摘要
分析了单级时效、双/多级时效、振动时效以及应力位向效应等工艺措施和因素对铝合金机翼整体壁板材料时效成形特性的影响,得到以下结论:应采用双/多级时效处理,以提高成形后壁板材料的综合性能;应采用振动时效应力松弛,以加速应力松弛,降低回弹,并提高成形后壁板材料的抗疲劳性能;对时效过程中存在应力位向效应的铝合金,应设计合适的时间温度曲线与加载曲线,以避免壁板材料因应力位向效应产生各向异性,导致材料屈服强度降低。提出了大型机翼整体壁板时效成形的工艺流程,给出了成形过程中热压罐内的温度时间曲线和气压时间曲线;提出了成形工装的模块化、标准化与柔性化设计以及解决壁板时效成形回弹问题的有限元方法,并对中国研究发展大型机翼整体壁板时效成形技术提出了建议。
The process factor and measure effects on age forming properties of aluminium alloy integral wing skin panels are analyzed,such as one-step aging,two/multi-step aging,vibratory stress relief method and stress-orienting effect.The following conclusions are drawn： two/multi-step aging should be adapted to improve the general performance of the wing panel;vibratory stress relief method should be taken to accelerate the stress relaxation,reduce springback and improve the fatigue resisting capability of panel material;appropriate temperature-time and air pressure-time relation curves should be designed to avoid anisotropic which leads to lower yield stress for the aluminium alloy with stress-orienting effect in age forming.As a result,an age forming process of large scale integral aircraft wing panel is proposed,including the temperature-time and air pressure-time relation curves of the clave in the forming process.A modular,standard and flexible method is presented for designing and manufacturing the forming tools.A finite element method is presented for solving the springback problem in age forming process.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2008年第3期728-733,共6页
Acta Aeronautica et Astronautica Sinica
基金
陕西省"13115"科技创新工程重大科技专项项目(2007ZDKG-65)
关键词
飞行器制造技术
时效成形
机翼整体壁板
多级时效
振动时效
aircraft manufacturing technology
age forming
integral aircraft wing panel
multi-step age method
vibratory stress relief method
