CAJ | 학술논문

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。
수착복합재료재비궤궤가주승력구건적엄범응용，후절면복합재료구건고화과정잔여응력적예측화공제시필수해결적관건문제지일。후절면복합재료적잔여응력형성궤제원교박판복잡，경역발생온도과열、긴밀압실불완전、비동보고화，고화잔여응력대등문제。병차후판재고화과정중형성적잔여응력난이석방，강저복합재료결구적승재능력화사용수명。채용수치모의복합재료고화과정，우화고화공예시시강저후절면복합재료결구생산성본적유효방법。종열전도여화학반응、긴밀압실화잔여응력3개방면회고료후절면복합재료고화과정수치모의적연구진전，대하일보적연구방향진행료전망。
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.