Fatigue properties of Reactive Powder Concrete (RPC) under axial compression of single-stage and multi-level amplitude in cycles were studied. The tests reveal the fatigue life, the strain and residual life of the R...Fatigue properties of Reactive Powder Concrete (RPC) under axial compression of single-stage and multi-level amplitude in cycles were studied. The tests reveal the fatigue life, the strain and residual life of the RPC samples. Through the analysis of the test results under cyclic loads of single amplitude, the S-N curve of RPC and the evolution rule of macro-damage of RPC were presented, which can be divided into latency stage, stable development stage and instability development stage according to the evolution pattern of the fatigue crack. Accordingly, the development of longitudinal deformation presents the similar three-stage-model, and the proportion of each stage is 15%, 75%, and 10%. According to test results, the fatigue strength reduction factor is 0.564. We brought forward an empirical formula to predict the life of RPC via total longitudinal strain and got the evolving rule for the residual strength of the RPC. The analysis of the test results under cyclic loads of multi-level amplitude shows that the strain under this loading pattern experiences three stages. The characteristic value for the residual strain was obtained. The irreversible damage and non-linear evolution of RPC was described by the development of the residual plastic strain.展开更多
The thermomechanical fatigue behaviour of different high temperature alloys has been investigated and is under investigation respectively. The creep-fatigue behaviour of heat resistant steels was investigated by long-...The thermomechanical fatigue behaviour of different high temperature alloys has been investigated and is under investigation respectively. The creep-fatigue behaviour of heat resistant steels was investigated by long-term service-type strain cycling tests simulating thermomechanical fatigue (TMF-) loading conditions at the heated surface of e.g. turbine rotors. Single-stage as well as three-stage cycles leads to similar results at the application of the damage accumulation rule. Life prediction which simulates typical combinations of cold starts, warm starts and hot starts has been established successfully for isothermal service-type loading and will be exceeded for thermomechanical loading. Long-term thermomechanical fatigue testing of Thermal Barrier Coating systems show typical delamination damage. An advanced TMF cruciform testing system enables complex multiaxial loading.展开更多
High strength threaded fasteners are widely used in the aircraft industry, and service experience shows that for structures where shear loading of the joints is significant, like skin splices, fuselage joints or spar ...High strength threaded fasteners are widely used in the aircraft industry, and service experience shows that for structures where shear loading of the joints is significant, like skin splices, fuselage joints or spar caps-web attachments, more cracks are initiated and grow from the edges of the fastener holes than from features like fillets radii and corners or from large access holes. The main causes of this cracking are the stress concentrations introduced by the fastener holes and by the threaded fasteners themselves, with the most common damage site being at the edge of the fastener holes. Intuitively, it is easy to visualize that after the crack initiation, during the growth stages, some of the load transferred initially by the fastener at the cracked hole will decrease, and it will be shed to the adjacent fasteners that will carry higher loads than in uncracked condition. Using currently available computer software, the method presented in this paper provides a relatively quick and quantitatively defined solution to account for the effects of crack length on the fastener loads transfer, and on the far field and bypass loads at each fastener adjacent to the crack. At each location, these variations are determined from the 3-dimensional distribution of stresses in the joint, and accounting for secondary bending effects and fastener tilt. Two cases of a typical skins lap splice with eight fasteners in a two rows configuration loaded in tension are presented and discussed, one representative for wing or fuselage skins configurations, and the second case representative for cost effective laboratory testing. Each case presents five cracking scenarios, with the cracks growing from approx. 0.03 inch to either the free edge, next hole or both simultaneously.展开更多
针对阶梯块谱下的材料疲劳寿命预测问题,尤其是已有相关非线性模型的计算参数依赖大量试验数据或较难选取合适的基准值,导致在实际工程中应用有一定局限性。提出了一种新的基于相邻载荷的作用系数αi=(Si+1/Si)1/b lg K,该系数中两个参...针对阶梯块谱下的材料疲劳寿命预测问题,尤其是已有相关非线性模型的计算参数依赖大量试验数据或较难选取合适的基准值,导致在实际工程中应用有一定局限性。提出了一种新的基于相邻载荷的作用系数αi=(Si+1/Si)1/b lg K,该系数中两个参数b、K来自材料疲劳寿命关系式S=KN-b。结合前人的二级、三级、四级应力加载试验结果,分别计算并对比了与多种疲劳损伤模型的结果。结果表明,新模型在疲劳寿命/损伤的预测结果优于Miner模型、Manson模型、Subramanyan模型及Hashin模型,可更为准确地预测阶梯块谱下的疲劳寿命/损伤。展开更多
针对传统检测方法中摄像头视角受限问题,提出了一种结合面部姿态矫正和改进ViViT的多视角下人脸疲倦检测方法。采用Mediapipe Face Mesh定位面部三维特征点并将其矫正为正面,利用提出的FGR-ViViT模型来捕捉矫正后的眼睛、眉毛、嘴巴线...针对传统检测方法中摄像头视角受限问题,提出了一种结合面部姿态矫正和改进ViViT的多视角下人脸疲倦检测方法。采用Mediapipe Face Mesh定位面部三维特征点并将其矫正为正面,利用提出的FGR-ViViT模型来捕捉矫正后的眼睛、眉毛、嘴巴线条图像帧序列变化。FGR-ViViT通过在ViViT的Temporal Transformer Encoder中添加部件选择模块来捕捉特征在时间维度中的细微差异,同时融合2次dropout和改进的对比损失函数来调整样本的相似性,降低模型过拟合风险并提高泛化能力。实验结果表明,提出的方法在YawDD和DROZY矫正后的线条图像帧的测试集上,F1-分数达到了94.5%和97.6%,相较于原始人脸图像帧分别提高了3.2%和10.4%,其FGR-ViViT相较于原始ViViT分别提高了6.1%和0.7%。所提方法适用于摄像头灵活摆放的多种应用场景,对解决多视角人脸睡意判断具有积极意义。展开更多
基金Funded by the National 863 Plan Foundation of China (No.2006AA03Z536)the National Natural Science Foundation of China (No.50778021)
文摘Fatigue properties of Reactive Powder Concrete (RPC) under axial compression of single-stage and multi-level amplitude in cycles were studied. The tests reveal the fatigue life, the strain and residual life of the RPC samples. Through the analysis of the test results under cyclic loads of single amplitude, the S-N curve of RPC and the evolution rule of macro-damage of RPC were presented, which can be divided into latency stage, stable development stage and instability development stage according to the evolution pattern of the fatigue crack. Accordingly, the development of longitudinal deformation presents the similar three-stage-model, and the proportion of each stage is 15%, 75%, and 10%. According to test results, the fatigue strength reduction factor is 0.564. We brought forward an empirical formula to predict the life of RPC via total longitudinal strain and got the evolving rule for the residual strength of the RPC. The analysis of the test results under cyclic loads of multi-level amplitude shows that the strain under this loading pattern experiences three stages. The characteristic value for the residual strain was obtained. The irreversible damage and non-linear evolution of RPC was described by the development of the residual plastic strain.
基金supported by the Deutsche Forschungsgemeinschaft(DFG),Project No.BE1890,16-1the Forschungs-vereinigung der Arbeitsgemeinschaften der Eisen und Metall verarbeitenden Industrie e.V.(AVIF),Project No.A166+1 种基金the FKM Forschungskuratorium Maschinenbau e.V.Project No.052510the Arbeitsgemeinschaft industrieller Forschungsvereinigungen(AiF)and the VDEh-Gesellschaft zur Forderung der Eisenforschung mbH,Project No.11200 N.
文摘The thermomechanical fatigue behaviour of different high temperature alloys has been investigated and is under investigation respectively. The creep-fatigue behaviour of heat resistant steels was investigated by long-term service-type strain cycling tests simulating thermomechanical fatigue (TMF-) loading conditions at the heated surface of e.g. turbine rotors. Single-stage as well as three-stage cycles leads to similar results at the application of the damage accumulation rule. Life prediction which simulates typical combinations of cold starts, warm starts and hot starts has been established successfully for isothermal service-type loading and will be exceeded for thermomechanical loading. Long-term thermomechanical fatigue testing of Thermal Barrier Coating systems show typical delamination damage. An advanced TMF cruciform testing system enables complex multiaxial loading.
文摘High strength threaded fasteners are widely used in the aircraft industry, and service experience shows that for structures where shear loading of the joints is significant, like skin splices, fuselage joints or spar caps-web attachments, more cracks are initiated and grow from the edges of the fastener holes than from features like fillets radii and corners or from large access holes. The main causes of this cracking are the stress concentrations introduced by the fastener holes and by the threaded fasteners themselves, with the most common damage site being at the edge of the fastener holes. Intuitively, it is easy to visualize that after the crack initiation, during the growth stages, some of the load transferred initially by the fastener at the cracked hole will decrease, and it will be shed to the adjacent fasteners that will carry higher loads than in uncracked condition. Using currently available computer software, the method presented in this paper provides a relatively quick and quantitatively defined solution to account for the effects of crack length on the fastener loads transfer, and on the far field and bypass loads at each fastener adjacent to the crack. At each location, these variations are determined from the 3-dimensional distribution of stresses in the joint, and accounting for secondary bending effects and fastener tilt. Two cases of a typical skins lap splice with eight fasteners in a two rows configuration loaded in tension are presented and discussed, one representative for wing or fuselage skins configurations, and the second case representative for cost effective laboratory testing. Each case presents five cracking scenarios, with the cracks growing from approx. 0.03 inch to either the free edge, next hole or both simultaneously.
文摘针对阶梯块谱下的材料疲劳寿命预测问题,尤其是已有相关非线性模型的计算参数依赖大量试验数据或较难选取合适的基准值,导致在实际工程中应用有一定局限性。提出了一种新的基于相邻载荷的作用系数αi=(Si+1/Si)1/b lg K,该系数中两个参数b、K来自材料疲劳寿命关系式S=KN-b。结合前人的二级、三级、四级应力加载试验结果,分别计算并对比了与多种疲劳损伤模型的结果。结果表明,新模型在疲劳寿命/损伤的预测结果优于Miner模型、Manson模型、Subramanyan模型及Hashin模型,可更为准确地预测阶梯块谱下的疲劳寿命/损伤。
文摘针对传统检测方法中摄像头视角受限问题,提出了一种结合面部姿态矫正和改进ViViT的多视角下人脸疲倦检测方法。采用Mediapipe Face Mesh定位面部三维特征点并将其矫正为正面,利用提出的FGR-ViViT模型来捕捉矫正后的眼睛、眉毛、嘴巴线条图像帧序列变化。FGR-ViViT通过在ViViT的Temporal Transformer Encoder中添加部件选择模块来捕捉特征在时间维度中的细微差异,同时融合2次dropout和改进的对比损失函数来调整样本的相似性,降低模型过拟合风险并提高泛化能力。实验结果表明,提出的方法在YawDD和DROZY矫正后的线条图像帧的测试集上,F1-分数达到了94.5%和97.6%,相较于原始人脸图像帧分别提高了3.2%和10.4%,其FGR-ViViT相较于原始ViViT分别提高了6.1%和0.7%。所提方法适用于摄像头灵活摆放的多种应用场景,对解决多视角人脸睡意判断具有积极意义。