复合材料层合板抗冲击损伤的参数表征

研究了铺层方式为［０２／９０２／４５２／－４５２］ｓ的航空用碳纤维增强树脂基复合材料（ＣＦＲＰ）准各向同性层合板低速冲击引起损伤的表征问题。通过落重冲击试验引入损伤程度Ｄ表示材料低速冲击后材料参数的变化大小，通过准静态球面弯曲试验提出复合材料层合板抗冲击的三种表征参数：层内开裂临界能Ｅ１ｃ、层间开裂（分层）临界能Ｅ２ｃ、分层扩展阻力Ｒ．

THE CHARACTERIZING PARAMETERS OF IMPACT RESISTANCE DAMAGE COMPOSITE LAMINATES

For the CFRP composite laminates with quasi-isotropic ply sequences of 02/902/452/- 452]s, whichis often available in airplane ,the characterizing problems on the damage caused by low velocity impact areinvestigated in this paper. The parameter alteration of the laminates before and after impact may be char-acterized by damage degree D which is induced by drop-weight impact tests. Three characterizing parame-ters determined by quasi-static bending tests-intraply cracking critical energy E1c, interlaminer crack-ing (delamination) critical energy E2c and delamination progating resistance R are given to judge the impactresistance of the CFRP composites. These characterizing parameters are valuable for the design of thedamage tolerance of composite structures and components as well as the development of composites withhigh impact resistance.