厚截面复合材料结构固化残余应力研究进展

Residual stress induced by cure processing in thick section composite part: State-of-art

随着复合材料在飞机机架主承力构件的广泛应用,厚截面复合材料构件固化过程残余应力的预测和控制是必须解决的关键问题之一。厚截面复合材料的残余应力形成机制远较薄板复杂,更易发生温度过热、紧密压实不完全、非同步固化,固化残余应力大等问题。并且厚板在固化过程中形成的残余应力难以释放,降低复合材料结构的承载能力和使用寿命。采用数值模拟复合材料固化过程,优化固化工艺是是降低厚截面复合材料结构生产成本的有效方法。从热传导与化学反应、紧密压实和残余应力3个方面回顾了厚截面复合材料固化过程数值模拟的研究进展,对下一步的研究方向进行了展望。

With composite materials widely applied in primary structure of airframe, it becomes important and urgent to predict and decrease the residual stress induced by cure processing in thick section composite parts. By comparison with thin composite parts, The thick composite parts have more complex form mechanism of residual stress, and were prone to overheating, inadequate consolidate, asynchronously cure and higher lever residual stress. And it＇s hard to release, that cause poor strength and fatigue life for the thick composites part. Numerical simulating and optimizing the cure processing were effective to save manufacturing cost of thick composites part. Recent works of thick composites part cure processing simulation were reviewed from thermal conduction and chemical reaction, consolidation and residual stress. The prospect of future research was forecasted for residual stress of thick composites parts.