Analysis on the Bonding Failure Mechanism of High Modulus Carbon Fiber Composites

In order to explore the bonding failure mechanism of high modulus carbon fiber composite materials, the tensile experiment and finite element numerical simulation for single-lap and bevel-lap joints of unidirectional laminates are carried out, and the stress distributions, the failure modes, and the damage contours are analyzed. The analysis shows that the main reason for the failure of the single-lap joint is that the stress concentration of the ply adjacent to the adhesive layer is serious owing to the modulus difference, and the stress cannot be effectively transmitted along the thickness direction of the laminate. When the tensile stress of the ply exceeds its ultimate strength in the loading process, the surface fiber will fail. Compared with the single-lap joint, the bevel-lap joint optimizes the stress transfer path along the thickness direction, allows each layer of the laminate to share the load, avoids the stress concentration of the surface layer, and improves the bearing capacity of the bevel-lap joint. The improved bearing capacity of the bevel-lap joint is twice as much as that of the single-lap joint. The research in this paper provides a new idea for the subsequent study of mechanical properties of adhesively bonded composite materials.     

评定复合材料的超声换能器的研制

由于复合材料结构的特殊性,对检测用的超声换能器提出了较高要求。论文系统分析了换能器的振动等效电路和振动方程,详细讨论了影响换能器性能的主要因素,成功研制出了符合使用要求的换能器。     

光学材料亚表面损伤深度破坏性测量技术的实验研究

基于差动原理对HF酸恒定化学蚀刻速率法进行改进,以降低环境(温度、HF酸浓度等)变化对测量结果的影响,从而提高测量效率和测量准确性。并将在新方法测量实验后的结果与理论估计值进行了比较分析。     

民用飞机短舱复合材料结构雷电直接效应试验验证方法及漆层厚度影响研究

随着飞机设计的发展,复合材料广泛应用于民用飞机短舱结构。由于碳纤维复合材料结构的导电性以及抗雷电损伤能力比铝合金结构差,复合材料短舱结构雷电防护能力已成为影响飞机飞行安全的一项关键问题。依据相关适航条款和相应的国际标准,阐述了民用飞机短舱复合材料雷电防护试验验证方法,并依据验证方法对漆层厚度的损伤影响进行了试验研究。短舱常规蒙皮构型的复合材料试验件,在不同漆层厚度下的雷电防护试验结果表明,漆层较薄时,漆层对短舱复合材料的雷电直接效应防护能力无明显的影响;当漆层厚度达到一定厚度时,较厚的漆层将显著降低短舱复合材料的雷电直接效应防护能力,最严重时将造成复合材料蒙皮的击穿,损伤蒙皮内部系统设备,从而危害飞行安全。试验结果与理论的机理分析具有良好的一致性,对民用飞机短舱复合材料结构的雷电防护设计提供了指导方向和参考意义。     

EWIS支架装配变形及其承载分析

民用飞机EWIS系统支架遍布全机,在空间狭小的区域,考虑到装配和维修的要求,需采用单侧安装工艺,若支架装配时未固定好或操作不当,会导致支架承受安装力矩载荷,使支架结构产生塑性变形和残余应力,严重的会导致支架破坏。为了分析EWIS支架在安装力矩下的应力和变形情况,采用ABAQUS对典型标准支架进行有限元分析,考虑材料的非线性特性,得到了支架在不同安装力矩下的变形和应力情况,并对塑性变形后的支架继续承载进行了分析,对比分析支架塑性变形前后承载的应力,得出了变形对承载的影响。采用非线性有限元分析方法可对支架安装力矩的作用进行模拟,并计算结构产生塑性变形后承载的应力水平,为民用飞机EWIS支架的装配过程和塑性变形后的承载分析提供参考。     

烧结多孔结构的渗透和流阻特性研究

为研究粉末冶金多孔结构的渗透性和流阻,以空气和氢气为介质进行了实验.实验显示微孔内流雷诺数低于1时,介质流量与穿过多孔结构的压降呈线性关系;当内流雷诺数高于1时,其流量与压降呈非线性特征.分析表明:传统的堆积床经验关系式将低估氢气和空气在烧结材料微孔中的流阻;相反,高估烧结多孔结构的渗透性能.并用粉末烧结结构的氢气和空气渗透实验数据拟合了多孔结构渗透率及摩擦阻力关联式.      

超声波辐照对聚合物及其复合材料性能的影响

综述了超声辐照对聚合物及其复合材料在超细添加材料分散、力学性能、理化性能以及组织结构等方面的影响规律及其相应的作用机理,提出了超声波辐照工艺与其他工艺复合等的发展趋势和应用前景。     

脉冲发动机软隔离装置反向打开过程研究

通过显示动力学的方法,对一种软隔离装置反向打开过程进行了模拟,并通过燃气发生器-隔层试验装置,进一步验证了隔层的打开过程,模拟结果与试验结果吻合得较好,验证了计算方法的合理性。研究结果表明,脆性断裂准则可较准确地预测隔层的破坏位置和压强,同时在内压冲击载荷作用下隔层薄弱区域首先出现破裂,破裂后下隔层结构逐渐反向打开,最终端口发生严重破坏,研究结果可用于发动机隔层的初步设计。     

民机复合材料目视检查中的眼动与疲劳检测

疲劳是导致民机复合材料结构目视检查差错的重要诱因，疲劳检测对于减少人的差错，保障飞行安全具有重要意义。对基于眼动行为的疲劳度量与检测方法进行了研究，建立了民机复合材料结构目视检查实验场景，利用Tobii眼动仪提取了正常状态和疲劳状态下的目视检查眼动数据，分析了瞳孔直径、平均注视时间、平均注视频率、平均眼跳时间、平均眼跳频率、注视热点与轨迹和扫视速度等眼动行为与疲劳的关系，进而提取了能表征疲劳的瞳孔直径、平均注视时间和扫视速度3种眼动指标，以该指标构建特征向量，利用支持向量机（SVM）方法构建了目视检查疲劳检测模型。研究发现疲劳状态下的目视检查平均注视时间更长，扫视速度更慢、瞳孔直径减小，右瞳孔减小程度更大，核函数为径向基函数和高斯函数的SVM方法对疲劳的检测效果好。研究结果表明，利用SVM方法训练由瞳孔直径、平均注视时间和扫视速度构成的眼动特征向量能有效检测目视检查中的疲劳状态。     

Numerical exploration on the thermal invasion characteristics of two typical gap-cavity structures subjected to hypersonic airflow

In this paper, numerical investigation of hypersonic gas flow over two typical gap-cavity structures is carried out using all-speed preconditioned density-based solver. Such structures filled with porous seal in the gap are often present at the joint locations of control surfaces of the hypersonic vehicles. Single-domain approach is adopted to integrate the governing equations for both porous and fluid regions. The basic thermal invasion characteristic is first illustrated using the maze gap-cavity structure without sealing. Then, the influence of seal filling depth on the thermal invasion characteristic is investigated for the structure with sealing. Finally, a comparison of thermal invasion characteristics between maze and straight gap-cavity structures is performed to examine the influence of gap bending. Results show that the main source of hot airflow invading into the gap is from the millimeter scale gas layer within the boundary layer. And the invasion characteristic presents approximate stationary behavior. A primary vortex occurs in the gap adjacent to the leeward wall, which is ascribed to the impinging effect between the separate boundary flow and the windward wall. This effect is also the main driving force of thermal invasion. A treatment of filling the seal in certain depth inside the gap can significantly reduce the thermal load of seal and maintain an acceptable level of the invading mass flow rate. Additionally, it is found that the gap bending exerts a limited block effect on the thermal invasion without sealing, and this effect can be ignored with sealing. These results can provide a reference for optimizing the seal gap-cavity structure configuration.