摘要
波音787飞机的机身蒙皮采用全复合材料,对于复合材料机身蒙皮的修理,波音787结构维修手册给出了明确的修理方案,其中包括复合材料机身蒙皮的钛合金板铆接修理。然而,对维修方案背后的理论依据,即强度、刚度等力学特性要求没有叙述。基于此,本文对复合材料机身蒙皮的钛合金板铆接修理建立了两种维修的三维有限元模型,分析了这两种维修方案母板、补片和填平板的应力大小和应力分布特性。研究表明:复合材料机身蒙皮大的穿透型裂纹钛合金板铆接修理能够满足静强度要求,两种维修方案的钛合金补片破坏源发生在不同位置。
Fuselage skin is all-composite in Boeing 787. Repair programs for composite fuselage skin are given in Boeing 787 structural repair manual, including composite fuselage skin repair with titanium plates riveting. Howev- er, the maintenance theory of these repair programs and repair procedures, strength, stiffness and other mechanical properties of these repair programs are not described. Based on this, two dimensional finite element models of compos- ite fuselage skin repair with titanium plates riveting are established in this paper. Stress size and distribution of ma- trix, patch and fill flat are analyzed on these two repair programs. Studies have shown that repairing large composite fuselage skin penetration crack with titanium plates riveting can meet the static strength requirements. Destroy sources of titanium patches of these two repair programs will occur at different locations.
出处
《宇航材料工艺》
CSCD
北大核心
2017年第2期29-33,共5页
Aerospace Materials & Technology
基金
国家自然科学基金(基金号51405491)
国家自然科学基金(基金号51605331)
中央高校基本科研业务费(3122017028)
关键词
复合材料
机身蒙皮
损伤
修理
Composite, Fuselage skin, Damage, Repair
