作者:宋欣，陈龙宝，单梁，刘倩，胡震东
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Authors:SONG Xin,CHEN Long-bao,SHAN Liang,LIU Qian,HU Zhen-dong
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摘要:摘要:针对增材制造的结构拓扑优化民机元件需要满足CCAR-25-R4适航认证的要求，以民机结构上的鹅颈链为对象，根据实际工况建立了静力验证方案，确保了试验数据的准确性和可靠性，为建立分析/计算MC2方法提供了可靠性数据基础；选择最大主应变作为试验数据与有限元分析结果的比对参数，结果表明：不同钛合金材料属性试验件的有限元分析结果与试验数据均值的误差均低于10%，在未获得准确的增材制造钛合金材料属性的前提下，采用各向同性、弹性模量 E =110 GPa和泊松比 ν =0.33进行有限元分析时，结果与试验数据偏差最小，为其它面向适航认证的增材制造小型民机元件静力验证试验方案的设计提供参考。
Abstract:Abstract: In order to meet the requirements of CCAR-25-R4 airworthiness certification for civil aircraft components of structural topology optimization using additive manufacturing, a static verification scheme was established based on the actual working conditions for the gooseneck chain on the civil aircraft structure, which ensured the accuracy and reliability of the test data and provided a reliability data basis for the establishment of the analysis/calculation MC2 method; the maximum principal strain was selected as the parameter for comparing the test data with the finite element analysis results. The results show that the error between the finite element analysis results and the mean value of the test data for different titanium alloy material properties is less than 10%, and without obtaining accurate material properties of the titanium alloy for additive manufacturing, the results of the finite element analysis using isotropic, elastic modulus E =110 GPa and Poisson′s ratio ν = 0.33 showed minimal deviation from the experimental data. This provides a reference for the design of other static verification test solution for small civil aircraft components manufactured with additive manufacturing of air-worthiness certification.

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