Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549521
F. Guner, H. Sofuoğlu, Omer Necati Cora
Multi Particle Finite Element Method (MPFEM) which is a power full approach for particle systems analyzes particle interactions via different friction models. In this study, Amontons-Coulomb constant friction (ACM), Wanheim/Bay generalized friction (WBM) and Levanov's friction models (LFM) are utilized in MPFEM in order to obtain coefficient of friction at particle-particle and particle-die wall interactions in spherical copper powder compaction. Friction models are introduced into the analysis by user subroutines. Compaction processes at room temperature and at 270°C were investigated by terms of coefficient of friction, shear stress and equivalent strain. Although equivalent strain curve of WBM and LFM are in good agreement, ACM resulted in higher equivalent strain and shear stress values. Coefficient of friction those were obtained with WBM and LFM varies in a reasonable range.
{"title":"Numerical investigation of coefficient of friction in copper powder compaction process at micro scale","authors":"F. Guner, H. Sofuoğlu, Omer Necati Cora","doi":"10.1109/ICMAE.2016.7549521","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549521","url":null,"abstract":"Multi Particle Finite Element Method (MPFEM) which is a power full approach for particle systems analyzes particle interactions via different friction models. In this study, Amontons-Coulomb constant friction (ACM), Wanheim/Bay generalized friction (WBM) and Levanov's friction models (LFM) are utilized in MPFEM in order to obtain coefficient of friction at particle-particle and particle-die wall interactions in spherical copper powder compaction. Friction models are introduced into the analysis by user subroutines. Compaction processes at room temperature and at 270°C were investigated by terms of coefficient of friction, shear stress and equivalent strain. Although equivalent strain curve of WBM and LFM are in good agreement, ACM resulted in higher equivalent strain and shear stress values. Coefficient of friction those were obtained with WBM and LFM varies in a reasonable range.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"64 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":"130044649","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.2016.7549533
D. Aneesh, Ronith Stanly, S. Sagaram, S. Suneesh
Magnus rotor is essentially a rotating cylinder that generates lift due to Magnus effect. The effect has been generating curiosity in a wide variety of fields ranging from sports to alternate energy. The wind turbine under investigation replaces tradition blades that have an airfoil cross-section, with such Magnus rotors. In this paper, Magnus wind turbines with three and five rotors have been analyzed at various velocity ratios and tip speed ratios. The primary motive is to find the best operating conditions for obtaining a higher lift to drag coefficient for both three and five rotor turbines, so that it can generate more power with the least available wind. It has been observed that the higher ratio of coefficient of lift to coefficient of drag values were obtained for lower values of tip speed ratio, which is in contrast to the requirement of higher tip speed ratios for turbines with airfoil cross-section. This translates to the fact that Magnus wind turbines can be an efficient solution to the generation of wind power with less noise generation, since the noise generated by a wind turbine decreases with decrease in the tip speed ratio.
{"title":"Numerical analysis of Magnus wind turbine","authors":"D. Aneesh, Ronith Stanly, S. Sagaram, S. Suneesh","doi":"10.1109/ICMAE.2016.7549533","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549533","url":null,"abstract":"Magnus rotor is essentially a rotating cylinder that generates lift due to Magnus effect. The effect has been generating curiosity in a wide variety of fields ranging from sports to alternate energy. The wind turbine under investigation replaces tradition blades that have an airfoil cross-section, with such Magnus rotors. In this paper, Magnus wind turbines with three and five rotors have been analyzed at various velocity ratios and tip speed ratios. The primary motive is to find the best operating conditions for obtaining a higher lift to drag coefficient for both three and five rotor turbines, so that it can generate more power with the least available wind. It has been observed that the higher ratio of coefficient of lift to coefficient of drag values were obtained for lower values of tip speed ratio, which is in contrast to the requirement of higher tip speed ratios for turbines with airfoil cross-section. This translates to the fact that Magnus wind turbines can be an efficient solution to the generation of wind power with less noise generation, since the noise generated by a wind turbine decreases with decrease in the tip speed ratio.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"5 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":"131139204","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.2016.7549582
A. Arshad, Qiushi Li, Tianyu Pan
Rotating stall inception in low speed axial compressor is experimentally investigated by using temporal casing pressure signals from the circumferentially distributed pressure transducers. At first, fundamental technique of visual inspection is implemented by the application of series of low pass frequency filters. Only small filter ranges reveal rotating stall disturbance, each exhibiting different rotating speed of stall disturbance and stall cell. Results are highly dependent on filter size, which found to be a critical limitation. In the next step, results of filtered signals are compared by using a newly developed non-filtering AWT program. AWT offers a beneficial tool for providing rotating stall inception information without employing any pre-filtering limitation. One-step execution technique with features of FFT and wavelet transform, AWT successfully verified the results from the filtered signals obtained after the application of different filter ranges. Verification of filtered signal results with AWT can be a useful approach in stall inception study.
{"title":"Application of non filtering analytic wavelet transform for the investigation of rotating stall inception in low speed compressor","authors":"A. Arshad, Qiushi Li, Tianyu Pan","doi":"10.1109/ICMAE.2016.7549582","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549582","url":null,"abstract":"Rotating stall inception in low speed axial compressor is experimentally investigated by using temporal casing pressure signals from the circumferentially distributed pressure transducers. At first, fundamental technique of visual inspection is implemented by the application of series of low pass frequency filters. Only small filter ranges reveal rotating stall disturbance, each exhibiting different rotating speed of stall disturbance and stall cell. Results are highly dependent on filter size, which found to be a critical limitation. In the next step, results of filtered signals are compared by using a newly developed non-filtering AWT program. AWT offers a beneficial tool for providing rotating stall inception information without employing any pre-filtering limitation. One-step execution technique with features of FFT and wavelet transform, AWT successfully verified the results from the filtered signals obtained after the application of different filter ranges. Verification of filtered signal results with AWT can be a useful approach in stall inception study.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"16 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":"128728867","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.2016.7549561
Chakshu Baweja, P. Deb
The corrosion of grids in ion thrusters due to unsymmetrical leaks and beam dissipation which tends to decrease lifetime of thruster. Usage of cathode neutralizers have shown to decrease corrosion and effect the thrust vector of main electron beam. The existing neutralizer configurations reduce backfiring rate of flow to a minimal level, which has in turn limited the usage and lifetime of thrusters. Present work addresses the issue of this cathodic flow to effectively neutralize the beam by placing multiple cathodes radially and optimize design conditions to produce maximum propulsive efficiency and control the flow of cathodic ions which shouldn't cross main beam threshold. Changes in propulsive efficiency and thrust have been calculated which show an effective increase of 20%-25% and thrust increase of 36%, depending on number of probes, along with maintenance of effective mixing and neutralizing.
{"title":"Effect of multiple cathode neutralizers in standard ion thrust engines","authors":"Chakshu Baweja, P. Deb","doi":"10.1109/ICMAE.2016.7549561","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549561","url":null,"abstract":"The corrosion of grids in ion thrusters due to unsymmetrical leaks and beam dissipation which tends to decrease lifetime of thruster. Usage of cathode neutralizers have shown to decrease corrosion and effect the thrust vector of main electron beam. The existing neutralizer configurations reduce backfiring rate of flow to a minimal level, which has in turn limited the usage and lifetime of thrusters. Present work addresses the issue of this cathodic flow to effectively neutralize the beam by placing multiple cathodes radially and optimize design conditions to produce maximum propulsive efficiency and control the flow of cathodic ions which shouldn't cross main beam threshold. Changes in propulsive efficiency and thrust have been calculated which show an effective increase of 20%-25% and thrust increase of 36%, depending on number of probes, along with maintenance of effective mixing and neutralizing.","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":"125913715","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.2016.7549511
J. Jamali, M. Mohammadzaheri, P. Sharifi, M. Haghshenas, M. Mohammadi
In this paper, mixed mode fracture of neat polymer and composite materials was inspected. The neat polymer in the study is made of pure epoxy and the composite consists of long glass fibres embedded in epoxy. The composite in the study differ from layered unidirectional to random fibre composite. To perform the experiment Compact Tension Shear (CTS) testing fixture and three point bending specimens are employed. The experiment is utilized to study the crack behavior in these materials and measure the fracture toughness and calculate the corresponding Critical Strain Energy Release Rate (CSERR). Studying crack propagation through the thickness of the composite and polymer showed that energy released during fracture at different modes of loading is connected to the morphology of the fracture surface.
{"title":"Polymers and polymer composites mixed mode fracture testing","authors":"J. Jamali, M. Mohammadzaheri, P. Sharifi, M. Haghshenas, M. Mohammadi","doi":"10.1109/ICMAE.2016.7549511","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549511","url":null,"abstract":"In this paper, mixed mode fracture of neat polymer and composite materials was inspected. The neat polymer in the study is made of pure epoxy and the composite consists of long glass fibres embedded in epoxy. The composite in the study differ from layered unidirectional to random fibre composite. To perform the experiment Compact Tension Shear (CTS) testing fixture and three point bending specimens are employed. The experiment is utilized to study the crack behavior in these materials and measure the fracture toughness and calculate the corresponding Critical Strain Energy Release Rate (CSERR). Studying crack propagation through the thickness of the composite and polymer showed that energy released during fracture at different modes of loading is connected to the morphology of the fracture surface.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"15 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":"126107648","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.2016.7549601
Zhang Weiyao, Tu Xiaozhen, Dong Tianbao, W. Wenlong, Li Wei
In the rocket transportation the road roughness load can cause its solid motor charge to vibrate randomly. To get information about the motor charge's dynamic characteristic and damage degree, this paper calculated the charge's vibration responses by road excitations on the numerical method of mechanical modeling. First the rocket launcher's simplified model was built and the transfer function was obtained. Then By the road roughness excitation PSDs (Power spectral density) response PSDs of the rocket's supporting points on the launcher were calculated. Moreover the rocket FEM model was established and its random vibration responses were acquired by the launcher's supporting point excitations (namely response PSDs of the rocket's supporting points). At last by Miner liner cumulative damage law and the danger point's stress results the motor charge's fatigue damage amount was solved. Results show that in the rocket transport process road loads can lead to the motor charge's remarkable structural vibration as well as fatigue damage and with loading time increasing it comes into the structural failure in the end.
{"title":"Fatigue lifetime estimation of the solid rocket motor charge by road roughness loads on mechanical methods","authors":"Zhang Weiyao, Tu Xiaozhen, Dong Tianbao, W. Wenlong, Li Wei","doi":"10.1109/ICMAE.2016.7549601","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549601","url":null,"abstract":"In the rocket transportation the road roughness load can cause its solid motor charge to vibrate randomly. To get information about the motor charge's dynamic characteristic and damage degree, this paper calculated the charge's vibration responses by road excitations on the numerical method of mechanical modeling. First the rocket launcher's simplified model was built and the transfer function was obtained. Then By the road roughness excitation PSDs (Power spectral density) response PSDs of the rocket's supporting points on the launcher were calculated. Moreover the rocket FEM model was established and its random vibration responses were acquired by the launcher's supporting point excitations (namely response PSDs of the rocket's supporting points). At last by Miner liner cumulative damage law and the danger point's stress results the motor charge's fatigue damage amount was solved. Results show that in the rocket transport process road loads can lead to the motor charge's remarkable structural vibration as well as fatigue damage and with loading time increasing it comes into the structural failure in the end.","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":"127252332","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.2016.7549526
S. P. Lee, M. Jupp, A. K. Nickson
This paper presents a computational investigation into the effect of volute secondary flow structures on turbine inlet flow conditions. The steady state results show Dean type vortices exist early in the volute. As a result a substantial variation in absolute flow angle at the volute exit was observed. Pulsed flow simulations showed that the size and position of the secondary flow structures are time dependent. The resulting volute exit flow conditions were also found to be time dependent with the absolute flow angle at the volute exit varying with pulse pressure. This paper shows that that the secondary flow structures that exist in the volute as a result of cross sectional shape can have significant downstream effects on rotor performance.
{"title":"The influence of secondary flow structures in a turbocharger turbine housing in steady state and pulsating flow conditions","authors":"S. P. Lee, M. Jupp, A. K. Nickson","doi":"10.1109/ICMAE.2016.7549526","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549526","url":null,"abstract":"This paper presents a computational investigation into the effect of volute secondary flow structures on turbine inlet flow conditions. The steady state results show Dean type vortices exist early in the volute. As a result a substantial variation in absolute flow angle at the volute exit was observed. Pulsed flow simulations showed that the size and position of the secondary flow structures are time dependent. The resulting volute exit flow conditions were also found to be time dependent with the absolute flow angle at the volute exit varying with pulse pressure. This paper shows that that the secondary flow structures that exist in the volute as a result of cross sectional shape can have significant downstream effects on rotor performance.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"72 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":"127654706","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.2016.7549599
K. Ananthakrishnan, M. Govardhan
In this present work, efforts are made to understand the effect of constant and variable radii fillet on secondary flow losses in Nozzle Guide Vane of the transonic turbine stage. Constant and variable radii fillets near vane-endwall juncture are designed using shape parameters like leading edge radius and minimum angle. Results are discussed using topological features of the flow field, Mach and density contours. Separation lines associated with inlet boundary layer and passage vortex, saddle point and attachment nodes are resolved. Variable radii fillet outperforms the constant radii fillet by reducing the height of three dimensional flow regime affected by secondary flow. It removes the separation bubble near the trailing edge. Increment in leading edge radius increases the movement of these flows towards midspan while the effect of minimum angle is found to be insignificant.
{"title":"Effect of constant and variable radii fillet on secondary flow field of transonic turbine stage's Nozzle Guide Vane","authors":"K. Ananthakrishnan, M. Govardhan","doi":"10.1109/ICMAE.2016.7549599","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549599","url":null,"abstract":"In this present work, efforts are made to understand the effect of constant and variable radii fillet on secondary flow losses in Nozzle Guide Vane of the transonic turbine stage. Constant and variable radii fillets near vane-endwall juncture are designed using shape parameters like leading edge radius and minimum angle. Results are discussed using topological features of the flow field, Mach and density contours. Separation lines associated with inlet boundary layer and passage vortex, saddle point and attachment nodes are resolved. Variable radii fillet outperforms the constant radii fillet by reducing the height of three dimensional flow regime affected by secondary flow. It removes the separation bubble near the trailing edge. Increment in leading edge radius increases the movement of these flows towards midspan while the effect of minimum angle is found to be insignificant.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"13 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":"114414034","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.2016.7549616
Zhao-Xiang Zhang, Guo-dong Xu
Pushbroom cameras are widely used for earth observation application. This sensor capture 1D image over time and sweep out a region of space and build a 2D image using the straight motion of the satellite. The attitude variation is assumed to be constant during the acquisition process. However, this assumption has been weakened due to a tendency of miniature and lightweight of satellites. In this paper, we analyze the warps of remote sensing image and introduce an improved image registration method. Then the correct images are retrieved and the satellite variation is estimated. The performances of our algorithm are shown on JL-1 satellite datasets. The results shows the possibility of the improvement in geometric processing accuracy for JL-1 imagery products and provide a good reference for satellite platform jitter source analysis.
{"title":"Detection of JL-1 satellite's jitter using multimodal pushbroom cameras","authors":"Zhao-Xiang Zhang, Guo-dong Xu","doi":"10.1109/ICMAE.2016.7549616","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549616","url":null,"abstract":"Pushbroom cameras are widely used for earth observation application. This sensor capture 1D image over time and sweep out a region of space and build a 2D image using the straight motion of the satellite. The attitude variation is assumed to be constant during the acquisition process. However, this assumption has been weakened due to a tendency of miniature and lightweight of satellites. In this paper, we analyze the warps of remote sensing image and introduce an improved image registration method. Then the correct images are retrieved and the satellite variation is estimated. The performances of our algorithm are shown on JL-1 satellite datasets. The results shows the possibility of the improvement in geometric processing accuracy for JL-1 imagery products and provide a good reference for satellite platform jitter source analysis.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"22 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":"126192628","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.2016.7549578
M. Noviello, F. Rea, M. Arena, R. Pecora, F. Amoroso
Modern aerospace research programs are increasingly oriented towards adaptive wing structures for greening the air transport in the near future. New structural concepts implementing and integrating innovative technologies are mandatory for succeeding in this critical task. Among these, the so-called morphing structures are taken into account in aerospace applications, since they ensure the structural shape control in order to optimize the aerodynamic efficiency during the different flight phases. Among the most ambitious research projects launched in Europe, the JTI - Green Regional Aircraft (GRA) is placed in foreground for the design and the demonstration of a true-scale morphing flap applicable to the Natural Laminar Flow (NLF) wing of a 130-seats reference aircraft belonging to EASA CS25 category. In this framework, the authors intensively worked on the definition of a specific actuation and control system layout properly enabling two flap operational modes: overall camber morphing in deployed configuration, during take-off and landing, to enhance high lift performances; upwards and downwards deflection of the flap trailing edge (nearly the 10% of the local chord) in stowed configuration, to improve wing aerodynamic efficiency in cruise. For this purpose, a digital logic control law was opportunely implemented into controller devices by using LTI DriveManager® software. Obtained results have been presented in terms of controlled morphed shapes, showing an excellent correlation with respect to the target geometries imposed by design requirements.
{"title":"Actuation and control of a novel wing flap architecture with bi-modal camber morphing capabilities","authors":"M. Noviello, F. Rea, M. Arena, R. Pecora, F. Amoroso","doi":"10.1109/ICMAE.2016.7549578","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549578","url":null,"abstract":"Modern aerospace research programs are increasingly oriented towards adaptive wing structures for greening the air transport in the near future. New structural concepts implementing and integrating innovative technologies are mandatory for succeeding in this critical task. Among these, the so-called morphing structures are taken into account in aerospace applications, since they ensure the structural shape control in order to optimize the aerodynamic efficiency during the different flight phases. Among the most ambitious research projects launched in Europe, the JTI - Green Regional Aircraft (GRA) is placed in foreground for the design and the demonstration of a true-scale morphing flap applicable to the Natural Laminar Flow (NLF) wing of a 130-seats reference aircraft belonging to EASA CS25 category. In this framework, the authors intensively worked on the definition of a specific actuation and control system layout properly enabling two flap operational modes: overall camber morphing in deployed configuration, during take-off and landing, to enhance high lift performances; upwards and downwards deflection of the flap trailing edge (nearly the 10% of the local chord) in stowed configuration, to improve wing aerodynamic efficiency in cruise. For this purpose, a digital logic control law was opportunely implemented into controller devices by using LTI DriveManager® software. Obtained results have been presented in terms of controlled morphed shapes, showing an excellent correlation with respect to the target geometries imposed by design requirements.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"77 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":"126228246","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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