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邓凡臣.大型飞机机身曲板多轴载荷试验技术研究[J].实验力学,2018,33(3):484~490
大型飞机机身曲板多轴载荷试验技术研究
On the experimental technique for large aircraft fuselage curved panel subjected to multiaxial loading
投稿时间: 2016-11-27  最后修改时间: 2017-03-03
DOI:10.7520/1001-4888-16-255
中文关键词:  机身壁板  加载方法  叠加原理  均匀性  多轴载荷
英文关键词:fuselage panel  loading method  superposition principle  uniform  multiaxial load
基金项目:国家自然科学基金(11602237)资助
作者单位
邓凡臣 中国飞机强度研究所 西安 710065 
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中文摘要:
      根据大型运输机及客机机身壁板结构静力分析与耐久性和损伤容限试验技术需求,研制了一套能够为机身壁板施加多轴载荷的试验系统(FPTS)。该系统由轴向载荷施加组件、剪切载荷施加组件、气压载荷及环向平衡载荷施加组件构成,既能为机身曲板施加单一载荷,同时又能实现多轴载荷协调加载,解决了多轴载荷施加边界约束的相互干涉与耦合问题。试验结果表明,单轴载荷试验应变数据均匀,多轴载荷试验应变满足结构在小变形下的叠加原理。上述试验结果可为机身静强度及疲劳强度设计提供数据支持。
英文摘要:
      According to experimental technical requirements of fuselage panel's structure static analysis, durability and damage tolerance test of large transport aircraft and passenger aircraft, a set of experimental system was developed that can exert multiaxial loads on fuselage curved panel. This system is composed of axial load applying components, shear load applying components, barometric pressure load applying components and annular equilibrium load applying components. It can not only exert single load on fuselage curved panel, but also realize multiaxial load coordinated loading, and has solved the problem of mutual interference and coupling due to multiaxial loading and boundary constraints. Experimental results show that the strain data is uniform in uniaxial loading experiment, and strain data satisfy superposition principle for small deformation in multiaxial loading experiment. Above results can provide data support for design of static strength and fatigue strength for fuselage.
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