Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549575
K. Nikolajevic, N. Bélanger
3D path planning close to helicopters' flight dynamics limits is a critical challenge to enhance missions' assistance or autonomy. Pure dynamics model with successive integrations, Pythagorian Hodograph methods or fictive potential fields bring different drawbacks that cannot solve the problem of connecting 3D positions with associated complex set of constraints (speed orientation, curvature, torsion...) in a satisfying way. We propose in the present paper a new method based on enhanced 3D motions primitives. Their construction has been possible due to the transformation of flight loop numerical simulations into a symbolic and infinitely derivable model based on Beziers curves. Our algorithm defines strategic forms like cylinders referring to Dubins circles or vertical planes and hooks them up with the ad hoc 3D motion primitives while minimizing the curvilinear abscissa according to new principles, which are introduced. The concepts are tested for two path-planning problems and then validated against a reconstructed helicopter accident. The performance of the algorithm is measured versus an ideal Dubins-like 3D path metrics. The extremely good results we obtained pushes the challenge a step further to build up “an all flight contexts” model for the future.
{"title":"A new method based on motion primitives to compute 3D path planning close to helicopters' flight dynamics limits","authors":"K. Nikolajevic, N. Bélanger","doi":"10.1109/ICMAE.2016.7549575","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549575","url":null,"abstract":"3D path planning close to helicopters' flight dynamics limits is a critical challenge to enhance missions' assistance or autonomy. Pure dynamics model with successive integrations, Pythagorian Hodograph methods or fictive potential fields bring different drawbacks that cannot solve the problem of connecting 3D positions with associated complex set of constraints (speed orientation, curvature, torsion...) in a satisfying way. We propose in the present paper a new method based on enhanced 3D motions primitives. Their construction has been possible due to the transformation of flight loop numerical simulations into a symbolic and infinitely derivable model based on Beziers curves. Our algorithm defines strategic forms like cylinders referring to Dubins circles or vertical planes and hooks them up with the ad hoc 3D motion primitives while minimizing the curvilinear abscissa according to new principles, which are introduced. The concepts are tested for two path-planning problems and then validated against a reconstructed helicopter accident. The performance of the algorithm is measured versus an ideal Dubins-like 3D path metrics. The extremely good results we obtained pushes the challenge a step further to build up “an all flight contexts” model for the future.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"35 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":"130424623","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.2016.7549611
Arslan Ahmed, R. Tiwari, M. Shah, Jiachen Yin
The amplitude and/or phase fluctuations in the received signal can severely affect the performance of the Global Positioning System (GPS). These amplitude and phase fluctuations arises when the GPS signal passes through the time-varying electron density irregularities in the ionosphere which can result in loss of lock due to cycle slip in the receiver tracking loop. During cycle slip, the phase jitter serves as an important parameter for updating the receiver tracking loop parameters for efficient tracking either by using a software-based GPS receiver or by hardware modifications. In this paper, a new method of estimating the tracking loop phase jitter is proposed which uses dual frequency based time and spatial variations of total electron content (TEC) at 1 Hz. This method not only involves less computation speed but is also simple to implement compared to the other methods and therefore can significantly improve the performance of the GPS receiver.
{"title":"GPS receiver phase jitter during ionospheric scintillation","authors":"Arslan Ahmed, R. Tiwari, M. Shah, Jiachen Yin","doi":"10.1109/ICMAE.2016.7549611","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549611","url":null,"abstract":"The amplitude and/or phase fluctuations in the received signal can severely affect the performance of the Global Positioning System (GPS). These amplitude and phase fluctuations arises when the GPS signal passes through the time-varying electron density irregularities in the ionosphere which can result in loss of lock due to cycle slip in the receiver tracking loop. During cycle slip, the phase jitter serves as an important parameter for updating the receiver tracking loop parameters for efficient tracking either by using a software-based GPS receiver or by hardware modifications. In this paper, a new method of estimating the tracking loop phase jitter is proposed which uses dual frequency based time and spatial variations of total electron content (TEC) at 1 Hz. This method not only involves less computation speed but is also simple to implement compared to the other methods and therefore can significantly improve the performance of the GPS receiver.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"14 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":"128177921","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.2016.7549503
Ling Xin, Jie Yang, Lianmei Wu, Geng Han, Zhidong Guan
Composite elastic constants prediction is an essential issue in composite mechanics. In this paper, a variety of experiments are used to measure the macro elastic constants of composite. Then the macro stiffness predictions of unidirectional composite based on finite element analysis (FEM) are conducted. Through this five independent macro elastic constants of composite (EL - longitudinal modulus, ET - transverse modulus, GLT - in-plane shear modulus, vTT - main Poisson's ratio, VTT - transverse Poisson's ratio) could be obtained. First square and hexagon RVEs considering the effect of interface cohesive zone were established to gain five macro elastic constants. Fiber is transversely isotropic material, and matrix is isotropic material. Finally a RVE of fiber random distribution containing 25 fibers were modeled and all the relative errors are less than 15%. Through finite element analysis, numerical models can effectively verify the experimental results. In future, the amount of tests can be reduced by means of numerical analysis.
{"title":"Finite element analysis of unidirectional composite elastic constants predictions considering interface","authors":"Ling Xin, Jie Yang, Lianmei Wu, Geng Han, Zhidong Guan","doi":"10.1109/ICMAE.2016.7549503","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549503","url":null,"abstract":"Composite elastic constants prediction is an essential issue in composite mechanics. In this paper, a variety of experiments are used to measure the macro elastic constants of composite. Then the macro stiffness predictions of unidirectional composite based on finite element analysis (FEM) are conducted. Through this five independent macro elastic constants of composite (EL - longitudinal modulus, ET - transverse modulus, GLT - in-plane shear modulus, vTT - main Poisson's ratio, VTT - transverse Poisson's ratio) could be obtained. First square and hexagon RVEs considering the effect of interface cohesive zone were established to gain five macro elastic constants. Fiber is transversely isotropic material, and matrix is isotropic material. Finally a RVE of fiber random distribution containing 25 fibers were modeled and all the relative errors are less than 15%. Through finite element analysis, numerical models can effectively verify the experimental results. In future, the amount of tests can be reduced by means of numerical analysis.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"36 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":"129262283","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.2016.7549571
Prabhjot Kaur Dhawan, Seongkyu Lee
This paper presents the validation and numerical parameter study of a semi-empirical trailing edge noise model. Turbulent boundary layer trailing edge noise is the main contributor of wind turbine noise and aircraft airframe noise. To predict this self-noise generated due to the interaction between a turbulent boundary layer flow and an airfoil trailing edge, a semi-empirical model was developed in NASA. The model has been widely used in academia and industry to predict the trailing edge noise. The capabilities and limitations of this semi-empirical model is further studied in this paper by comparing the predictions of the model with experimental data that were presented in a recent Benchmark Problems for Airframe Noise Computations (BANC) workshop. In order to better understand the behavior of trailing edge noise with operating conditions, numerical parameter study is investigated by varying variables such as chord length, Reynolds number, and Mach number.
{"title":"Validation and numerical parameter study of a semi-empirical trailing edge noise model","authors":"Prabhjot Kaur Dhawan, Seongkyu Lee","doi":"10.1109/ICMAE.2016.7549571","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549571","url":null,"abstract":"This paper presents the validation and numerical parameter study of a semi-empirical trailing edge noise model. Turbulent boundary layer trailing edge noise is the main contributor of wind turbine noise and aircraft airframe noise. To predict this self-noise generated due to the interaction between a turbulent boundary layer flow and an airfoil trailing edge, a semi-empirical model was developed in NASA. The model has been widely used in academia and industry to predict the trailing edge noise. The capabilities and limitations of this semi-empirical model is further studied in this paper by comparing the predictions of the model with experimental data that were presented in a recent Benchmark Problems for Airframe Noise Computations (BANC) workshop. In order to better understand the behavior of trailing edge noise with operating conditions, numerical parameter study is investigated by varying variables such as chord length, Reynolds number, and Mach number.","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":"128443021","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.2016.7549593
Chengxi Li, Gang Liu, Guanxin Hong
Carrier landing is the accident prone phase during carrier-based aircraft task. The prediction of carrier landing position is able to provide pilots with decision basis while various guidance modes represented by automatic carrier landing system (ACLS) are available. Air wake and deck heaving motion are both crucial factors leading to carrier landing error. Hence, taking F-18/A with ACLS as the research plane, a method to predict the carrier landing position based on BPNN with 3 discussed schemes, including landing error output, landing range output and dual parallel neural networks, was proposed in this paper. It was discovered through simulation in MATLAB that the proposed method was able to predict landing position with the mean error about 0.5m and the standard deviation about 2.60m. The prediction scheme with dual parallel neural networks performed better in such controlled circumstance.
{"title":"A method of F-18/A carrier landing position prediction based on back propagation neural network","authors":"Chengxi Li, Gang Liu, Guanxin Hong","doi":"10.1109/ICMAE.2016.7549593","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549593","url":null,"abstract":"Carrier landing is the accident prone phase during carrier-based aircraft task. The prediction of carrier landing position is able to provide pilots with decision basis while various guidance modes represented by automatic carrier landing system (ACLS) are available. Air wake and deck heaving motion are both crucial factors leading to carrier landing error. Hence, taking F-18/A with ACLS as the research plane, a method to predict the carrier landing position based on BPNN with 3 discussed schemes, including landing error output, landing range output and dual parallel neural networks, was proposed in this paper. It was discovered through simulation in MATLAB that the proposed method was able to predict landing position with the mean error about 0.5m and the standard deviation about 2.60m. The prediction scheme with dual parallel neural networks performed better in such controlled circumstance.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"114 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":"128117144","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.2016.7549566
Yuki Kawai, K. Uchiyama
We propose the method for a system considering the dynamic characteristics of an actuator through use of new design concept of integral sliding mode with saturation function. Sliding mode controller has been used because of robustness against parametric uncertainty and high-frequency unmodeled dynamics if and only if a system accomplishes infinitely fast switching. On the other hand, integral sliding mode controller has the robustness throughout an entire response of the system. However, stationary disturbance causes a chattering phenomenon when using those control methods. Therefore, we design a controller using modified integral sliding mode control method to have robustness against a stationary disturbance without chattering. Numerical simulations are performed for a rotary type UAV with an arm to verify the validity of the proposed control method.
{"title":"Modified integral sliding mode controller with saturation function","authors":"Yuki Kawai, K. Uchiyama","doi":"10.1109/ICMAE.2016.7549566","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549566","url":null,"abstract":"We propose the method for a system considering the dynamic characteristics of an actuator through use of new design concept of integral sliding mode with saturation function. Sliding mode controller has been used because of robustness against parametric uncertainty and high-frequency unmodeled dynamics if and only if a system accomplishes infinitely fast switching. On the other hand, integral sliding mode controller has the robustness throughout an entire response of the system. However, stationary disturbance causes a chattering phenomenon when using those control methods. Therefore, we design a controller using modified integral sliding mode control method to have robustness against a stationary disturbance without chattering. Numerical simulations are performed for a rotary type UAV with an arm to verify the validity of the proposed control method.","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":"127625751","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.2016.7549564
Javier Pérez, J. Pomares, M. Reza Emami
Robot manipulators have multiple uses and are especially useful when dealing with complex manipulation tasks in unstructured environments. This paper presents a direct image-based controller for performing the guidance of a free-floating robot manipulator. A camera is attached to the end-effector of the manipulator and the robot is attached to a base satellite. The proposed direct image-based control strategy computes the torque to be applied to the joints, and takes into account the system's kinematics and dynamics model. The operation is such that the base is completely free and floating in space with no attitude control, and thus freely reacting to the movements of the robot manipulator attached to it. The main objective is to track a desired trajectory in the image space with respect to an observed object in space. The proposed control strategy optimizes the motor commands with respect to a specified metric. The controller is applied to direct visual control of a four-degree-of-freedom robot manipulator.
{"title":"Image-based control of satellite-mounted robot manipulators","authors":"Javier Pérez, J. Pomares, M. Reza Emami","doi":"10.1109/ICMAE.2016.7549564","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549564","url":null,"abstract":"Robot manipulators have multiple uses and are especially useful when dealing with complex manipulation tasks in unstructured environments. This paper presents a direct image-based controller for performing the guidance of a free-floating robot manipulator. A camera is attached to the end-effector of the manipulator and the robot is attached to a base satellite. The proposed direct image-based control strategy computes the torque to be applied to the joints, and takes into account the system's kinematics and dynamics model. The operation is such that the base is completely free and floating in space with no attitude control, and thus freely reacting to the movements of the robot manipulator attached to it. The main objective is to track a desired trajectory in the image space with respect to an observed object in space. The proposed control strategy optimizes the motor commands with respect to a specified metric. The controller is applied to direct visual control of a four-degree-of-freedom robot manipulator.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"67 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":"133140453","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.2016.7549523
Hyung-Seop Han, H. Seok, Yu-Chan Kim
The purpose of this study was to investigate the fatigue life of an endosseous root-form dental implant using finite element analysis. A conventional Brånemark dental implant system was redesigned to utilize the biocompatible, lightweight magnesium alloy which promotes bone growth. ANSYS Workbench 11.0 was used to generate a three-dimensional mesh of a model created with the actual size specifications. Regulations and schematic of test set-up from ISO 14801 - “Fatigue test for endosseous dental implants” were strictly followed to simulate the fatigue test. To validate the credibility of calculated fatigue life, actual prototypes were built with the design specifications and tested using Material Test System 810. Result of finite element analysis displayed a close approximation of experimental fatigue behavior both displaying that the proposed implant would achieve a fatigue limit of 5 × 106 cycle suggested by the ISO at 150 N. The main advantage of performed computer simulations is that it is fast, efficient and cheap. A comparison of the calculated fatigue life with experimental fatigue life data displayed the accuracy and reliability of the computer simulation method.
{"title":"Finite element analysis of newly developed endosseous root-form dental implant utilizing biodegradable magnesium alloy","authors":"Hyung-Seop Han, H. Seok, Yu-Chan Kim","doi":"10.1109/ICMAE.2016.7549523","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549523","url":null,"abstract":"The purpose of this study was to investigate the fatigue life of an endosseous root-form dental implant using finite element analysis. A conventional Brånemark dental implant system was redesigned to utilize the biocompatible, lightweight magnesium alloy which promotes bone growth. ANSYS Workbench 11.0 was used to generate a three-dimensional mesh of a model created with the actual size specifications. Regulations and schematic of test set-up from ISO 14801 - “Fatigue test for endosseous dental implants” were strictly followed to simulate the fatigue test. To validate the credibility of calculated fatigue life, actual prototypes were built with the design specifications and tested using Material Test System 810. Result of finite element analysis displayed a close approximation of experimental fatigue behavior both displaying that the proposed implant would achieve a fatigue limit of 5 × 106 cycle suggested by the ISO at 150 N. The main advantage of performed computer simulations is that it is fast, efficient and cheap. A comparison of the calculated fatigue life with experimental fatigue life data displayed the accuracy and reliability of the computer simulation method.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"2 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":"128833769","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.2016.7549577
Ashok Kuppusamy, S. Yoon
This paper describes the qualification test guide (QTG) items made for a small, single engine, and commercial aircraft during the evaluation of simulator by any regulatory authority before the simulator can be used to train the student pilots. The test items described here are listed in Federal Aviation Regulations part 60. Out of those, the static control check tests are explained in detail since they need a control loading system to obtain its performance. The challenging task also is to compare the test results obtained by using the hardware control loader and the software made control loader by using commercial software called MATLAB/Simulink. Since this is a reversible control loading system, the artificial feel system for software control loader is created by making a second order transfer function called mass-spring-damper system. The feel system is created by keeping in consideration that there is only underdamping once the system is stabilized. The software control loader is designed by using a double integrator force feedback loop. The mathematical model presented in this paper showed good results in the actual experiments.
{"title":"Design of reversible control loading system for a fixed wing aircraft using X-Plane simulator","authors":"Ashok Kuppusamy, S. Yoon","doi":"10.1109/ICMAE.2016.7549577","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549577","url":null,"abstract":"This paper describes the qualification test guide (QTG) items made for a small, single engine, and commercial aircraft during the evaluation of simulator by any regulatory authority before the simulator can be used to train the student pilots. The test items described here are listed in Federal Aviation Regulations part 60. Out of those, the static control check tests are explained in detail since they need a control loading system to obtain its performance. The challenging task also is to compare the test results obtained by using the hardware control loader and the software made control loader by using commercial software called MATLAB/Simulink. Since this is a reversible control loading system, the artificial feel system for software control loader is created by making a second order transfer function called mass-spring-damper system. The feel system is created by keeping in consideration that there is only underdamping once the system is stabilized. The software control loader is designed by using a double integrator force feedback loop. The mathematical model presented in this paper showed good results in the actual experiments.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"57 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":"128763716","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.2016.7549499
Mi Zhang, Zhidong Guan, Wei Sun, Geng Han
Kink band is a typical phenomenon in longitudinal compression of composites. Numerical simulations considering fiber misalignment and plastic matrix with ductile damage have been built to study the formation of kink band. The matrix was simulated by using the extended Drucker-Prager constitutive model. Then random fiber strength distribution and stiffness reduction were considered to simulate the fiber break. The calculated critical stress and compressive modulus are consistent with experimental results. And the simulation results clearly reveal the longitudinal compressive damage process of the composites. It can be concluded that kink band formation and peak load rely on the matrix yielding. However, fiber properties including fiber misalignment, fiber volume fraction and fiber diameter do affect the kink band shape and compressive strength.
{"title":"Micro-mechanical simulation of longitudinal compression in composites considering stochastic fiber strength","authors":"Mi Zhang, Zhidong Guan, Wei Sun, Geng Han","doi":"10.1109/ICMAE.2016.7549499","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549499","url":null,"abstract":"Kink band is a typical phenomenon in longitudinal compression of composites. Numerical simulations considering fiber misalignment and plastic matrix with ductile damage have been built to study the formation of kink band. The matrix was simulated by using the extended Drucker-Prager constitutive model. Then random fiber strength distribution and stiffness reduction were considered to simulate the fiber break. The calculated critical stress and compressive modulus are consistent with experimental results. And the simulation results clearly reveal the longitudinal compressive damage process of the composites. It can be concluded that kink band formation and peak load rely on the matrix yielding. However, fiber properties including fiber misalignment, fiber volume fraction and fiber diameter do affect the kink band shape and compressive strength.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"17 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":"114624772","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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