利用层压板刚度减少技术推导了含表面缺口复合材料层压板的临界应力表达式。
A simplified expression for calculating the critical stress is developed according to a stiffness reduction technique. The experimental and theoretical results show good agreement.
论文以大展弦比飞翼布局机翼蒙皮的优化设计为背景，开展了复合材料层压板结构的优化设计工作。
In this paper, an effective design optimization method for High-aspect-ratio composite wing skin is presented.
研究表明，通过在可靠性分析中引入了冲击威胁的概念，可以较充分地发挥复合材料层压板的损伤容限性能。
The results indicate that the damage tolerance behavior of composite laminates can be taken fully by taking the impact threats into consideration in the reliability analysis.
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