Pub Date : 2021-09-01DOI: 10.6125/JOAAA.202109_53(3).04
Efstratios Ntantis, Earl Francis, Vetrichelvan Pugazendi, Joseph George, A. Tarek, Mohammed Emthias, Syed Rasheed
{"title":"Study of Sinusoidal Perturbations on the Leading Edge of an Aircraft Wing","authors":"Efstratios Ntantis, Earl Francis, Vetrichelvan Pugazendi, Joseph George, A. Tarek, Mohammed Emthias, Syed Rasheed","doi":"10.6125/JOAAA.202109_53(3).04","DOIUrl":"https://doi.org/10.6125/JOAAA.202109_53(3).04","url":null,"abstract":"","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"58 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127082019","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 : 2021-09-01DOI: 10.6125/JOAAA.202109_53(3).03
K. M. Chung, Ying-Chi Huang, C. Y. Lin, Y. T. Wu
Pressure sensitive paint (PSP) gives the full-field pressure pattern on the model surface with a high spatial resolution and is an alternative to traditional pressure taps used in a wind tunnel model. This study determines surface pressure patterns on the forebody of an AGARD B model in a compressible flow and the data is in comparison with a numerical simulation using ANSYS Fluent software. The lift and drag coefficients are calculated and compared with data in literature. The experiments use a blowdown wind tunnel. The freestream Mach number is 0.83 and the angle of attack ranges from -4° to 8°. The difference between the results using PSP and the numerical simulation is less than 5%.
{"title":"Surface Pressure Measurements on a Forebody Using Pressure Sensitive Paint","authors":"K. M. Chung, Ying-Chi Huang, C. Y. Lin, Y. T. Wu","doi":"10.6125/JOAAA.202109_53(3).03","DOIUrl":"https://doi.org/10.6125/JOAAA.202109_53(3).03","url":null,"abstract":"Pressure sensitive paint (PSP) gives the full-field pressure pattern on the model surface with a high spatial resolution and is an alternative to traditional pressure taps used in a wind tunnel model. This study determines surface pressure patterns on the forebody of an AGARD B model in a compressible flow and the data is in comparison with a numerical simulation using ANSYS Fluent software. The lift and drag coefficients are calculated and compared with data in literature. The experiments use a blowdown wind tunnel. The freestream Mach number is 0.83 and the angle of attack ranges from -4° to 8°. The difference between the results using PSP and the numerical simulation is less than 5%.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"54 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124830678","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 : 2021-09-01DOI: 10.6125/JOAAA.202109_53(3).02
Yueh‐Heng Li, Killian Dorn, Hsun-Chen Hsieh, T. Kuo, Y. Hsu
This study focused on the development of a pulsed plasma thruster (PPT) using various electrode angles, including asymmetric ones. Four electrode angles and asymmetric configuration setups were selected and examined, and we revealed their influence on the performance and reliability of the PPT. The original design, manufacture, and demonstration of the PPT were completed. An interesting phenomenon was observed and elucidated using a high-speed camera, and hypothetical solutions were addressed. In addition, a Taguchi method was employed to analyze the effects of design parameters on PPT performance and reliability. The results demonstrated that the electrodes with a deflection angle of 40° would deteriorate the reliability of PPT discharging, and the corresponding failure rate would reach 50% and more.
{"title":"Effect of Electrode Angle on Pulsed Plasma Thruster Performance","authors":"Yueh‐Heng Li, Killian Dorn, Hsun-Chen Hsieh, T. Kuo, Y. Hsu","doi":"10.6125/JOAAA.202109_53(3).02","DOIUrl":"https://doi.org/10.6125/JOAAA.202109_53(3).02","url":null,"abstract":"This study focused on the development of a pulsed plasma thruster (PPT) using various electrode angles, including asymmetric ones. Four electrode angles and asymmetric configuration setups were selected and examined, and we revealed their influence on the performance and reliability of the PPT. The original design, manufacture, and demonstration of the PPT were completed. An interesting phenomenon was observed and elucidated using a high-speed camera, and hypothetical solutions were addressed. In addition, a Taguchi method was employed to analyze the effects of design parameters on PPT performance and reliability. The results demonstrated that the electrodes with a deflection angle of 40° would deteriorate the reliability of PPT discharging, and the corresponding failure rate would reach 50% and more.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"336 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133314203","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 : 2021-06-01DOI: 10.6125/JOAAA.202106_53(2).03
I. Mohammed, A. Talib
The study was based on the behavior of the fabricated composite that comprise of aluminium and a thin layer of epoxy/aerogel and coated with epoxy/different types of silica aerogel subjected to flame fire using a standard ISO2685 propane-air burner. The aim of this study is to fabricate a new, user friendly composite and to evaluate the behaviour of the composites in a pool fire by determining the penetration time of silica aerogels used. The composites were developed to resist a fire penetration based on the standard of temperature and heat flux for at least 15 minutes for fireproof and 5 minutes for fire resistance. The developed samples are one weight percent of aerogel in the mixture of resin/hardener and were mixed using mechanical mixer and sonicator. The results indicate that composite of GEA^(TM) 0.125 silica aerogel resists higher flame than the other types of aerogel composites examined, where it was 5.56% and 10.39% more fire resistance than Enova® IC3100 and Hamzel® respectively. The study reveals that the developed composites possess the required properties to be used.
{"title":"Experimental Investigation of Metal- Laminates with Aerogel in High-Temperature Application","authors":"I. Mohammed, A. Talib","doi":"10.6125/JOAAA.202106_53(2).03","DOIUrl":"https://doi.org/10.6125/JOAAA.202106_53(2).03","url":null,"abstract":"The study was based on the behavior of the fabricated composite that comprise of aluminium and a thin layer of epoxy/aerogel and coated with epoxy/different types of silica aerogel subjected to flame fire using a standard ISO2685 propane-air burner. The aim of this study is to fabricate a new, user friendly composite and to evaluate the behaviour of the composites in a pool fire by determining the penetration time of silica aerogels used. The composites were developed to resist a fire penetration based on the standard of temperature and heat flux for at least 15 minutes for fireproof and 5 minutes for fire resistance. The developed samples are one weight percent of aerogel in the mixture of resin/hardener and were mixed using mechanical mixer and sonicator. The results indicate that composite of GEA^(TM) 0.125 silica aerogel resists higher flame than the other types of aerogel composites examined, where it was 5.56% and 10.39% more fire resistance than Enova® IC3100 and Hamzel® respectively. The study reveals that the developed composites possess the required properties to be used.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128409831","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 : 2021-06-01DOI: 10.6125/JOAAA.202106_53(2).08
M. Shafie, M. F. A. Hamid, A. Rafie, M. R. Saad
The potential of UAVs to serve as an alternative solution for performing inspection and surveillance is of greater interest when considering lower workforce and operating costs. Coanda effect-based UAV is one of the options. However, the present knowledge on this type of UAV is yet fully explored, such as the profile of the curved surface to harness the utmost lift force augmentation. This paper presents an experimental evaluation of the static lift force due to the changes in the curved surface tilting profile angle subjected to the Coanda jet flow. Two test models (axisymmetric 2D half-hemispherical curved surfaces) are considered in this study; semi-circular surface (Rx/Ry = 1) and semi-ellipse surface (Rx/Ry = 2). The static lift force is quantified through static pressure measurement from 13 pressure tapping points located at the centerline of the test models that are connected to a manometer. From the acquired measurements, the static pressure coefficient and lift coefficient distributions are plotted. The result has shown that altering the tilting angle of the test models has yielded additional static lift, up to about 30%; due to the translation of the concentrated pressure region on the curved surface. It was also shown that the semi-circular surface provides a higher lift output compared to the semi-ellipse surface.
{"title":"Aerodynamic Force of Coandà Jet on a Curved Surface with Tilted Profile","authors":"M. Shafie, M. F. A. Hamid, A. Rafie, M. R. Saad","doi":"10.6125/JOAAA.202106_53(2).08","DOIUrl":"https://doi.org/10.6125/JOAAA.202106_53(2).08","url":null,"abstract":"The potential of UAVs to serve as an alternative solution for performing inspection and surveillance is of greater interest when considering lower workforce and operating costs. Coanda effect-based UAV is one of the options. However, the present knowledge on this type of UAV is yet fully explored, such as the profile of the curved surface to harness the utmost lift force augmentation. This paper presents an experimental evaluation of the static lift force due to the changes in the curved surface tilting profile angle subjected to the Coanda jet flow. Two test models (axisymmetric 2D half-hemispherical curved surfaces) are considered in this study; semi-circular surface (Rx/Ry = 1) and semi-ellipse surface (Rx/Ry = 2). The static lift force is quantified through static pressure measurement from 13 pressure tapping points located at the centerline of the test models that are connected to a manometer. From the acquired measurements, the static pressure coefficient and lift coefficient distributions are plotted. The result has shown that altering the tilting angle of the test models has yielded additional static lift, up to about 30%; due to the translation of the concentrated pressure region on the curved surface. It was also shown that the semi-circular surface provides a higher lift output compared to the semi-ellipse surface.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"52 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129075835","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 : 2021-06-01DOI: 10.6125/JOAAA.202106_53(2).02
S. A. Shukri, F. I. Romli, Wan Teh Fatimah Wan Badaruddin, Aina Suriani Mahmood
There have been many aviation maintenance incidents that are linked to miscommunication and misinterpretation of maintenance instructions, which can lead to severe safety repercussion of flight operation. These occurrences are further related to the competency of English language among the aviation maintenance personnel, particularly among the non-native English speakers. In view of this notion, this study aims to gain an insight on the importance of English language among aviation maintenance personnel in Malaysia in order to perform their tasks through a conducted survey. A total of 22 respondents from various local aviation maintenance companies have participated in the survey. Based on the analysis results of the collected survey responses, it can be concluded that many aviation maintenance tasks frequently involve a high use of English language and the maintenance personnel need to possess good English language proficiency to ensure the correct and smooth execution of their tasks. This finding aptly implies the importance of English language in performing aviation maintenance works and it also supports the action taken by Civil Aviation Authority Malaysia to enforce additional English language competency requirement for all local maintenance personnel in Malaysia.
{"title":"Importance of English Language in Aviation Maintenance: A Malaysia Case Study","authors":"S. A. Shukri, F. I. Romli, Wan Teh Fatimah Wan Badaruddin, Aina Suriani Mahmood","doi":"10.6125/JOAAA.202106_53(2).02","DOIUrl":"https://doi.org/10.6125/JOAAA.202106_53(2).02","url":null,"abstract":"There have been many aviation maintenance incidents that are linked to miscommunication and misinterpretation of maintenance instructions, which can lead to severe safety repercussion of flight operation. These occurrences are further related to the competency of English language among the aviation maintenance personnel, particularly among the non-native English speakers. In view of this notion, this study aims to gain an insight on the importance of English language among aviation maintenance personnel in Malaysia in order to perform their tasks through a conducted survey. A total of 22 respondents from various local aviation maintenance companies have participated in the survey. Based on the analysis results of the collected survey responses, it can be concluded that many aviation maintenance tasks frequently involve a high use of English language and the maintenance personnel need to possess good English language proficiency to ensure the correct and smooth execution of their tasks. This finding aptly implies the importance of English language in performing aviation maintenance works and it also supports the action taken by Civil Aviation Authority Malaysia to enforce additional English language competency requirement for all local maintenance personnel in Malaysia.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"60 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123153459","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 : 2021-06-01DOI: 10.6125/JOAAA.202106_53(2).17
M. A. Wahid, N. Othman, M. Zain, N. Shaharuddin
The high demand for Unmanned Aerial System (UAS) in today's world increases our community's safety, well-being, and sustainability. However, there are still issues to be solved. One of the problems discussed in this paper is the UAS manoeuvring in the rural area and the ability of the UAS to manoeuvre around buildings or obstacles. This study conceptualizes the control method and motion used to avoid obstacles using a PID controller and a laser scanner embedded to a quadcopter. The distance error experiment measurement shows that the error decreases with distance and expected distance error is about 4mm with a standard deviation of 0.1577mm. The laser scanner distance error and standard deviation experimental measurement applied to Matlab Simulink's avoidance controller program shows that the algorithm can avoid obstacle with a minimum clearance of 0.5m to avoid damage on the quadcopter. The PID controller design can follow a defined path with some noise present in the horizontal position due to the scanner noise and a 5% error in altitude.
{"title":"Control and Simulation of Obstacle Avoidance for a Quadcopter","authors":"M. A. Wahid, N. Othman, M. Zain, N. Shaharuddin","doi":"10.6125/JOAAA.202106_53(2).17","DOIUrl":"https://doi.org/10.6125/JOAAA.202106_53(2).17","url":null,"abstract":"The high demand for Unmanned Aerial System (UAS) in today's world increases our community's safety, well-being, and sustainability. However, there are still issues to be solved. One of the problems discussed in this paper is the UAS manoeuvring in the rural area and the ability of the UAS to manoeuvre around buildings or obstacles. This study conceptualizes the control method and motion used to avoid obstacles using a PID controller and a laser scanner embedded to a quadcopter. The distance error experiment measurement shows that the error decreases with distance and expected distance error is about 4mm with a standard deviation of 0.1577mm. The laser scanner distance error and standard deviation experimental measurement applied to Matlab Simulink's avoidance controller program shows that the algorithm can avoid obstacle with a minimum clearance of 0.5m to avoid damage on the quadcopter. The PID controller design can follow a defined path with some noise present in the horizontal position due to the scanner noise and a 5% error in altitude.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"36 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115780469","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 : 2021-06-01DOI: 10.6125/JOAAA.202106_53(2).04
Hindawan Hariowibowo, O. Arifianto, H. M. Pasaribu, H. Muhammad
In the early stage of fighter aircraft development, handling quality (HQ) become an important aspect in evaluating design results. One aspect of handling quality which involving pilot-in-the-loop, known as closed loop handling quality (CLHQ) will determine aircraft acceptability to fulfill its operational requirements. This paper explains the dynamic model of fighter aircraft for lateral-directional motions and simulate the CLHQ. The dynamic model consists of aircraft equation of motion and flight control system. In order to make CLHQ simulation, a pilot model has been added to the dynamic model. The simulation results are utilized to evaluate the sensitivity of the parameter values inside the elements of the dynamic model and the pilot model. Also, the current simulation results of CLHQ will be used for an evaluation of aircraft Pilot-Induced-Oscillation (PIO) phenomenon.
{"title":"Fighter Aircraft Closed Loop Handling Quality Simulation on Lateral-Directional Modes","authors":"Hindawan Hariowibowo, O. Arifianto, H. M. Pasaribu, H. Muhammad","doi":"10.6125/JOAAA.202106_53(2).04","DOIUrl":"https://doi.org/10.6125/JOAAA.202106_53(2).04","url":null,"abstract":"In the early stage of fighter aircraft development, handling quality (HQ) become an important aspect in evaluating design results. One aspect of handling quality which involving pilot-in-the-loop, known as closed loop handling quality (CLHQ) will determine aircraft acceptability to fulfill its operational requirements. This paper explains the dynamic model of fighter aircraft for lateral-directional motions and simulate the CLHQ. The dynamic model consists of aircraft equation of motion and flight control system. In order to make CLHQ simulation, a pilot model has been added to the dynamic model. The simulation results are utilized to evaluate the sensitivity of the parameter values inside the elements of the dynamic model and the pilot model. Also, the current simulation results of CLHQ will be used for an evaluation of aircraft Pilot-Induced-Oscillation (PIO) phenomenon.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"42 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114717686","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 : 2021-06-01DOI: 10.6125/JOAAA.202106_53(2).23
M. Johari, Z. Ali, W. Wisnoe, Noriswadi Ismail, I. S. Ishak
This paper discusses the aerodynamic characteristics of Hawkeye UAV aircraft with a forward-swept wing configuration. The unconventional wing design on Hawkeye allows for better maneuverability and stability during a field test but there were no prior studies on its aerodynamic characteristics. A series of CFD simulations were conducted using ANSYS Fluent to obtain the aerodynamic characteristic of Hawkeye; lift, drag and moment coefficient. A full-size model and Reynolds-averaged Navier-Stokes (RANS) numerical method-based equations, Spalart-Allmaras turbulence model was used for the simulation. The angle of attack of the aircraft differs from -10° to 30° with an interval of 2° at a flight condition of Mach number 0.1 (~35 m/s). The CFD results obtained will be used to calculate the aircraft performance in a real field test and for future improvement of the UAV.
{"title":"Computational Aerodynamic Analysis of UiTM's Hawkeye UAV Aircraft","authors":"M. Johari, Z. Ali, W. Wisnoe, Noriswadi Ismail, I. S. Ishak","doi":"10.6125/JOAAA.202106_53(2).23","DOIUrl":"https://doi.org/10.6125/JOAAA.202106_53(2).23","url":null,"abstract":"This paper discusses the aerodynamic characteristics of Hawkeye UAV aircraft with a forward-swept wing configuration. The unconventional wing design on Hawkeye allows for better maneuverability and stability during a field test but there were no prior studies on its aerodynamic characteristics. A series of CFD simulations were conducted using ANSYS Fluent to obtain the aerodynamic characteristic of Hawkeye; lift, drag and moment coefficient. A full-size model and Reynolds-averaged Navier-Stokes (RANS) numerical method-based equations, Spalart-Allmaras turbulence model was used for the simulation. The angle of attack of the aircraft differs from -10° to 30° with an interval of 2° at a flight condition of Mach number 0.1 (~35 m/s). The CFD results obtained will be used to calculate the aircraft performance in a real field test and for future improvement of the UAV.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124944987","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 : 2021-06-01DOI: 10.6125/JOAAA.202106_53(2).22
Ömer Seçgin, M. Sogut
In the aviation industry, it is essential to use parts that are lightweight but durable, and aluminum alloys generally provides effective solutions. In manufacturing processes, automation-based production techniques and robotic and efficient processing processes such as Computer Numeric Technique (CNC) are used, and it is important to define optimum production parameters. In this study, parametric optimization values of machining criteria were developed for the milling operation of AL 6068 aluminum alloy. For this purpose, Response Surface Method (RSM) was used for optimal solutions of parametric values and evaluation of relationships. According this, optimum processing parameters were determined to be 1521 rpm revolution speed, 0.4 mm depth of cut, and 197 mm/min federate. These manufacturing parameters were evaluated. A quadratic regression equation giving the surface roughness was created for this operation. At the end of the study, some suggestions were made regarding the improvement of production efficiency based on the parameters defined.
{"title":"Parametric Optimization of Machining Criteria for Al 6068 Aluminum Alloy using in Manufacturing Process of Aircraft","authors":"Ömer Seçgin, M. Sogut","doi":"10.6125/JOAAA.202106_53(2).22","DOIUrl":"https://doi.org/10.6125/JOAAA.202106_53(2).22","url":null,"abstract":"In the aviation industry, it is essential to use parts that are lightweight but durable, and aluminum alloys generally provides effective solutions. In manufacturing processes, automation-based production techniques and robotic and efficient processing processes such as Computer Numeric Technique (CNC) are used, and it is important to define optimum production parameters. In this study, parametric optimization values of machining criteria were developed for the milling operation of AL 6068 aluminum alloy. For this purpose, Response Surface Method (RSM) was used for optimal solutions of parametric values and evaluation of relationships. According this, optimum processing parameters were determined to be 1521 rpm revolution speed, 0.4 mm depth of cut, and 197 mm/min federate. These manufacturing parameters were evaluated. A quadratic regression equation giving the surface roughness was created for this operation. At the end of the study, some suggestions were made regarding the improvement of production efficiency based on the parameters defined.","PeriodicalId":335344,"journal":{"name":"Journal of aeronautics, astronautics and aviation, Series A","volume":"95 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117312393","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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