【摘要】 随着碳纤维复合材料(carbon fiber composite, CFC)在军事领域中的广泛应用，建立球形破片对CFC的侵彻工程模型对满足武器装备防护结构设计和目标易损性研究的需求具有重要意义。开展试验研究分析了不同入射角以及靶板厚度下的CFC失效模式和耗能机制，据此建立了计算弹道极限速度和破片剩余速度的工程模型，并在广泛的弹、靶参数范围内进行了对比验证。研究表明：高速冲击条件下，CFC层合板的失效模式包括剪切冲塞破坏、纤维拉伸断裂、层合板破碎和分层；破片入射角的变化对层合板失效机制没有明显影响；对于不同材质的球形破片和CFC层合板，在弹靶相对厚度0<h/(dcos θ)<3范围内，弹道极限速度和破片剩余速度工程模型的预测误差分别小于8%和5%。更多还原

【Abstract】 With widespread application of carbon fiber composite(CFC) materials in military field, to establish a penetration engineering model of spherical fragments into CFC materials is of great significance to meet needs of weapon equipment protective structure design and target vulnerability studies. Here, test studies were conducted to analyze failure modes and energy dissipation mechanisms of CFC materials under different fragment incident angles and target plate thicknesses. Then, an engineering model was established to calculate ballistic limit velocity and fragment residual velocities. The contrastive verification was performed within wide ranges of fragment and target parameters. Studies showed that under high-speed impact conditions, failure modes of CFC laminates include shear plug failure, fiber tensile fracture, laminate fragmentation and delamination; changes of fragment incident angles have no obvious effect on failure mechanism of laminates; for spherical fragments of different materials and CFC laminates, prediction errors of engineering models of ballistic ultimate velocity and fragment residual velocity are less than 8% and 5%, respectively within target relative thickness range of 0<h/(dcos θ)<3.更多还原