WO2023151233A1 - 基于虚拟应变能的金属材料多轴疲劳寿命预测方法与系统 - Google Patents

基于虚拟应变能的金属材料多轴疲劳寿命预测方法与系统 Download PDF

Info

Publication number
WO2023151233A1
WO2023151233A1 PCT/CN2022/107269 CN2022107269W WO2023151233A1 WO 2023151233 A1 WO2023151233 A1 WO 2023151233A1 CN 2022107269 W CN2022107269 W CN 2022107269W WO 2023151233 A1 WO2023151233 A1 WO 2023151233A1
Authority
WO
WIPO (PCT)
Prior art keywords
strain energy
stress
shear
shear strain
plane
Prior art date
Application number
PCT/CN2022/107269
Other languages
English (en)
French (fr)
Chinese (zh)
Inventor
王英玉
王文轩
龚帅
张晓凡
姚卫星
Original Assignee
南京航空航天大学
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 南京航空航天大学 filed Critical 南京航空航天大学
Priority to JP2022577653A priority Critical patent/JP7479727B2/ja
Publication of WO2023151233A1 publication Critical patent/WO2023151233A1/zh

Links

Images

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • G—PHYSICS
    • G16—INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR SPECIFIC APPLICATION FIELDS
    • G16C—COMPUTATIONAL CHEMISTRY; CHEMOINFORMATICS; COMPUTATIONAL MATERIALS SCIENCE
    • G16C60/00—Computational materials science, i.e. ICT specially adapted for investigating the physical or chemical properties of materials or phenomena associated with their design, synthesis, processing, characterisation or utilisation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
    • Y02P90/30—Computing systems specially adapted for manufacturing

Definitions

  • the invention relates to a method and system for predicting the multiaxial fatigue life of metal materials based on virtual strain energy, which belongs to the field of life prediction of metal materials in additive manufacturing and can be used in the technical field of aviation systems.
  • AWA additive manufacturing
  • Aircraft structures are subjected to complex multiaxial loads in service. For example, an airfoil as a whole is subjected to shear forces, bending moments, and torques. The skin on the wing will experience both normal and shear stresses. Aircraft landing gear structures are subjected to loads from multiple directions during takeoff and landing. Multiaxial fatigue failure is often the cause of failure of these structures. At present, the prediction of multiaxial fatigue life is mainly by equating the multiaxial stress state to the uniaxial stress state, and then predicting the fatigue life according to the uniaxial stress life curve. These methods can be divided into stress criteria, strain criteria and energy criteria.
  • the energy criterion believes that the accumulation of energy near the fatigue danger point is the cause of fatigue damage, which is more in line with the internal mechanism of fatigue damage. At the same time, energy is a scalar quantity, and the calculation process is relatively simple. However, various methods are suitable for specific materials or loading conditions, and there is currently no recognized method for multiaxial fatigue life prediction of additively manufactured metal materials that meets the requirements of engineering structure design.
  • the purpose of the present invention is to provide a multi-axial virtual strain energy processing method to solve the problem of multi-axial fatigue life prediction of metal materials in additive manufacturing.
  • a method for predicting the multiaxial fatigue life of metal materials based on virtual strain energy comprising the following steps:
  • said step (1) includes:
  • three-dimensional modeling software is used to draw the geometric model of the component, and the mesh is divided, and the mesh is refined near the fatigue dangerous point; the material properties are assigned to the finite element model, and boundary conditions are added to the finite element model, Simulate the load condition of the component in the real environment; obtain the stress-strain load time history at the dangerous point through finite element analysis.
  • the shear strain energy calculation method on each plane passing through the dangerous point in the step (2) includes:
  • a local Cartesian coordinate system Oxyz is established at the fatigue hazard point O, and any plane ⁇ passing through the hazard point O can be used for two direction vectors and a plane
  • the vector a is the intersection line between the plane ⁇ and the plane Oxy in the coordinate system Oxyz
  • the vector b is a vector perpendicular to the a-axis on the plane ⁇
  • n is the normal vector of the plane ⁇ .
  • the position relationship between the vector n, a, b and the coordinate system Oxyz can use three angles said, among them, is the angle between the direction normal vector n of the plane ⁇ and the x-axis; ⁇ is the angle between the direction normal vector n of the plane ⁇ and the z-axis, and ⁇ is the angle between any vector q and the vector a on the plane ⁇ .
  • the stress-strain load time history at the dangerous point O is represented by the following matrix:
  • ⁇ x (t), ⁇ y (t), ⁇ z (t) are normal stress components
  • ⁇ xy (t), ⁇ yz (t) are shear stress components
  • ⁇ x ( t) are positive strain components
  • ⁇ xy (t) ⁇ yz (t)
  • ⁇ xz (t) are shear strain components
  • t is in the interval [0, T] at any time
  • the mean value of the normal stress ⁇ n,m on any plane is defined as the average value of the integral of the normal stress in the interval [0,T], and the amplitude of the normal stress ⁇ n,a is defined by the variance of the normal stress
  • the 4 ⁇ a ⁇ a multiaxial stress ratio ⁇ is defined as the ratio of the maximum normal stress ⁇ n,max to the shear stress amplitude ⁇ a :
  • the shear strain energy life curve under uniaxial tension and compression load and torsional load is determined according to the following method:
  • ⁇ is the shear strain energy
  • N f is the lifetime
  • the normalized virtual strain energy W V in the step (3) is expressed as:
  • the present invention provides a multi-axis fatigue life prediction system for metal materials based on virtual strain energy, including an input module, a processing module and an output module, the input module is used to input the geometric model of the metal member and the external load ; The output module is used to display the life of the predicted metal component under a given external load; the processing module includes:
  • the stress-strain calculation unit is used to conduct finite element analysis on metal components, determine the dangerous point and calculate the stress-strain load time history at the dangerous point;
  • the critical surface calculation unit is used to calculate the shear strain energy of each plane passing through the dangerous point, and the plane with the largest shear strain energy is used as the critical surface to obtain the shear strain energy and the multiaxial stress ratio on the critical surface;
  • the shear strain energy is defined as is the product of the shear stress amplitude and the shear strain amplitude
  • the multiaxial stress ratio is defined as the ratio of the maximum value of the normal stress on the critical surface to the shear stress amplitude;
  • Shear strain energy is the normalized strain energy.
  • the shear-strain energy life curve under uniaxial tension-compression load and torsional load is generated by a power function fitting unit, and the power function fitting unit is used to calculate each fatigue life curve under uniaxial tension-compression load and torsional load respectively.
  • the shear strain energy on the critical surface of the data points is connected end to end to draw the shear strain energy-life curve, and the parameters A 1 , B 1 , A 3 , B 3 .
  • the normalized virtual strain energy W V in the prediction unit is expressed as:
  • a computer system provided by the present invention includes a memory, a processor, and a computer program stored on the memory and operable on the processor.
  • the computer program When the computer program is loaded into the processor, the described Multiaxial fatigue life prediction method for metallic materials based on virtual strain energy.
  • the present invention analyzes the shear strain energy life curves of typical ductile metal materials under uniaxial tension, compression and torsion states, and finds that the shear strain energy and life under the two loading conditions have a good logarithmic linear relationship, based on the following Two points are considered to normalize the shear strain energy to obtain the virtual strain energy, and use the shear strain energy life curve of torsional load for life prediction, so that it can be used for life analysis problems of different load paths: one is the fatigue crack of ductile metal materials The behavior is manifested as shear failure, and the shear strain energy life curve of torsional load is more intuitive; second, the shear strain energy life curve of torsional load is often located at the top of all curves, and it is more intuitive to fit under this curve, and normalized The coefficient form is relatively simple.
  • the traditional stress criterion is often used for high cycle fatigue with small plastic strain
  • the strain criterion is often used for low cycle fatigue with large plastic strain.
  • the present invention adopts the energy criterion of multiplying stress and strain to take into account both low cycle and high cycle fatigue. .
  • Fig. 1 is an overall flow chart of the embodiment of the present invention.
  • Fig. 2 is a schematic diagram of definition of a local coordinate system at a dangerous point involved in an embodiment of the present invention.
  • Fig. 3 is a flow chart of detailed calculation of fatigue life in an embodiment of the present invention.
  • Fig. 4 is a graph showing the change of shear strain energy with the service life of the 316L steel of the experimental example of the present invention under uniaxial tension, compression and torsional loads.
  • Fig. 5 is a schematic diagram of grid division for finite element modeling of an experimental example of the present invention.
  • Fig. 6 is a graph comparing the prediction results and test results of the experimental example of the present invention.
  • Fig. 7 is a schematic diagram of the module structure of the embodiment of the present invention.
  • the material properties are given to the finite element model, and the linear elastic or elastoplastic constitutive model is selected according to whether the material has plastic strain during the fatigue test;
  • the finite element analysis obtains the stress-strain load time history at the dangerous point O for subsequent calculation.
  • a local Cartesian coordinate system Oxyz is established at the fatigue hazard point O, and any plane ⁇ passing through the hazard point O can be used for two direction vectors and a plane
  • the vector a is the intersection line between the plane ⁇ and the plane Oxy in the coordinate system Oxyz
  • the vector b is a vector perpendicular to the a-axis on the plane ⁇
  • n is the normal vector of the plane ⁇ .
  • the position relationship between the vector n, a, b and the coordinate system Oxyz can use three angles said, among them, is the angle between the direction normal vector n of the plane ⁇ and the x-axis; ⁇ is the angle between the direction normal vector n of the plane ⁇ and the z-axis, and ⁇ is the angle between any vector q and the vector a on the plane ⁇ .
  • the stress-strain load time history at the dangerous point O can be expressed by the following matrix:
  • ⁇ x (t), ⁇ y (t), ⁇ z (t) are normal stress components
  • ⁇ xy (t), ⁇ yz (t) are shear stress components
  • ⁇ x ( t), ⁇ y (t), ⁇ z (t) are positive strain components
  • ⁇ xy (t), ⁇ yz (t) are shear strain components
  • t is in the interval [0, T] any moment.
  • the mean value of the normal stress ⁇ n,m on any plane is defined as the average value of the integral of the normal stress in the interval [0,T], and the amplitude of the normal stress ⁇ n,a is defined by the variance of the normal stress
  • the multiaxial stress ratio ⁇ is defined as the ratio of the maximum normal stress ⁇ n,max to the shear stress amplitude ⁇ a , namely:
  • the virtual strain energy is the strain energy after normalization of the shear strain energy in the shear strain energy life curve under uniaxial tension-compression load and torsional load.
  • the shear strain energy life curve under uniaxial tension-compression load and torsional load is determined in advance according to the data of uniaxial tension-compression and torsional fatigue test of the material. Specifically:
  • the virtual strain energy calculates the fatigue life by normalizing the shear strain energy for different load paths:
  • the multiaxial stress ratio ⁇ is used to reflect the influence of different load paths.
  • the solution of the present invention will be further verified with a specific experimental example below.
  • the material used in this example is 316L stainless steel produced by selective laser melting. Fatigue tests with multiple load paths, namely uniaxial tension-compression, torsion, proportional and 90° non-proportional multiaxial loading, were carried out.
  • the finite element analysis of the test piece is carried out to determine the dangerous point and calculate the stress-strain load time history [ ⁇ (t)], [ ⁇ (t)] at the dangerous point; then the shear strain energy ⁇ and Multiaxial stress ratio ⁇ ; then determine the model parameters A 1 , B 1 , A 3 , and B 3 according to the uniaxial tension-compression and torsion fatigue test data of the material; finally calculate the virtual strain energy W V at the dangerous point under the load to be determined and solve Lifetime N f .
  • the detailed process is as follows:
  • test piece used in this example is additively manufactured 316L steel, a solid round bar with a gauge length of 38mm and a diameter of 12mm.
  • Use MTS809 tension and torsion testing machine to carry out uniaxial tension and compression without average stress, torsion, multiaxial proportional load, 90° non-proportional load and uniaxial tension and compression with average stress, multiaxial proportional load, 90° non-proportional load test .
  • the fatigue data of the uniaxial tension-compression and torsion test pieces are used to determine the parameters of the model of the present invention, and the fatigue data of other load paths are used to verify the correctness of the model of the present invention.
  • the specific test data are as shown in table 1, wherein the load ratio R is The ratio of the minimum value to the maximum value of the stress is used to describe the size of the average stress, and the phase angle ⁇ is the phase difference between the normal stress and the shear stress, which is used to describe the degree of non-proportionality.
  • the finite element software Patran & Nastran is used for finite element analysis.
  • the center of mass of the test piece is taken as the origin, and the axial direction of the test piece is the x-axis, and the overall coordinate system is established. Since the stress-strain state of each point on the surface of the gauge section of the smooth specimen is the same, cracks may initiate from any position on the surface of the gauge section. It may be assumed that the fatigue dangerous point is a point with coordinates (0,6,0).
  • Mesh division adopts the method of establishing two-dimensional shell elements first, and then rotating and sweeping along the axis to generate three-dimensional solid elements, and locally encrypts the fatigue dangerous points, and divides 20 elements into 1mm.
  • the finite element modeling results are shown in Figure 5.
  • one end of the test piece is fixed, and the other end is established with MPC and load is applied.
  • an embodiment of the present invention provides a virtual strain energy-based multiaxial fatigue life prediction system for metal materials, as shown in Figure 7, including an input module, a processing module and an output module, the input module is used for Input the geometric model of the metal component and the external load; the output module is used to display the predicted life of the metal component under a given external load; the processing module includes: a stress-strain calculation unit for performing finite element analysis on the metal component, Determine the dangerous point and calculate the stress-strain load time history at the dangerous point; the critical surface calculation unit is used to calculate the shear strain energy of each plane passing through the dangerous point, and the plane with the largest shear strain energy is the critical surface to obtain the critical surface The shear strain energy and the multiaxial stress ratio; where the shear strain energy is defined as the product of the shear stress amplitude and the shear strain amplitude, and the multiaxial stress ratio is defined as the ratio of the maximum value of the normal stress on the critical surface to the shear stress amplitude; and The prediction unit is used to
  • the shear-strain energy life curve under uniaxial tension-compression load and torsional load is generated by a power function fitting unit, which is used to calculate the critical surface of each fatigue data point under uniaxial tension-compression and torsional load respectively.
  • the shear strain energy is connected end to end to draw the shear strain energy-life curve, and the power function is used to fit and solve the parameters of the shear strain energy-life curve under the two loading conditions.
  • a computer system provided by an embodiment of the present invention includes a memory, a processor, and a computer program stored in the memory and operable on the processor.
  • the computer program When the computer program is loaded into the processor, the A multiaxial fatigue life prediction method for metallic materials based on virtual strain energy.
  • the storage medium includes: a U disk, a mobile hard disk, a read-only memory ROM, a random access memory RAM, a magnetic disk or an optical disk, and other media capable of storing computer programs.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • Geometry (AREA)
  • General Physics & Mathematics (AREA)
  • Computing Systems (AREA)
  • Computer Hardware Design (AREA)
  • Evolutionary Computation (AREA)
  • General Engineering & Computer Science (AREA)
  • Pure & Applied Mathematics (AREA)
  • Mathematical Optimization (AREA)
  • Mathematical Analysis (AREA)
  • Computational Mathematics (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Bioinformatics & Cheminformatics (AREA)
  • Bioinformatics & Computational Biology (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
PCT/CN2022/107269 2022-02-09 2022-07-22 基于虚拟应变能的金属材料多轴疲劳寿命预测方法与系统 WO2023151233A1 (zh)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2022577653A JP7479727B2 (ja) 2022-02-09 2022-07-22 仮想歪みエネルギーに基づく金属材料の多軸疲労寿命予測方法及びシステム

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN202210120848.2A CN114580098B (zh) 2022-02-09 2022-02-09 基于虚拟应变能的金属材料多轴疲劳寿命预测方法与系统
CN202210120848.2 2022-02-09

Publications (1)

Publication Number Publication Date
WO2023151233A1 true WO2023151233A1 (zh) 2023-08-17

Family

ID=81773855

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2022/107269 WO2023151233A1 (zh) 2022-02-09 2022-07-22 基于虚拟应变能的金属材料多轴疲劳寿命预测方法与系统

Country Status (3)

Country Link
JP (1) JP7479727B2 (ja)
CN (1) CN114580098B (ja)
WO (1) WO2023151233A1 (ja)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117131748A (zh) * 2023-10-26 2023-11-28 湖南云箭科技有限公司 基于静动疲劳分析的结构抗疲劳分析方法及系统
CN117373580A (zh) * 2023-12-05 2024-01-09 宝鸡富士特钛业（集团）有限公司 基于时序网络实现钛合金产品的性能分析方法及系统
CN117540494A (zh) * 2024-01-10 2024-02-09 天目山实验室 一种航空舱段结构降阶分析方法、系统及设备
CN117571507A (zh) * 2024-01-16 2024-02-20 中国航空工业集团公司金城南京机电液压工程研究中心 一种单向复合材料界面剪应力值的计算方法
CN118130098A (zh) * 2024-05-10 2024-06-04 中国航发四川燃气涡轮研究院 发动机轴类零件振扭比获取方法
CN118171397A (zh) * 2024-05-15 2024-06-11 三一重型装备有限公司 拨档齿轮轴的拨档寿命次数确定方法、装置及设备
CN118364533A (zh) * 2024-03-05 2024-07-19 广西南宾公路建设发展有限公司 一种压力锚杆剪切抗力预测方法及锚固力优化系统
CN118675670A (zh) * 2024-08-20 2024-09-20 南昌大学 表面粗糙度对金属材料疲劳性能影响的数值模拟量化方法

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114580098B (zh) * 2022-02-09 2024-08-06 南京航空航天大学 基于虚拟应变能的金属材料多轴疲劳寿命预测方法与系统
CN115310311B (zh) * 2022-07-01 2023-08-01 南京航空航天大学 一种金属材料在谱载荷下疲劳寿命计算方法
CN115982907B (zh) * 2022-12-27 2023-10-17 重庆科技学院 一种海洋深水钻井导管或者表层套管疲劳分析方法及系统

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107423540A (zh) * 2017-04-09 2017-12-01 北京工业大学 一种基于权平均最大剪切应变幅平面的多轴疲劳寿命预测方法
CN109241577A (zh) * 2018-08-14 2019-01-18 南京航空航天大学 一种预测多轴疲劳寿命的修正fs法
WO2021227925A1 (zh) * 2020-05-09 2021-11-18 清华大学 基于主载荷模式的缺口件疲劳寿命预测方法及预测装置
CN114580098A (zh) * 2022-02-09 2022-06-03 南京航空航天大学 基于虚拟应变能的金属材料多轴疲劳寿命预测方法与系统

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2005227065A (ja) 2004-02-12 2005-08-25 Hitachi Ltd 構造物の推定寿命表示方法、寿命分布作成方法、画像表示装置
US9243985B2 (en) 2009-10-05 2016-01-26 Board Of Supervisors Of Louisiana State University And Agricultural And Mechanical College Fracture fatigue entropy determination
CN106354898B (zh) * 2016-06-28 2019-05-03 湖南工业大学 一种基于总应变能量密度的焊缝疲劳寿命计算方法
CN109885874B (zh) 2019-01-11 2022-12-23 华东理工大学 一种基于abaqus的多轴蠕变疲劳预测方法
CN109948216B (zh) 2019-03-12 2023-01-03 华东理工大学 总应变能密度修正的缺口件低周疲劳预测方法
CN110274826B (zh) 2019-07-17 2020-10-09 北京航空航天大学 基于单轴s-n的硬质金属多轴高周疲劳寿命预测方法
CN110362940B (zh) * 2019-07-19 2022-05-17 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） 复杂载荷作用下海洋工程结构极限承载能力计算方法
KR20230007422A (ko) * 2020-04-28 2023-01-12 스트롱 포스 티피 포트폴리오 2022, 엘엘씨 운송 시스템용 디지털 트윈 시스템 및 방법
CN111881603B (zh) * 2020-07-17 2023-04-14 北京理工大学 一种考虑失效相关性的机械结构疲劳可靠性评估方法
CN112711835B (zh) 2020-12-16 2022-10-21 北京理工大学 一种基于修正塑性应变能的金属材料疲劳寿命预测方法
CN113312817B (zh) 2021-05-31 2022-05-20 中国石油大学(华东) 一种小冲杆疲劳试验获得材料应变-寿命曲线的方法
CN113435017B (zh) * 2021-06-10 2022-08-19 北京理工大学 一种jh-2本构完整强度方程参数的优化方法
CN113987681A (zh) 2021-11-02 2022-01-28 电子科技大学 缺口-尺寸效应下耦合应变能梯度的结构疲劳寿命评估方法

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107423540A (zh) * 2017-04-09 2017-12-01 北京工业大学 一种基于权平均最大剪切应变幅平面的多轴疲劳寿命预测方法
CN109241577A (zh) * 2018-08-14 2019-01-18 南京航空航天大学 一种预测多轴疲劳寿命的修正fs法
WO2021227925A1 (zh) * 2020-05-09 2021-11-18 清华大学 基于主载荷模式的缺口件疲劳寿命预测方法及预测装置
CN114580098A (zh) * 2022-02-09 2022-06-03 南京航空航天大学 基于虚拟应变能的金属材料多轴疲劳寿命预测方法与系统

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117131748A (zh) * 2023-10-26 2023-11-28 湖南云箭科技有限公司 基于静动疲劳分析的结构抗疲劳分析方法及系统
CN117131748B (zh) * 2023-10-26 2024-01-30 湖南云箭科技有限公司 基于静动疲劳分析的结构抗疲劳分析方法及系统
CN117373580A (zh) * 2023-12-05 2024-01-09 宝鸡富士特钛业（集团）有限公司 基于时序网络实现钛合金产品的性能分析方法及系统
CN117373580B (zh) * 2023-12-05 2024-03-08 宝鸡富士特钛业（集团）有限公司 基于时序网络实现钛合金产品的性能分析方法及系统
CN117540494A (zh) * 2024-01-10 2024-02-09 天目山实验室 一种航空舱段结构降阶分析方法、系统及设备
CN117540494B (zh) * 2024-01-10 2024-04-05 天目山实验室 一种航空舱段结构降阶分析方法、系统及设备
CN117571507A (zh) * 2024-01-16 2024-02-20 中国航空工业集团公司金城南京机电液压工程研究中心 一种单向复合材料界面剪应力值的计算方法
CN117571507B (zh) * 2024-01-16 2024-04-09 中国航空工业集团公司金城南京机电液压工程研究中心 一种单向复合材料界面剪应力值的计算方法
CN118364533A (zh) * 2024-03-05 2024-07-19 广西南宾公路建设发展有限公司 一种压力锚杆剪切抗力预测方法及锚固力优化系统
CN118130098A (zh) * 2024-05-10 2024-06-04 中国航发四川燃气涡轮研究院 发动机轴类零件振扭比获取方法
CN118171397A (zh) * 2024-05-15 2024-06-11 三一重型装备有限公司 拨档齿轮轴的拨档寿命次数确定方法、装置及设备
CN118675670A (zh) * 2024-08-20 2024-09-20 南昌大学 表面粗糙度对金属材料疲劳性能影响的数值模拟量化方法

Also Published As

Publication number Publication date
JP7479727B2 (ja) 2024-05-09
JP2024513620A (ja) 2024-03-27
CN114580098A (zh) 2022-06-03
CN114580098B (zh) 2024-08-06

Similar Documents

Publication Publication Date Title
WO2023151233A1 (zh) 基于虚拟应变能的金属材料多轴疲劳寿命预测方法与系统
CN111460583B (zh) 一种针对复杂几何结构件的蠕变-疲劳寿命设计方法
Luo et al. A notch critical plane approach of multiaxial fatigue life prediction for metallic notched specimens
CN107389471A (zh) 裂纹失效模式判定方法及基于该方法的疲劳寿命预测方法
Yang et al. Multi-objective optimization of parallel manipulators using a game algorithm
Li et al. Multiaxial fatigue damage and reliability assessment of aero-engine compressor blades made of TC4 titanium alloy
Linjiang et al. Inverse identification of constitutive parameters of Ti2AlNb intermetallic alloys based on cooperative particle swarm optimization
Savage The influence of crystal orientation on the elastic stresses of a single crystal nickel-based turbine blade
CN112528415B (zh) 一种复合材料轴结构宏-细观失效模式分析方法
Luo et al. Fatigue life prediction of vortex reducer based on stress gradient
CN109241577A (zh) 一种预测多轴疲劳寿命的修正fs法
Jing et al. Influence of size effect on the dynamic mechanical properties of OFHC copper at micro-/meso-scales
Ma et al. Finite element modeling of straight pipeline with partially attached viscoelastic damping patch based on variable thickness laminated element
Wu et al. Multiaxial low-cycle fatigue life model for notched specimens considering small sample characteristics
Huang et al. Computational analysis of torsional bulking behavior of 3D 4-directional braided composites shafts
Zhang et al. Residual stress and deformation analysis of lattice compressor impeller based on 3D printing simulation
He et al. Probabilistic fatigue evaluation of notched specimens considering small sample properties under multiaxial loading
Kirane et al. Grain level dwell fatigue crack nucleation model for Ti alloys using crystal plasticity finite element analysis
Zhang et al. Performance-oriented digital twin assembly of high-end equipment: a review
Wu et al. Residual stress homogenization of SiC P/Al composites with thermal vibration coupling
KR100799207B1 (ko) 고주기 피로 수명 해석 방법
Peng et al. A detected-data-enhanced FEM for residual stress reconstruction and machining deformation prediction
Zhang et al. Three-dimensional dynamic modeling and analysis of flexible robot with coupling deformation based on spinor theory
Zhu et al. Load-spectrum-based high-cycle fatigue life assessment of the crane arms
Feng et al. Research Progress on Prediction Models of Plastic Deformation and Ductile Fracture of Titanium Alloy

Legal Events

Date Code Title Description
WWE Wipo information: entry into national phase

Ref document number: 2022577653

Country of ref document: JP

121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 22925592

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE