Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549531
K. Ai, E. Avital, T. Korakianitis, A. Samad, N. Venkatesan
The effect of surface waves on the hydrodynamic performance of a marine current turbine (MCT) is studied using the unsteady BEM method. The calculation are found to be in a very good agreement with experimental results of a small scale MCT. It is shown that a large amplitude wave, but still a long wave can affect the time-averaged coefficient of power and also introduce non-linearity in the time response of the turbine particularly at low tip speed ratio. This can have consequence for an effective control of the turbine. Instantaneous blade loading and power spectra are given and analyzed.
{"title":"Surface wave effect on marine current turbine, modelling and analysis","authors":"K. Ai, E. Avital, T. Korakianitis, A. Samad, N. Venkatesan","doi":"10.1109/ICMAE.2016.7549531","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549531","url":null,"abstract":"The effect of surface waves on the hydrodynamic performance of a marine current turbine (MCT) is studied using the unsteady BEM method. The calculation are found to be in a very good agreement with experimental results of a small scale MCT. It is shown that a large amplitude wave, but still a long wave can affect the time-averaged coefficient of power and also introduce non-linearity in the time response of the turbine particularly at low tip speed ratio. This can have consequence for an effective control of the turbine. Instantaneous blade loading and power spectra are given and analyzed.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"12 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121655652","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Flexible net, a new kind of future structure for advanced concepts in space exploration, has special potential application, such as capturing space debris and building huge antenna. A critical issue in the design and analysis of space net system is deployment modelling technology. As reliable tests cannot be performed under gravity, numerical analysis is necessary for the design of orbital capture. The dynamics behaviour of flexible net systems is investigated based on finite segment approach in this paper. The flexible net is modelled as a series of collected semi-damp springs with masses lumped at appropriated nodes. The motion equations of each tether node are developed with considering internal elastic force and external forces. The dynamics model has been verified by comparison with ground experiment, and used to investigate the deployment process in the orbital environment.
{"title":"Dynamics modelling and ground test of space nets","authors":"Q. Gao, Qingbin Zhang, Wuyu Peng, Qiangang Tang, Zhiwei Feng","doi":"10.1109/ICMAE.2016.7549608","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549608","url":null,"abstract":"Flexible net, a new kind of future structure for advanced concepts in space exploration, has special potential application, such as capturing space debris and building huge antenna. A critical issue in the design and analysis of space net system is deployment modelling technology. As reliable tests cannot be performed under gravity, numerical analysis is necessary for the design of orbital capture. The dynamics behaviour of flexible net systems is investigated based on finite segment approach in this paper. The flexible net is modelled as a series of collected semi-damp springs with masses lumped at appropriated nodes. The motion equations of each tether node are developed with considering internal elastic force and external forces. The dynamics model has been verified by comparison with ground experiment, and used to investigate the deployment process in the orbital environment.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121440777","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549595
Junliang Li, Ke-nan Teng, Chouzhou Yang, Baogang Li
Military aircraft is a complex repairable system, instantaneous availability analysis of it is a difficult problem in the integrated logistics support field. The SMTN (Stochastic Maintenance Task Net) based on mission requirement and technical condition of the military aircraft is constructed, and the maintenance function distribution types of activities in the SMTN are different. The moment generating function is defined, and the numerical characteristics of the system maintenance distribution function are solved. The functions are verified by substituting expectation and variance into different distribution functions, and the maintenance functions that meet the actual situation are selected. And the military aircraft availability in the mission preparation period is simulated. In the calculation process, a new algorithm is designed based on the Monte Carlo method, which can increase calculation efficiency and reflects the logic, topology and randomness of the maintenance process well. The simulation result can truly reflect the fluctuation of the instantaneous availability of military aircraft in the mission preparation period. This method can be applied widely in complex repairable system to provide basis for decision-making of the use of equipment, to provide quantitative indicators for support effectiveness evaluation of support system, and is of certain exploration value on the research of “dynamic” indicator in the integrated logistics support field.
{"title":"Research on the SMTN-based instantaneous availability of military aircraft in the mission preparation period","authors":"Junliang Li, Ke-nan Teng, Chouzhou Yang, Baogang Li","doi":"10.1109/ICMAE.2016.7549595","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549595","url":null,"abstract":"Military aircraft is a complex repairable system, instantaneous availability analysis of it is a difficult problem in the integrated logistics support field. The SMTN (Stochastic Maintenance Task Net) based on mission requirement and technical condition of the military aircraft is constructed, and the maintenance function distribution types of activities in the SMTN are different. The moment generating function is defined, and the numerical characteristics of the system maintenance distribution function are solved. The functions are verified by substituting expectation and variance into different distribution functions, and the maintenance functions that meet the actual situation are selected. And the military aircraft availability in the mission preparation period is simulated. In the calculation process, a new algorithm is designed based on the Monte Carlo method, which can increase calculation efficiency and reflects the logic, topology and randomness of the maintenance process well. The simulation result can truly reflect the fluctuation of the instantaneous availability of military aircraft in the mission preparation period. This method can be applied widely in complex repairable system to provide basis for decision-making of the use of equipment, to provide quantitative indicators for support effectiveness evaluation of support system, and is of certain exploration value on the research of “dynamic” indicator in the integrated logistics support field.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131180529","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549609
Jia Yu, Xiaodong Mao, G. Lin, L. Bai, Haichuan Jin, Z. Mu
Trajectory interference is a critical problem for the two-seat escape system in low speed which will seriously threaten the pilot's life. In this research, a divergence technology was designed and adopted. The computational simulation method was firstly utilized to analyze and evaluate the trajectory divergence characteristics involving divergence performance and the influence of divergence on ejection height. The mathematical formulations of the entire ejection sequence were established. According to the thoughts of modularization, a solver platform containing many modules depend on the basic physical parts was programmed. By the data flow between modules the realistic physical process could be simulated. The simulation results indicated that the divergence technology effectively prevent the two seats from interference at whole velocity range. Although the ejection height was maximum reduced 12 meters, the integrate performance of the system sufficed the life-saving demands. Subsequently, two-seat rocket sled test was implemented. The results showed that the interference was prevented and the parachute developed successfully before landing which ultimately verified the divergence technology in improving the performance of the two-seat escape system. Consequently, the technology could be applied in engineering.
{"title":"Study on trajectory divergence technology for double-seat escape system and experimental validation","authors":"Jia Yu, Xiaodong Mao, G. Lin, L. Bai, Haichuan Jin, Z. Mu","doi":"10.1109/ICMAE.2016.7549609","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549609","url":null,"abstract":"Trajectory interference is a critical problem for the two-seat escape system in low speed which will seriously threaten the pilot's life. In this research, a divergence technology was designed and adopted. The computational simulation method was firstly utilized to analyze and evaluate the trajectory divergence characteristics involving divergence performance and the influence of divergence on ejection height. The mathematical formulations of the entire ejection sequence were established. According to the thoughts of modularization, a solver platform containing many modules depend on the basic physical parts was programmed. By the data flow between modules the realistic physical process could be simulated. The simulation results indicated that the divergence technology effectively prevent the two seats from interference at whole velocity range. Although the ejection height was maximum reduced 12 meters, the integrate performance of the system sufficed the life-saving demands. Subsequently, two-seat rocket sled test was implemented. The results showed that the interference was prevented and the parachute developed successfully before landing which ultimately verified the divergence technology in improving the performance of the two-seat escape system. Consequently, the technology could be applied in engineering.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132672921","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549541
A. Jammal, C. Gu, Hui Wang, Rong-nian Li, Yuning Song, Y. Rong
Helical gears are known for high load carrying capacity and reduced noise generation characteristics. High speed will lead to increased dynamic loading, which is influential on the gear performance and premature failure. However, predicting the gear response under complex loading conditions becomes complicated, which leads to the need of developing an experimental test to anticipate the gear performance at selected boundary conditions. In the following paper, an experimental setup was developed with the aim to measure gears misalignments, temperatures and vibrations under random and fluctuating speeds. Consequently the effect of input variables can be inspected and the gears performance can be improved by implementing design modification and recommendations. Results showed that higher fluctuating speeds will affect misalignments, as well as vibration amplitudes will increase. Furthermore measured oil temperature varied with the speed increase which will lead to lower viscosity and potential contact surface wear and gear premature.
{"title":"An experimental study on high speed helical gears misalignments and dynamic behavior under random loading","authors":"A. Jammal, C. Gu, Hui Wang, Rong-nian Li, Yuning Song, Y. Rong","doi":"10.1109/ICMAE.2016.7549541","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549541","url":null,"abstract":"Helical gears are known for high load carrying capacity and reduced noise generation characteristics. High speed will lead to increased dynamic loading, which is influential on the gear performance and premature failure. However, predicting the gear response under complex loading conditions becomes complicated, which leads to the need of developing an experimental test to anticipate the gear performance at selected boundary conditions. In the following paper, an experimental setup was developed with the aim to measure gears misalignments, temperatures and vibrations under random and fluctuating speeds. Consequently the effect of input variables can be inspected and the gears performance can be improved by implementing design modification and recommendations. Results showed that higher fluctuating speeds will affect misalignments, as well as vibration amplitudes will increase. Furthermore measured oil temperature varied with the speed increase which will lead to lower viscosity and potential contact surface wear and gear premature.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133509866","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549607
Zihui Hao, Chao Yan, Yu-pei Qin, Lingjiu Zhou
Boundary layer transition is important for thermal protection and drag reduction in the design of hypersonic vehicles. A three-equation k-ω-γ model is applied in predicting a hypersonic flat plate transition with different Reynolds numbers. The transition onset advances with Reynolds number and the boundary thickness becomes thinner in the laminar zone before transition onset. The Mack modes dominate the hypersonic boundary layer transition. The first mode is viscous instability and the second mode is inviscid instability. The second mode distributes near the wall in the region Marel >1 and the value is larger than the first mode time scale in the laminar zone. The first and second mode time scale, non-turbulence viscosity and equivalent fluctuation kinetic both increase with Reynolds number increasing.
{"title":"Study of hypersonic boundary layer transition with different reynolds numbers","authors":"Zihui Hao, Chao Yan, Yu-pei Qin, Lingjiu Zhou","doi":"10.1109/ICMAE.2016.7549607","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549607","url":null,"abstract":"Boundary layer transition is important for thermal protection and drag reduction in the design of hypersonic vehicles. A three-equation k-ω-γ model is applied in predicting a hypersonic flat plate transition with different Reynolds numbers. The transition onset advances with Reynolds number and the boundary thickness becomes thinner in the laminar zone before transition onset. The Mack modes dominate the hypersonic boundary layer transition. The first mode is viscous instability and the second mode is inviscid instability. The second mode distributes near the wall in the region Marel >1 and the value is larger than the first mode time scale in the laminar zone. The first and second mode time scale, non-turbulence viscosity and equivalent fluctuation kinetic both increase with Reynolds number increasing.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133870567","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549537
D. Guo, Guojun Jiang, Xinbo Lin, Yue Wu
3D Laser-rapid Prototyping blisk blades could have more defects, like slag inclusions, cracks and incomplete fusions, than ones made by traditional machining. Therefore, a six-axis automated ultrasonic testing system (AUTS) was developed for 3D laser-rapid prototyping blisk blades in this paper. The applied technology is mainly about B-spline surface reconstruction from CAD, scan path planning based on B-spline surface and adaptive defect gating. In experiments conducted on blades with the system, defects could be clearly identified on generated 3D C-Scan images.
{"title":"Automated ultrasonic testing for 3D laser-rapid prototyping blisk blades","authors":"D. Guo, Guojun Jiang, Xinbo Lin, Yue Wu","doi":"10.1109/ICMAE.2016.7549537","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549537","url":null,"abstract":"3D Laser-rapid Prototyping blisk blades could have more defects, like slag inclusions, cracks and incomplete fusions, than ones made by traditional machining. Therefore, a six-axis automated ultrasonic testing system (AUTS) was developed for 3D laser-rapid prototyping blisk blades in this paper. The applied technology is mainly about B-spline surface reconstruction from CAD, scan path planning based on B-spline surface and adaptive defect gating. In experiments conducted on blades with the system, defects could be clearly identified on generated 3D C-Scan images.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115868931","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549517
Liu Guangwu, Li Yangang
Optically transparent silica aerogel with high specific surface area and low density based on tetramethyl orthosilicate (TMOS) were prepared by using a two-step sol-gel process. Obtained aerogels are more transparent than conventional samples, and the refractive index is well controlled in the acetonitrile supercritical drying process. We developed monolithic aerogels with a density of 0.04g/cm3 as space dust capturer. The microstructure and morphology of highly transparence silica aerogels were characterized by the specific surface area, SEM, UV-Vis and the pore size distribution techniques. The results shown that highly transparence silica aerogels are with excellent performance in physical properties, such as high optical transmittance (86.4%, 800 nm), low density (0.04 g/cm3), high specific surface area (925.4 m /g) and large pore volume (2.4 cm3/g). Which are critical characteristics for practical applications of highly transparent silica aerogel, particularly in particle capture areas, for easy observation and lossless capture.
以正硅酸四甲基(TMOS)为基料，采用溶胶-凝胶两步法制备了高比表面积、低密度的光学透明二氧化硅气凝胶。所得气凝胶比常规样品更透明，在乙腈超临界干燥过程中折射率得到了很好的控制。我们开发了密度为0.04g/cm3的单片气凝胶作为空间尘埃捕集器。采用比表面积、扫描电镜、紫外可见光谱和孔径分布技术对高透明二氧化硅气凝胶的微观结构和形貌进行了表征。结果表明，高透明二氧化硅气凝胶具有高透光率(86.4%，800 nm)、低密度(0.04 g/cm3)、高比表面积(925.4 m /g)和大孔体积(2.4 cm3/g)等优异的物理性能。这是高透明二氧化硅气凝胶实际应用的关键特性，特别是在颗粒捕获区域，便于观察和无损捕获。
{"title":"Fabrication and properties of optically transparent silica aerogels for hypervelocity particle capture","authors":"Liu Guangwu, Li Yangang","doi":"10.1109/ICMAE.2016.7549517","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549517","url":null,"abstract":"Optically transparent silica aerogel with high specific surface area and low density based on tetramethyl orthosilicate (TMOS) were prepared by using a two-step sol-gel process. Obtained aerogels are more transparent than conventional samples, and the refractive index is well controlled in the acetonitrile supercritical drying process. We developed monolithic aerogels with a density of 0.04g/cm3 as space dust capturer. The microstructure and morphology of highly transparence silica aerogels were characterized by the specific surface area, SEM, UV-Vis and the pore size distribution techniques. The results shown that highly transparence silica aerogels are with excellent performance in physical properties, such as high optical transmittance (86.4%, 800 nm), low density (0.04 g/cm3), high specific surface area (925.4 m /g) and large pore volume (2.4 cm3/g). Which are critical characteristics for practical applications of highly transparent silica aerogel, particularly in particle capture areas, for easy observation and lossless capture.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131743990","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549596
Chenghu Jing, Hongguang Xu
In mechanical engineering, especially in the aerospace, actuator systems must be tested under the corresponding load conditions. The conventional load simulator is disturbed by the motion of tested actuator, which seriously affects the loading performance. This paper presents an electro-hydraulic friction load simulator (EHFLS) for actuator test that is not disturbed by the motion of tested actuator in theory. Its mathematical model is constructed. Theoretically analyzing, friction is the key factor to affect the loading performance. Simulations are performed to discuss how the loading performance of the electro-hydraulic friction load simulator is affected by friction.
{"title":"A study on the influence of friction on loading performance of electro-hydraulic friction load simulator for actuator test","authors":"Chenghu Jing, Hongguang Xu","doi":"10.1109/ICMAE.2016.7549596","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549596","url":null,"abstract":"In mechanical engineering, especially in the aerospace, actuator systems must be tested under the corresponding load conditions. The conventional load simulator is disturbed by the motion of tested actuator, which seriously affects the loading performance. This paper presents an electro-hydraulic friction load simulator (EHFLS) for actuator test that is not disturbed by the motion of tested actuator in theory. Its mathematical model is constructed. Theoretically analyzing, friction is the key factor to affect the loading performance. Simulations are performed to discuss how the loading performance of the electro-hydraulic friction load simulator is affected by friction.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"38 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133836860","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549548
Karuppasamy Pandian Marimuthu, Felix Rickhey, Hyungyil Lee, Jin Haeng Lee
This work aims at characterizing the formation of cone-cracks in brittle materials upon spherical indentation. The cone-cracking is simulated by the extended finite element method (XFEM) in Abaqus / Standard. The element size-dependency is reduced by scaling the damage initiation strength based on mean stress criterion and calibration techniques. The formation of a kinked-cone-crack is observed when the indenter comes into (second) contact with the surface part outside the ring crack. After analyzing the effects of friction, Poisson's ratio on cone-crack evolution, a database for enhanced Roesler's constant, which considers the effect of cone-crack-kinking, is provided by performing systematic XFE analyses. This database can be used for the fracture toughness evaluation in brittle materials.
{"title":"Spherical indentation cracking in brittle materials: An XFEM study","authors":"Karuppasamy Pandian Marimuthu, Felix Rickhey, Hyungyil Lee, Jin Haeng Lee","doi":"10.1109/ICMAE.2016.7549548","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549548","url":null,"abstract":"This work aims at characterizing the formation of cone-cracks in brittle materials upon spherical indentation. The cone-cracking is simulated by the extended finite element method (XFEM) in Abaqus / Standard. The element size-dependency is reduced by scaling the damage initiation strength based on mean stress criterion and calibration techniques. The formation of a kinked-cone-crack is observed when the indenter comes into (second) contact with the surface part outside the ring crack. After analyzing the effects of friction, Poisson's ratio on cone-crack evolution, a database for enhanced Roesler's constant, which considers the effect of cone-crack-kinking, is provided by performing systematic XFE analyses. This database can be used for the fracture toughness evaluation in brittle materials.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116272927","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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