Pub Date : 2020-09-10DOI: 10.23890/ijast.vm01is01.0102
B. Unal, Tamer Savas, I. Yazar
Today, coupled with technological development, UAV (Unmanned Aerial Vehicle) systems show an important improvement in civil area applications. UAV systems have active tasks with cost-effective solutions in several areas like defense, logistics, engineering and agriculture. Especially in agricultural applications, UAV system usage contributes to improvement of the critical parameters of this sector as efficiency and sustainability. Thus, in agricultural areas, improvement and usage of unmanned systems are of importance. In this study, a remote-control rotary wing UAV system that has the ability to perform irrigation and spraying and its design, production and application processes are discussed. The designed, verified and all test operations completed UAV system is planned to be used in remote control liquid rejection in the agricultural area.
{"title":"Design of a Pesticide Spraying Quadcopter","authors":"B. Unal, Tamer Savas, I. Yazar","doi":"10.23890/ijast.vm01is01.0102","DOIUrl":"https://doi.org/10.23890/ijast.vm01is01.0102","url":null,"abstract":"Today, coupled with technological development, UAV (Unmanned Aerial Vehicle) systems show an important improvement in civil area applications. UAV systems have active tasks with cost-effective solutions in several areas like defense, logistics, engineering and agriculture. Especially in agricultural applications, UAV system usage contributes to improvement of the critical parameters of this sector as efficiency and sustainability. Thus, in agricultural areas, improvement and usage of unmanned systems are of importance. In this study, a remote-control rotary wing UAV system that has the ability to perform irrigation and spraying and its design, production and application processes are discussed. The designed, verified and all test operations completed UAV system is planned to be used in remote control liquid rejection in the agricultural area.","PeriodicalId":178218,"journal":{"name":"International Journal of Aviation Science and Technology","volume":"100 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-09-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122606376","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 : 2020-06-27DOI: 10.23890/ijast.vm02is01.0103
H. Akdeniz
In this study, it is aimed to assess the aerodynamic and flight effects of the flap design on an airfoil. For this purpose, NACA 4415 type wing profile, which can also be used in unmanned aerial vehicles (UAVs), is selected. The original design and the +5-degree flapped design which has constant other design features are compared. Assessments are performed under constant Reynolds numbers and an angle of attack between 0-10 degrees with a 1-degree interval. Analyses are made using the open-source software XFLR5. For the flapped design is named NACA 4415-2, some basic aerodynamic performance parameters such as coefficient of drag (CD), coefficient of lift (CL) coefficient of pressure (Cp) maximum lift coefficient (Clmax) and minimum stall velocity (Vstall) have been observed. According to results, when the flap with 5o is added to the airfoil, it has been observed that the CL and Lift force of the original design of the airfoil increase significantly, CD of the airfoil increase partially, and the pressure coefficient tends to decrease significantly. Furthermore, it has been observed that while the minimum stall velocity has decreased, Clmax values increased.
{"title":"A Study on Aerodynamic Behavior of Subsonic UAVs' Wing Sections with Flaps","authors":"H. Akdeniz","doi":"10.23890/ijast.vm02is01.0103","DOIUrl":"https://doi.org/10.23890/ijast.vm02is01.0103","url":null,"abstract":"In this study, it is aimed to assess the aerodynamic and flight effects of the flap design on an airfoil. For this purpose, NACA 4415 type wing profile, which can also be used in unmanned aerial vehicles (UAVs), is selected. The original design and the +5-degree flapped design which has constant other design features are compared. Assessments are performed under constant Reynolds numbers and an angle of attack between 0-10 degrees with a 1-degree interval. Analyses are made using the open-source software XFLR5. For the flapped design is named NACA 4415-2, some basic aerodynamic performance parameters such as coefficient of drag (CD), coefficient of lift (CL) coefficient of pressure (Cp) maximum lift coefficient (Clmax) and minimum stall velocity (Vstall) have been observed. According to results, when the flap with 5o is added to the airfoil, it has been observed that the CL and Lift force of the original design of the airfoil increase significantly, CD of the airfoil increase partially, and the pressure coefficient tends to decrease significantly. Furthermore, it has been observed that while the minimum stall velocity has decreased, Clmax values increased.","PeriodicalId":178218,"journal":{"name":"International Journal of Aviation Science and Technology","volume":"41 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-06-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133039194","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}
{"title":"Volume 01 Issue 02","authors":"canadien de ehirurgie","doi":"10.23890/ijast.vm01is01","DOIUrl":"https://doi.org/10.23890/ijast.vm01is01","url":null,"abstract":"","PeriodicalId":178218,"journal":{"name":"International Journal of Aviation Science and Technology","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122548375","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 : 2019-12-18DOI: 10.23890/ijast.2019.0102
Can Beker, A. E. Turgut, Kutluk Bilge Arıkan, D. Kurtulus
In this study, a 3D model of the bio-inspired blowfly wing Callphere Erytrocephala is created and aeroelastic analysis is performed to calculate its aerodynamical characteristics by use of numerical methods. To perform the flapping motion, a sinusoidal input function is created. The scope of this study is to perform aeroelastic analysis by synchronizing computational fluid dynamics (CFD) and structural dynamic analysis models and to investigate the unsteady lift formation on the aeroelastic flapping wing for different angles of attack.
{"title":"Aeroelastic Analysis of a Flapping Blow Fly Wing","authors":"Can Beker, A. E. Turgut, Kutluk Bilge Arıkan, D. Kurtulus","doi":"10.23890/ijast.2019.0102","DOIUrl":"https://doi.org/10.23890/ijast.2019.0102","url":null,"abstract":"In this study, a 3D model of the bio-inspired blowfly wing Callphere Erytrocephala is created and aeroelastic analysis is performed to calculate its aerodynamical characteristics by use of numerical methods. To perform the flapping motion, a sinusoidal input function is created. The scope of this study is to perform aeroelastic analysis by synchronizing computational fluid dynamics (CFD) and structural dynamic analysis models and to investigate the unsteady lift formation on the aeroelastic flapping wing for different angles of attack.","PeriodicalId":178218,"journal":{"name":"International Journal of Aviation Science and Technology","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-12-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116703332","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 : 2019-12-18DOI: 10.23890/ijast.2019.0103
Ali Dinç
In this study, preliminary sizing of a turboprop engine powered high altitude unmanned aerial vehicle and it`s propulsion system for an assumed mission profile in Turkey was performed. Aircraft mission profile is one of the most important design inputs in aircraft design. While the aircraft is dimensioned according to the requirements in the specification (useful payload, range, target cost, etc.), parameters such as cruise altitude and speed within the mission profile affect the engine type, power level, fuel quantity, and therefore the overall dimensions and total weight of the aircraft. The unmanned aerial vehicle with turboprop engine investigated in this study, can stay in the air for at least 24 hours at high altitude (40000 ft) and can be used for border surveillance, coast control, forest fires and land exploration.
{"title":"Sizing of a Turboprop Engine Powered High Altitude Unmanned Aerial Vehicle and It`s Propulsion System for an Assumed Mission Profile in Turkey","authors":"Ali Dinç","doi":"10.23890/ijast.2019.0103","DOIUrl":"https://doi.org/10.23890/ijast.2019.0103","url":null,"abstract":"In this study, preliminary sizing of a turboprop engine powered high altitude unmanned aerial vehicle and it`s propulsion system for an assumed mission profile in Turkey was performed. Aircraft mission profile is one of the most important design inputs in aircraft design. While the aircraft is dimensioned according to the requirements in the specification (useful payload, range, target cost, etc.), parameters such as cruise altitude and speed within the mission profile affect the engine type, power level, fuel quantity, and therefore the overall dimensions and total weight of the aircraft. The unmanned aerial vehicle with turboprop engine investigated in this study, can stay in the air for at least 24 hours at high altitude (40000 ft) and can be used for border surveillance, coast control, forest fires and land exploration.","PeriodicalId":178218,"journal":{"name":"International Journal of Aviation Science and Technology","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-12-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130353972","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 : 2019-12-18DOI: 10.23890/ijast.2019.0106
{"title":"First Issue of 2019","authors":"","doi":"10.23890/ijast.2019.0106","DOIUrl":"https://doi.org/10.23890/ijast.2019.0106","url":null,"abstract":"","PeriodicalId":178218,"journal":{"name":"International Journal of Aviation Science and Technology","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-12-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121636393","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 : 1900-01-01DOI: 10.23890/ijast.vm04is01.0106
{"title":"**************************","authors":"","doi":"10.23890/ijast.vm04is01.0106","DOIUrl":"https://doi.org/10.23890/ijast.vm04is01.0106","url":null,"abstract":"","PeriodicalId":178218,"journal":{"name":"International Journal of Aviation Science and Technology","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128155614","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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