软式飞艇囊体结构弯皱特性分析

发布时间：2018-01-04 20:18

  本文关键词：软式飞艇囊体结构弯皱特性分析　出处：《哈尔滨工业大学》2016年硕士论文　论文类型：学位论文

  更多相关文章： 软式飞艇 弯皱特性 临近空间热环境 多尺度方法 变截面梁

【摘要】：软式飞艇作为典型的充气薄膜结构,在外载荷作用下容易发生失稳现象,临近空间热环境复杂且昼夜变化较大,促进飞艇热场集中和褶皱产生,加速飞艇的破坏,开展软式飞艇的褶皱特性研究具有重要的指导意义。针对三点弯曲充气梁的弯皱特性,建立了多尺度分析模型,对其褶皱发生、扩展规律和承载特性进行了数值分析。考察了多尺度模型中不同的界面处理方式以及精细化区域选取对褶皱分析结果影响,得到了充气梁的多尺度模型最优建模方式。设计了充气梁褶皱的三点弯曲实验,获取了充气梁在三点弯曲载荷作用下的褶皱特性实验结果,与数值分析结果对比,验证了多尺度分析方法的准确性和有效性。建立了三点弯曲充气梁褶皱特性预报模型,预报了褶皱区域长度、褶皱角和抗弯刚度变化,确定了充气梁三点弯曲载荷位移曲线,实验验证了预报模型的准确性。建立了空间变截面梁传递矩阵推导方法,得到了变截面梁刚度矩阵;完成了非连续变截面单元刚度矩阵计算,明确了锥形变化梁传递矩阵和刚度矩阵表达形式,验证了该理论准确性与高效性;建立了飞艇多尺度模型,完成了大变形非线性弯曲分析,获得了飞艇起皱载荷与失效载荷。建立了临近空间大气温度、太阳辐射、地球反照和红外辐射模型,开展了飞艇瞬态与稳态温度场分析,阐明了飞艇的温度场变化规律,分析了太阳能电池对飞艇热特性影响。开展了临近空间热环境下飞艇褶皱特性研究,分析了临近空间热环境对飞艇褶皱特性的影响。
[Abstract]:As a typical inflatable membrane structure, soft airship is prone to instability under external load. The thermal environment is complex and the diurnal variation is large in the adjacent space, which promotes the thermal field concentration and fold generation of the airship. It is of great significance to accelerate the damage of airship and to study the fold characteristics of flexible airship. According to the bending characteristics of three-point curved inflatable beam, a multi-scale analysis model is established and the fold occurs. The effects of different interface processing methods and fine regions selection on the results of fold analysis were investigated. The multi-scale model of inflatable beam is obtained, the three-point bending experiment of inflatable beam is designed, and the experimental results of the folding characteristics of inflatable beam under three-point bending load are obtained. Compared with the numerical analysis results, the accuracy and validity of the multi-scale analysis method are verified. A prediction model for the fold characteristics of three-point curved inflatable beam is established to predict the variation of fold region length, fold angle and bending stiffness. The three-point bending load displacement curve of inflatable beam is determined and the accuracy of the prediction model is verified experimentally. The transfer matrix derivation method of spatial variable section beam is established and the stiffness matrix of variable section beam is obtained. The stiffness matrix of discontinuous variable section element is calculated, and the expression of transfer matrix and stiffness matrix of tapered variable beam is defined, which verifies the accuracy and efficiency of the theory. The multi-scale model of airship is established, the nonlinear bending analysis of large deformation is completed, the wrinkling load and failure load of airship are obtained, and the models of atmospheric temperature, solar radiation, earth reflection and infrared radiation are established. The transient and steady-state temperature field analysis of airship is carried out, the variation law of airship temperature field is clarified, the influence of solar energy cell on the thermal characteristics of airship is analyzed, and the fold characteristics of airship in near space thermal environment are studied. The influence of thermal environment in adjacent space on the fold characteristics of airship is analyzed.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V214;V274
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本文编号：1379935