摘要
分别采用PAN基及粘胶丝基炭布作为增强体,进行了一种新型的炭/炭 酚醛双基体烧蚀防热层板材料的探索研究。结果表明,炭/炭 酚醛双基体材料的密度基本与炭/酚醛材料的密度相当;弯曲强度与炭/酚醛材料及C/C材料相当,弯曲模量稍高于炭/酚醛材料而低于C/C材料。其层剪强度低于炭/酚醛材料和C/C材料,降低了30%～40%。炭/炭 酚醛双基体材料保持了炭/酚醛材料低热导率的特点,热膨胀系数低于炭/酚醛材料,但高于C/C材料,其线烧蚀率比炭/酚醛材料降低20%～40%。与PAN基炭布增强材料相比,粘胶丝基炭布表现出层剪强度高、密度低和模量低的优点,但热膨胀系数大和线烧蚀率较大。
A novel carbon fabric reinforced carbon and phenolics bi-matrix laminates(CC-P) were fabricated with PAN-based carbon fabric and rayon-based carbon fabric as reinforcements. The results show that the CC-P has very close density to carbonphenolics(CP) ablative material. Its bending strength is correspond to that of CP and carboncarbon(CC) composites, and its bending modulus is considerably higher than that of CP, but lower than that of CC. Its interlaminar shear strength(ILSS) is reduced from 30% to 40% in comparison with that of CP and CC. The CC-P has the same low thermal conductivity characteristics as CP. Its coefficient of thermal expansion(CTE) is lower than that of CP, but higher than that of CC, and its linear ablation ratio is decreased by 20% to 40% compared with that of CP. As compared with PAN carbon fabric reinforced composites, rayon reinforced ablative material has many advantages, such as high ILSS, low density and low modulus, but it is has high CTE and linear ablation (ratio).
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2004年第2期136-140,共5页
Journal of Solid Rocket Technology
关键词
烧蚀材料
炭/炭
炭/酚醛
层剪强度
复合材料
ablative material
carboncarbon
carbonpheno lics
interlaminar shear strength
