摘要
液体火箭发动机中大量采用延性铜合金,严苛载荷导致其普遍工作于大塑性变形状态。由于无法有效处理拉伸试验颈缩后数据,传统工程强度分析所用材料本构无法充分反映出材料的真实承载能力。针对某延性铜合金开展常温单轴拉伸试验,并从工程强度分析的角度提出通用修正函数与参数拟合原则,随后通过有限元颈缩仿真拟合得到加权因子w=0.75和指数修正因子n=2.4。研究表明,有限元颈缩仿真的载荷-位移响应对模型参数和网格具有收敛性,指数修正方法可更好地描述铜合金试件颈缩后响应,选取n=2.4可得到偏保守的材料性能估计。
Ductile copper alloys are widely used in liquid rocket engines,which are generally subjected to large plastic deformation due to extreme loads.Due to the lack of method to effectively process the post-necking data of tensile tests,traditional material constitutive models used in engineering structural analysis failed to fully reflect the real bearing capacity of materials.Uniaxial tensile tests were carried out at room temperature for a ductile copper alloy,and the universal correction function and parameter fitting principles were proposed from the perspective of engineering structural strength analysis.Then,the weighted factor w=0.75 and the exponential correction factor n=2.4 were obtained through the FEM necking simulation.The results show that the load-displacement response of the finite element necking simulation is convergent to the model parameters and mesh.The exponential correction method can better describe the post-necking response of copper alloy specimens.A conservative material property estimate can be obtained by selecting n=2.4.
作者
张凭
李斌
高玉闪
王振
姜薇
霍世慧
ZHANG Ping;LI Bin;GAO Yushan;WANG Zhen;JIANG Wei;HUO Shihui(National Key Laboratory of Aerospace Liquid Propulsion,Xi’an 710100,China;Academy of Aerospace Propulsion Technology,Xi’an 710100,China)
出处
《火箭推进》
CAS
北大核心
2024年第2期130-139,共10页
Journal of Rocket Propulsion
关键词
铜合金
延性
颈缩
应力-应变曲线
单轴拉伸
修正方法
copper alloy
ductility
necking
stress-strain curve
uniaxial tension
correction
