺参数控制得到低成本炭/炭复合材料.CLD工艺所得材料沉积密度1.6 g/cm3,轴向压缩强度92 MPa,等离子烧蚀率0.06 mm/s,与CVD工艺所得材料相近.与常规CVD工艺相比,CLD工艺制备的C/C复合材料在制备时间上缩短了4/5,致密速率快5倍多.所得基体裂解炭为粗糙层与光滑层结构(大部分为粗糙层结构).基体炭与炭纤维接合界面适中,且呈洋葱状分布,从而材料具有一定韧性.
簡述瞭製備炭/炭複閤材料的新工藝--化學液相沉積(CLD)的沉積原理.利用工業燃油作為裂解炭前驅體,炭纖維氈作為增彊體,通過工藝參數控製得到低成本炭/炭複閤材料.CLD工藝所得材料沉積密度1.6 g/cm3,軸嚮壓縮彊度92 MPa,等離子燒蝕率0.06 mm/s,與CVD工藝所得材料相近.與常規CVD工藝相比,CLD工藝製備的C/C複閤材料在製備時間上縮短瞭4/5,緻密速率快5倍多.所得基體裂解炭為粗糙層與光滑層結構(大部分為粗糙層結構).基體炭與炭纖維接閤界麵適中,且呈洋蔥狀分佈,從而材料具有一定韌性.
간술료제비탄/탄복합재료적신공예--화학액상침적(CLD)적침적원리.이용공업연유작위렬해탄전구체,탄섬유전작위증강체,통과공예삼수공제득도저성본탄/탄복합재료.CLD공예소득재료침적밀도1.6 g/cm3,축향압축강도92 MPa,등리자소식솔0.06 mm/s,여CVD공예소득재료상근.여상규CVD공예상비,CLD공예제비적C/C복합재료재제비시간상축단료4/5,치밀속솔쾌5배다.소득기체렬해탄위조조층여광활층결구(대부분위조조층결구).기체탄여탄섬유접합계면괄중,차정양총상분포,종이재료구유일정인성.
The densification mechanism of chemical liquid deposition (CLD) process was introduced. Taking industrial fuel as the precursor for carbon matrix and carbon fiber felt as the reinforcement, a low-cost C/C composite (C/C) was prepared. The results show that the properties of CLD C/C are the same as those of CVD C/C, i.e. the bulk density is up to 1.6 g/cm3 , the axial compressive strength can be up to 92 MPa, and the plasma ablation rate can be less than 0.06 mm/s. Compared with CVD process, the densification rate of CLD process can be increased about 5 times. Consequently, the deposition period can be shortened about 4/5. CLD carbon matrix includes rough laminar pyrocarbon ( RL Pyc) and smooth laminar pyrocarbon ( SL Pyc) ( mainly RL Pyc). The carbon matrix with an onion structure bonds with carbon fiber moderately, that is to say, the matrix/fiber interface of CLD C/C is better. So it can be predicated that the mechanical properties of CLD C/C can be improved.