摘要
介绍了C/C复合材料在日本固体火箭发动机喷管的应用情况,主要包括卫星远地点助推发动机用螺旋形状碳布铺层的2D-C/C扩张段、固体助推器及固体运载用3D-C/C喉衬。2D-C/C扩张段采用黏胶丝基碳纤维成型,M-V固体运载一级发动机C/C喉衬采用碳纤维三向正交圆筒编织结构,热等静压-石墨化致密,外径Ф1 100 mm,密度达1.95 g/cm3。C/C复合材料在固体及液体火箭发动机喷管延伸出口锥的应用是未来的发展方向。
The application state of C/C composites in solid rocket motor nozzle in Japan. The components in- clude a rosetta carbon fabric laminated 2D-C/C exit cone for satellite apogee boost motor, and 3D-C/C throat inserts for solid rocket booster and launch vehicle. The rayon based carbon fiber is adopted to make the 2D-C/C exit cone. The 3D-C/C throat insert, used as the 1 st stage of M-V solid rocket launch vehicle, has a dimension of Ф1100 mm in outer diameter and a density of 1.95 g/cm3. The 3D preform is orthogonally weaved in a cylinder structure, and then densified by a repeating heat isostatic pressure-graphitization cycles. Applications of C/C composites in both solid and liquid rocket motor nozzle extendable exit cones are future development trend in this area.
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2013年第2期13-17,共5页
Aerospace Materials & Technology
