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Stiffness Degradation Modeling for Composite Wind Turbine Blades Based on Full-Scale Fatigue Testing
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作者 Haixia Kou Kongyuan Wei +1 位作者 Yanhu Liu Xuyao Zhang 《Journal of Beijing Institute of Technology》 EI CAS 2023年第4期517-528,共12页
In order to provide more insights into the damage propagation composite wind turbine blades(blade)under cyclic fatigue loading,a stiffness degradation model for blade is proposed based on the full-scale fatigue testin... In order to provide more insights into the damage propagation composite wind turbine blades(blade)under cyclic fatigue loading,a stiffness degradation model for blade is proposed based on the full-scale fatigue testing of a blade.A novel non-linear fatigue damage accumulation model is proposed using the damage assessment theories of composite laminates for the first time.Then,a stiffness degradation model is established based on the correlation of fatigue damage and residual stiffness of the composite laminates.Finally,a stiffness degradation model for the blade is presented based on the full-scale fatigue testing.The scientific rationale of the proposed stiffness model of blade is verified by using full-scale fatigue test data of blade with a total length of 52.5 m.The results indicate that the proposed stiffness degradation model of the blade agrees well with the fatigue testing results of this blade.This work provides a basis for evaluating the fatigue damage and lifetime of blade under cyclic fatigue loading. 展开更多
关键词 composite wind turbine blades fatigue damage stiffness degradation model full-scale fatigue testing
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An Advanced Control Strategy for Dual-Actuator Driving System in Full-Scale Fatigue Test of Wind Turbine Blades
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作者 Guanhua Wang Jinghua Wang +2 位作者 Xuemei Huang Leian Zhang Weisheng Liu 《Energy Engineering》 EI 2022年第4期1649-1662,共14页
A new dual-actuator fatigue loading system of wind turbine blades was designed.Compared with the traditional pendulum loading mode,the masses in this system only moved linearly along the loading direction to increase ... A new dual-actuator fatigue loading system of wind turbine blades was designed.Compared with the traditional pendulum loading mode,the masses in this system only moved linearly along the loading direction to increase the exciting force.However,the two actuators and the blade constituted a complicated non-linear energy transferring system,which led to the non-synchronization of actuators.On-site test results showed that the virtual spindle synchronous strategy commonly used in synchronous control was undesirable and caused the instability of the blade’s amplitude eventually.A cross-coupled control strategy based on the active disturbance rejection algorithm was proposed.Firstly,a control system model was built according to the synchronization error and tracking error.Furthermore,based on arranging the transition process,estimating the system state and error feedback,and compensating disturbance,an active disturbance rejection controller was designed by adopting the optimal control function.Finally,on-site test results showed that the cross-coupled control strategy based on the active disturbance rejection algorithm could ensure the synchronization of two actuators.The maximum speed synchronization error of the two motors was less than 16 RPM,the displacement synchronization error of the two actuators was less than 0.25 mm and approaching zero after 4 seconds,and the peak value of vibration of the blade was less than 5 mm,which satisfied the fatigue test requirement. 展开更多
关键词 Wind turbine blades full-scale fatigue test synchronous control cross-coupled control strategy active disturbance rejection control algorithm
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Lifetime Prediction of Wind Turbine Blade Based on Full-Scale Fatigue Testing 被引量:1
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作者 KOU Haixia AN Zongwen +1 位作者 MA Qiang GUO Xu 《Journal of Shanghai Jiaotong university(Science)》 EI 2020年第6期755-761,共7页
In order to predict the lifetime of products appropriately with long lifetime and high reliability,the accelerated degradation testing(ADT)has been proposed.Composite wind turbine blade is one of the most important co... In order to predict the lifetime of products appropriately with long lifetime and high reliability,the accelerated degradation testing(ADT)has been proposed.Composite wind turbine blade is one of the most important components in wind turbine system.Its fatigue cycle is very long in practice.A full-scale fatigue testing is usually used to verify the design of a new blade.In general,the full-scale fatigue testing of blade is accelerated on the basis of the damage equivalent principle.During the full-scale fatigue test ing,blade is subjected to higher testing load than normal operat ing conditions;consequently,the performance degradation of the blade is hastened over time.The full-scale fatigue testing of blade is regarded as a special ADT.According to the fatigue failure criterion,we choose blade stiffness as the characteristic quantity of the blade performance,and propose an accelerated model(AM)for blade on the basis of the theories of ADT.Then,degradation path of the blade stiffness is modeled by using Gamma process.Finally,the lifet ime prediction of full-scale megawatt(MW)blade is conducted by combining the proposed AM and blade stiffness degradation model.The prediction results prove the reasonability and validity of this study.This can supply a new approach to predict the lifetime of the full-scale MW blade. 展开更多
关键词 composite wind turbine blade accelerated degradation testing(ADT) acelerated model(AM) full-scale fatigue testing blade stiffness lifet ime prediction
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飞机起落架变行程疲劳试验技术发展综述 被引量:3
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作者 赵俊杰 王逾涯 +1 位作者 李岷 高祖德 《机械强度》 CAS CSCD 北大核心 2004年第z1期285-287,共3页
飞机起落架疲劳试验技术经历了固定行程、一维变行程、二维变行程、三维变行程等发展阶段。固定行程的疲劳试验简单易行 ,但试验寿命偏长。一维变行程疲劳试验技术应用于垂直安装的支柱式起落架。二维变行程疲劳试验技术解决了起落架支... 飞机起落架疲劳试验技术经历了固定行程、一维变行程、二维变行程、三维变行程等发展阶段。固定行程的疲劳试验简单易行 ,但试验寿命偏长。一维变行程疲劳试验技术应用于垂直安装的支柱式起落架。二维变行程疲劳试验技术解决了起落架支柱安装上存在空间倾斜角的问题。实时三维变行程疲劳试验 ,能更真实地模拟起落架的使用情况 。 展开更多
关键词 飞机 起落架 变行程 疲劳试验 疲劳寿命
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磁记忆检测技术在飞机起落架检测中的应用 被引量:16
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作者 任吉林 宋凯 +3 位作者 邬冠华 胡伟利 蒋耘生 张志宏 《无损检测》 2002年第8期346-348,351,共4页
飞机起落架构件容易发生疲劳损伤。探讨了磁记忆检测技术在起落架构件疲劳试验中应力集中部位检测的应用。可以预计 ,该方法将在构件的疲劳分析。
关键词 起落架 磁性检验 磁记忆材料 疲劳试验 飞机 应力集中
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涡流检测在飞机疲劳试验中的应用 被引量:4
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作者 唐继红 张元仕 +3 位作者 任吉林 胡伟利 蒋耘生 张志宏 《无损检测》 2001年第12期514-517,共4页
通过理论分析和试验研究 。
关键词 涡流检验 飞机 疲劳试验 疲劳裂纹
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军用飞机无损检测设备发展简介 被引量:1
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作者 苏义鑫 杨小林 许泱 《无损检测》 北大核心 2005年第8期416-417,422,共3页
着重回顾国内军用飞机结构件损伤无损检测设备的历史,经历了目视检测、模拟式设备和数字式设备三个阶段;并对相关无损检测设备的发展趋势进行了展望,认为早期诊断、原位检测微机处理及网络化远程探测和评估是今后的发展方向。
关键词 无损检测 航空维修 飞机结构件 腐蚀损伤 疲劳裂纹 发展趋势
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通用飞机全尺寸疲劳验证试验技术 被引量:8
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作者 范瑞娟 王新波 杨剑锋 《航空科学技术》 2016年第6期57-61,共5页
全尺寸疲劳验证试验是新型通用飞机取得单机适航证的前提条件,是飞机服役后持续适航的重要保障。本文以"小鹰"-500飞机的全尺寸疲劳验证试验为例,从适航条例CCAR-23.572条款的要求出发,对"小鹰"-500飞机的全尺寸疲... 全尺寸疲劳验证试验是新型通用飞机取得单机适航证的前提条件,是飞机服役后持续适航的重要保障。本文以"小鹰"-500飞机的全尺寸疲劳验证试验为例,从适航条例CCAR-23.572条款的要求出发,对"小鹰"-500飞机的全尺寸疲劳验证试验技术做以全面总结,给出了一套行之有效的编谱方法、试验方法,为今后同类飞机的疲劳验证试验提供参考和借鉴。 展开更多
关键词 通用飞机 全尺寸飞机结构 疲劳试验 载荷谱
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飞机疲劳试验工程优化方法 被引量:3
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作者 郭兰中 王育鹏 《兰州工业高等专科学校学报》 2000年第2期1-3,共3页
相关系数法是一种有效的飞机疲劳试验载荷处理方法。通过对某型飞机后机身设计弯矩图和试验弯矩图的比较 。
关键词 飞机 疲劳试验 载荷处理 相关系数法 工程优化法 结构设计
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航空机轮加速寿命试验台的结构设计及论证 被引量:1
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作者 王学锋 马晓军 邓伟林 《航空精密制造技术》 2020年第6期6-10,14,共6页
航空机轮加速寿命试验台为完成对航空机轮的疲劳寿命考核而建立的,具备垂直加载、侧偏加载和阻力加载的能力,可在同一鼓轮下同时进行两套机轮疲劳寿命试验。航空机轮在该试验台上,可以按照规定的载荷谱、速度谱进行常规滚转试验,也可通... 航空机轮加速寿命试验台为完成对航空机轮的疲劳寿命考核而建立的,具备垂直加载、侧偏加载和阻力加载的能力,可在同一鼓轮下同时进行两套机轮疲劳寿命试验。航空机轮在该试验台上,可以按照规定的载荷谱、速度谱进行常规滚转试验,也可通过调整载荷谱,增加阻力载荷进行强化滚转试验,从而缩短试验时间,达到与常规滚转试验等效的累积里程,加快机轮的研制进程,降低研制成本。为后续建设提供了可行性论证。 展开更多
关键词 飞机刹车系统 航空机轮 疲劳试验 应力分析
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