摘要
先进的航空航天器表面结构暴露在严酷的工作载荷环境中,包括复杂的机械力载荷、压力载荷、声载荷和热载荷等,航空航天器表面结构可简化为薄壁结构,在复合载荷作用下结构以非线性方式响应,呈现出复杂的响应特性。首先以热弹性力学、板壳理论及结构稳定性原理为基础,建立热及噪声载荷联合作用下薄壁板运动模态方程,讨论了薄壁结构跳变响应的机理,进而运用等价线性化方法求解模态方程,在此基础上分析了热及噪声载荷对薄壁结构屈曲的影响,进而探讨了热及噪声载荷作用下薄壁结构的非线性响应统计特性。计算了四边简支高温钛合金薄板在声载荷下四个关键点处的均方应变,为进一步开展薄壁结构声疲劳寿命估算和强度设计奠定了基础。
Advanced aircraft and spacecraft structure is exposed to severe operation environment frequently,which is the combination of mechanical,pressure,acoustic,and thermal loads.These loading conditions cause structures to respond in a nonlinear fashion and exhibit complex response characteristics.First,this paper builds thin-walled structure motion governing equations and lists the model equation based on nonliner large deflection based on thermoelasticity theory,thin plate theory,shell theory and structure stability theory,discusses the essential phenomenon of snap-through,solves the equation with EL method and exahibites different influence on thin walled pannel by thermal loading and acoustic loading,and then calculates the root mean square strain on four keypoints of quadrilateral simply supported titanium slab,which establishes research foundtion for further sonic fatigue life.
出处
《沈阳航空工业学院学报》
2010年第5期23-28,共6页
Journal of Shenyang Institute of Aeronautical Engineering
基金
航空基础科学基金资助基金项目(项目编号:02C54007)
关键词
薄壁结构
大挠度非线性
热屈曲
跳变响应
thin-walled structure
large deflection nonlinerity
thermal buckling
snap-through response
