CAJ | 학술논문

针对空天飞行器热防护系统抗冲击性能，基于已得实验结果对冲击载荷作用的平纹编织C／SiC复合材料薄板碎片云团结构定性建模及分析，获得 C ／SiC 碎片云中特殊轴向柱状高能区。基于 Autodyn 正交各向异性材料模型推导材料参数并与实验对比，验证模型及参数的合理性。据 C ／SiC 碎片云团特点选取弹丸剩余速度、碎片云轴向平均速度及分散角作为主要特征参数，并以球形 Al 弹丸薄板撞击模型为对象，对超高速撞击多种工况 C ／SiC 面板的抗冲击性能进行规律分析及评估。
침대공천비행기열방호계통항충격성능，기우이득실험결과대충격재하작용적평문편직C／SiC복합재료박판쇄편운단결구정성건모급분석，획득 C ／SiC 쇄편운중특수축향주상고능구。기우 Autodyn 정교각향이성재료모형추도재료삼수병여실험대비，험증모형급삼수적합이성。거 C ／SiC 쇄편운단특점선취탄환잉여속도、쇄편운축향평균속도급분산각작위주요특정삼수，병이구형 Al 탄환박판당격모형위대상，대초고속당격다충공황 C ／SiC 면판적항충격성능진행규률분석급평고。
The impact resistance of thermal protective system is an important determinant for the safety service of space airplane in orbit.Based on impact experiments,a debris cloud structure model of plain-woven C/SiC composite under impact load was proposed and analysed qualitatively,in which the special axial columnar high energy zone of C/SiC debris cloud was emphasized.Based on the Autodyn orthotropic composite model,the material parameters were derived, whose rationality was verified by the comparison of numerical results with the experimental results.The residual velocity of projectile,the axial average velocity and the distributed angle of debris cloud were selected as the main characteristic parameters according to the debris cloud characteristics of C/SiC composite.Taking Al spherical projectile as the impacting object,the impact resistance of a C/SiC plate was analysed and assessed under various conditions.