Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549592
R. Saltoglu, Nazmia Humaira, G. Inalhan
Aircraft maintenance cost consists of two elements. The first one is direct maintenance cost and the other one is indirect maintenance cost. The first element includes the costs that are directly related to the maintenance activities such as labor, material, tool and equipment. The second element includes the cost that does not directly affect operator's maintenance budget, which is defined as downtime cost. In most cases, downtime cost is neglected claiming that downtime is a natural fact of maintenance. However, to our surprise, as maintenance period gets longer and the required tools and materials get more complex, downtime starts to cost operator in the same way the maintenance activities do. Therefore, the aim of this study is to examine the elements of maintenance downtime and to what extent they affect the total maintenance cost.
{"title":"Maintenance stop time influence on aircraft total maintenane cost with downtime integrated cost model","authors":"R. Saltoglu, Nazmia Humaira, G. Inalhan","doi":"10.1109/ICMAE.2016.7549592","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549592","url":null,"abstract":"Aircraft maintenance cost consists of two elements. The first one is direct maintenance cost and the other one is indirect maintenance cost. The first element includes the costs that are directly related to the maintenance activities such as labor, material, tool and equipment. The second element includes the cost that does not directly affect operator's maintenance budget, which is defined as downtime cost. In most cases, downtime cost is neglected claiming that downtime is a natural fact of maintenance. However, to our surprise, as maintenance period gets longer and the required tools and materials get more complex, downtime starts to cost operator in the same way the maintenance activities do. Therefore, the aim of this study is to examine the elements of maintenance downtime and to what extent they affect the total maintenance cost.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"83 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":"124759109","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.2016.7549500
Hengchang Nie, Jifeng Xu, Zhidong Guan, Qian Wang, Zengshan Li
The damage introduced by low-velocity impact is a threat to adhesively bonded composite joints. The impact response and tensile behaviors after impact of composite scarf joints was investigated using experimental and finite element analysis techniques. 18 specimens were impacted in three different locations and tensile tests after impact were conducted. The test results demonstrated that when impacted on the back face of scarf tip, the average dent depth was largest and the average tensile strength after impact was lowest. When impacted in the middle of the bondline slope, the dent depth was smallest and the tensile strength after impact was highest. When impacted on the front face of scarf tip, the dent depth and the tensile strength after impact was mediate. Stress concentration was observed in the scarf tips and areas beside the impact location because of the influence of bending stress and bypass load. The finite element analysis results showed that the extensive expand of fiber damage and adhesive damage lead to catastrophic failure of the whole structure.
{"title":"Tensile behaviors after impact of composite scarf joints","authors":"Hengchang Nie, Jifeng Xu, Zhidong Guan, Qian Wang, Zengshan Li","doi":"10.1109/ICMAE.2016.7549500","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549500","url":null,"abstract":"The damage introduced by low-velocity impact is a threat to adhesively bonded composite joints. The impact response and tensile behaviors after impact of composite scarf joints was investigated using experimental and finite element analysis techniques. 18 specimens were impacted in three different locations and tensile tests after impact were conducted. The test results demonstrated that when impacted on the back face of scarf tip, the average dent depth was largest and the average tensile strength after impact was lowest. When impacted in the middle of the bondline slope, the dent depth was smallest and the tensile strength after impact was highest. When impacted on the front face of scarf tip, the dent depth and the tensile strength after impact was mediate. Stress concentration was observed in the scarf tips and areas beside the impact location because of the influence of bending stress and bypass load. The finite element analysis results showed that the extensive expand of fiber damage and adhesive damage lead to catastrophic failure of the whole structure.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"82 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":"122090766","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.2016.7549543
Nuo Bao, Jianming Ma, Xingqi Zhang, Zhenghu Zhong
A lightweight bionic design method is proposed to reinforce the structure. The characteristics of leaf vein and honeycomb are investigated to optimize the shape and distribution of the stiffened plate. The structural bionic design for the stiffened plate of base structure is carried out based on biological structure characteristics. Then, a comparison of static performance between initial and bionic structures is conducted to verify the proposed approach by employing finite element analysis. The results show that the mass of the bionic types is reduced by 12.46% and 8.02%, the maximum deformation is reduced by 5.45% and 3.58%, respectively. And thus the validity and applicability of this method is verified.
{"title":"Structural bionic lightweight design for the stiffened plate of base structure","authors":"Nuo Bao, Jianming Ma, Xingqi Zhang, Zhenghu Zhong","doi":"10.1109/ICMAE.2016.7549543","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549543","url":null,"abstract":"A lightweight bionic design method is proposed to reinforce the structure. The characteristics of leaf vein and honeycomb are investigated to optimize the shape and distribution of the stiffened plate. The structural bionic design for the stiffened plate of base structure is carried out based on biological structure characteristics. Then, a comparison of static performance between initial and bionic structures is conducted to verify the proposed approach by employing finite element analysis. The results show that the mass of the bionic types is reduced by 12.46% and 8.02%, the maximum deformation is reduced by 5.45% and 3.58%, respectively. And thus the validity and applicability of this method is verified.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"49 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":"125458775","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.2016.7549550
Oyendrila Singha, N. Venkatesan, A. Samad, E. Avital
Marine tidal energy extraction faces multi-fold challenges during design, installation, operation and grid-connection. The control of turbine speed with tidal variation is vital to get a steady power output from the turbines during the operation phase throughout the year. This paper deals with the development and implementation of a control strategy for a horizontal axis turbine using the Blade Element Momentum (BEM) approach as the hydrodynamic model and generator (DFIG) control. A control efficiency of 71% is achieved between the system's overall and the hydrodynamic power of a small scale turbine. It is also shown that the generator speed can be well maintained to operate in a super-synchronous mode.
{"title":"Modeling and controller implementation of tidal turbine for Indian remote islands","authors":"Oyendrila Singha, N. Venkatesan, A. Samad, E. Avital","doi":"10.1109/ICMAE.2016.7549550","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549550","url":null,"abstract":"Marine tidal energy extraction faces multi-fold challenges during design, installation, operation and grid-connection. The control of turbine speed with tidal variation is vital to get a steady power output from the turbines during the operation phase throughout the year. This paper deals with the development and implementation of a control strategy for a horizontal axis turbine using the Blade Element Momentum (BEM) approach as the hydrodynamic model and generator (DFIG) control. A control efficiency of 71% is achieved between the system's overall and the hydrodynamic power of a small scale turbine. It is also shown that the generator speed can be well maintained to operate in a super-synchronous mode.","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":"116522157","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.2016.7549534
Ann Smith, F. Gu, A. Ball
With the exponential growth in data collection and storage and the necessity for timely prognostic health monitoring of industrial processes traditional methods of data analysis are becoming redundant. Big data sets and huge volumes of inputs give rise to equally massive computational requirements. In this paper the differences in input parameter selection using a subset of the original variables and using data reduction techniques are compared. Each selection procedure being illustrated by both statistical methods and machine learning techniques. It is shown that the subsequent classification models are highly comparable. Finally the merits of a combined multivariate statistical and wavelet decomposition approach is considered. Techniques are applied to output signals from an experimental compressor rig.
{"title":"Maintaining model efficiency, avoiding bias and reducing input parameter volume in compressor fault classification","authors":"Ann Smith, F. Gu, A. Ball","doi":"10.1109/ICMAE.2016.7549534","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549534","url":null,"abstract":"With the exponential growth in data collection and storage and the necessity for timely prognostic health monitoring of industrial processes traditional methods of data analysis are becoming redundant. Big data sets and huge volumes of inputs give rise to equally massive computational requirements. In this paper the differences in input parameter selection using a subset of the original variables and using data reduction techniques are compared. Each selection procedure being illustrated by both statistical methods and machine learning techniques. It is shown that the subsequent classification models are highly comparable. Finally the merits of a combined multivariate statistical and wavelet decomposition approach is considered. Techniques are applied to output signals from an experimental compressor rig.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"342 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":"132667324","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.2016.7549587
T. Truong, Marcro Debiasi, U. Kureemun, H. Lee
The development of flapping wing micro air vehicles (MAVs) have yielded remarkable progress over the last decades. Achieving high component stiffness is often in conflict with low weight requirement, which is highly desirable for longer flight time and higher payload. Moreover, the vibration originated predominantly from the wings, the gears and the frame excitations, compromises the flapping wing MAV's stability and the fatigue life. In order to improve the vehicle's efficiency and performance, optimization of these various parameters is necessary. In this work, we present the structural optimization of the flapping wing micro air vehicles. Specifically, we focus on the gearbox optimization using Simulia Tosca Structure in Abaqus, which is a robust tool for designing lightweight, rigid and durable components. The various numerical experiments have been conducted towards optimizing the components' topology. The results provide understanding of the optimal design topology for a spur gear and the structural components used in MAVs.
{"title":"Structural optimization of a flapping wing micro air vehicle","authors":"T. Truong, Marcro Debiasi, U. Kureemun, H. Lee","doi":"10.1109/ICMAE.2016.7549587","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549587","url":null,"abstract":"The development of flapping wing micro air vehicles (MAVs) have yielded remarkable progress over the last decades. Achieving high component stiffness is often in conflict with low weight requirement, which is highly desirable for longer flight time and higher payload. Moreover, the vibration originated predominantly from the wings, the gears and the frame excitations, compromises the flapping wing MAV's stability and the fatigue life. In order to improve the vehicle's efficiency and performance, optimization of these various parameters is necessary. In this work, we present the structural optimization of the flapping wing micro air vehicles. Specifically, we focus on the gearbox optimization using Simulia Tosca Structure in Abaqus, which is a robust tool for designing lightweight, rigid and durable components. The various numerical experiments have been conducted towards optimizing the components' topology. The results provide understanding of the optimal design topology for a spur gear and the structural components used in MAVs.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"62 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":"114773547","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.2016.7549528
S. P. Lee, M. Jupp, A. K. Nickson
This paper introduces a tilted volute design for operation with a mixed flow turbine rotor. CFD results show an efficiency gain of up to 1.2% over the standard radial design at the highest tested turbine rotational speed. The efficiency gain was found to be the result of a reduction in separation from the blade suction surface. A reduction in the flow cone angle was also observed for the tilted housing, as a result an increase in negative incidence angles at the blade LE was observed. This work shows that optimization of the turbine housing specifically for mixed flow applications can yield significant performance benefits.
{"title":"The introduction of a tilted volute design for operation with a mixed flow turbine for turbocharger applications","authors":"S. P. Lee, M. Jupp, A. K. Nickson","doi":"10.1109/ICMAE.2016.7549528","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549528","url":null,"abstract":"This paper introduces a tilted volute design for operation with a mixed flow turbine rotor. CFD results show an efficiency gain of up to 1.2% over the standard radial design at the highest tested turbine rotational speed. The efficiency gain was found to be the result of a reduction in separation from the blade suction surface. A reduction in the flow cone angle was also observed for the tilted housing, as a result an increase in negative incidence angles at the blade LE was observed. This work shows that optimization of the turbine housing specifically for mixed flow applications can yield significant performance benefits.","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":"133537758","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.2016.7549597
R. Du, Chao Yan, Huafeng Yu, Zheng Han
Partially-averaged Navier-Stokes (PANS) method, as a bridging method between Reynolds-averaged Navier-Stokes (RANS) and direct numerical simulation (DNS), has attracted many researchers' attentions in recent years. In this paper, PANS is extended to the simulations of a jet injected into a supersonic crossflow. A dynamic function of the resolution control parameter fk (unresolved-to-total ratio of kinetic energy) is adopted. Numerical results are compared to the experimental data and the performance of PANS is evaluated. The predictions of dynamic fk PANS overall agree well with the measurements and the instantaneous flow filed is provided. In addition, the distribution of fk is presented to have a better understanding of the method's scale resolving behavior throughout the computation domain. Current study has shown the capabilities and potential of PANS method for supersonic industrial flows.
{"title":"Partially-averaged navier-stokes method for turbulence simulations: A jet injected into a supersonic crossflow","authors":"R. Du, Chao Yan, Huafeng Yu, Zheng Han","doi":"10.1109/ICMAE.2016.7549597","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549597","url":null,"abstract":"Partially-averaged Navier-Stokes (PANS) method, as a bridging method between Reynolds-averaged Navier-Stokes (RANS) and direct numerical simulation (DNS), has attracted many researchers' attentions in recent years. In this paper, PANS is extended to the simulations of a jet injected into a supersonic crossflow. A dynamic function of the resolution control parameter fk (unresolved-to-total ratio of kinetic energy) is adopted. Numerical results are compared to the experimental data and the performance of PANS is evaluated. The predictions of dynamic fk PANS overall agree well with the measurements and the instantaneous flow filed is provided. In addition, the distribution of fk is presented to have a better understanding of the method's scale resolving behavior throughout the computation domain. Current study has shown the capabilities and potential of PANS method for supersonic industrial flows.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"29 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":"122106904","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.2016.7549580
M. Arena, M. Noviello, F. Rea, F. Amoroso, R. Pecora, G. Amendola
The meaningful growth process and the exponential development related to aircraft industry has currently introduced new requirements concerning the fuel burn reduction and the noise emitted. The awareness on meeting the comfort targets implied a significant evolution of the assessments in aircraft design, aimed at reducing the problems that have emerged in empirical investigations. The aircraft renewal process involves targeted technical choices both to careful observance of safety as to the market requirements. In the current “low-noise” research scenario on a global scale, the morphing technology is playing a dominant role for the many benefits available in the greening of the next generation air transport. The research project CRIAQ-MDO505, born by an intense synergy among industries, research centers and universities has allowed for investigating morphing structures potentials through the design and manufacturing of a variable camber aileron tailored for CS-25 category aircraft applications. In this framework, the authors focused on the setup of an advanced finite element model (FEM) and on its validation through ground resonance tests performed on a true-scale prototype. A very good correlation between numerical and experimental modal parameters was proven thus showing the adequacy of the adopted modelling strategies as well as the reliability of the FEM. Relying upon the validated FEM, sensitivity modal analyses were carried out to evaluate the stability of results with respect to single and combined failures of the actuation line enabling morphing. Modal parameters pertinent to each failure scenario were arranged into a rational database for further studies on the aero-servo-elastic behavior of the morphing system.
{"title":"Modal stability assessment for a morphing aileron subjected to actuation system failures: Numerical analysis supported by test evidence","authors":"M. Arena, M. Noviello, F. Rea, F. Amoroso, R. Pecora, G. Amendola","doi":"10.1109/ICMAE.2016.7549580","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549580","url":null,"abstract":"The meaningful growth process and the exponential development related to aircraft industry has currently introduced new requirements concerning the fuel burn reduction and the noise emitted. The awareness on meeting the comfort targets implied a significant evolution of the assessments in aircraft design, aimed at reducing the problems that have emerged in empirical investigations. The aircraft renewal process involves targeted technical choices both to careful observance of safety as to the market requirements. In the current “low-noise” research scenario on a global scale, the morphing technology is playing a dominant role for the many benefits available in the greening of the next generation air transport. The research project CRIAQ-MDO505, born by an intense synergy among industries, research centers and universities has allowed for investigating morphing structures potentials through the design and manufacturing of a variable camber aileron tailored for CS-25 category aircraft applications. In this framework, the authors focused on the setup of an advanced finite element model (FEM) and on its validation through ground resonance tests performed on a true-scale prototype. A very good correlation between numerical and experimental modal parameters was proven thus showing the adequacy of the adopted modelling strategies as well as the reliability of the FEM. Relying upon the validated FEM, sensitivity modal analyses were carried out to evaluate the stability of results with respect to single and combined failures of the actuation line enabling morphing. Modal parameters pertinent to each failure scenario were arranged into a rational database for further studies on the aero-servo-elastic behavior of the morphing system.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"92 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":"126062535","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.2016.7549556
Y. Yokoi
In order to understand the flow feature around an in-line forced oscillating circular cylinder with splitter plate (splitter plate ratio SL/d = 2.0), numerical and visual experiments were performed. As a result, even if it was the case of circular cylinder with splitter plate, the lock-in phenomenon arises. The characteristics of fluid force and typical flow patterns were obtained. It was found that an existence of re-circulation flow supplied to the separating shear layer is important in formation of the vortex shedding flow.
{"title":"Flow feature around an in-line forced oscillating circular cylinder with splitter plate in low reynolds number","authors":"Y. Yokoi","doi":"10.1109/ICMAE.2016.7549556","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549556","url":null,"abstract":"In order to understand the flow feature around an in-line forced oscillating circular cylinder with splitter plate (splitter plate ratio SL/d = 2.0), numerical and visual experiments were performed. As a result, even if it was the case of circular cylinder with splitter plate, the lock-in phenomenon arises. The characteristics of fluid force and typical flow patterns were obtained. It was found that an existence of re-circulation flow supplied to the separating shear layer is important in formation of the vortex shedding flow.","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":"129996849","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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