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.2016.7549548
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}
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.2016.7549561
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}
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