针对飞机结构疲劳特性,提出了基于频率域信息的随机载荷历程——功率谱密度函数(Power speetraldensity,PSD)估算结构振动疲劳的一种新的计算方法。首先对结构进行频率响应计算,得到结构的传递函数;将此传递函数与输入的功率谱相乘,获...针对飞机结构疲劳特性,提出了基于频率域信息的随机载荷历程——功率谱密度函数(Power speetraldensity,PSD)估算结构振动疲劳的一种新的计算方法。首先对结构进行频率响应计算,得到结构的传递函数;将此传递函数与输入的功率谱相乘,获得结构的应力功率谱密度;再结合材料参数,选择合适的疲劳损伤模型,利用频域方法计算结构的疲劳强度。对某型飞机机翼,采用本文方法,应用有限元分析(Finite element analysis,FEA)获得了应力响应功率谱密度函数,并对机翼在随机振动载荷下的强度特性进行了模拟与分析,给出了分析结果。展开更多
According to the concept of critical plane, a life prediction approach forrandom multiaxial fatigue is presented. First, the critical plane under the multiaxial randomloading is determined based on the concept of the ...According to the concept of critical plane, a life prediction approach forrandom multiaxial fatigue is presented. First, the critical plane under the multiaxial randomloading is determined based on the concept of the weight-averaged maximum shear strain direction.Then the shear and normal strain histories on the determined critical plane are calculated and takenas the subject of multiaxial load simplifying and multiaxial cycle counting. Furthermore, amultiaxial fatigue life prediction model including the parameters resulted from multiaxial cyclecounting is presented and applied to calculating the fatigue damage generated from each cycle.Finally, the cumulative damage is added up using Miner's linear rule, and the fatigue predictionlife is given. The experiments under multiaxial loading blocks are used for the verification of theproposed method. The prediction has a good correction with the experimental results.展开更多
文摘针对飞机结构疲劳特性,提出了基于频率域信息的随机载荷历程——功率谱密度函数(Power speetraldensity,PSD)估算结构振动疲劳的一种新的计算方法。首先对结构进行频率响应计算,得到结构的传递函数;将此传递函数与输入的功率谱相乘,获得结构的应力功率谱密度;再结合材料参数,选择合适的疲劳损伤模型,利用频域方法计算结构的疲劳强度。对某型飞机机翼,采用本文方法,应用有限元分析(Finite element analysis,FEA)获得了应力响应功率谱密度函数,并对机翼在随机振动载荷下的强度特性进行了模拟与分析,给出了分析结果。
基金This project is supported by National Natural Science Foundation of China (No.59775030).
文摘According to the concept of critical plane, a life prediction approach forrandom multiaxial fatigue is presented. First, the critical plane under the multiaxial randomloading is determined based on the concept of the weight-averaged maximum shear strain direction.Then the shear and normal strain histories on the determined critical plane are calculated and takenas the subject of multiaxial load simplifying and multiaxial cycle counting. Furthermore, amultiaxial fatigue life prediction model including the parameters resulted from multiaxial cyclecounting is presented and applied to calculating the fatigue damage generated from each cycle.Finally, the cumulative damage is added up using Miner's linear rule, and the fatigue predictionlife is given. The experiments under multiaxial loading blocks are used for the verification of theproposed method. The prediction has a good correction with the experimental results.
