Pub Date : 2023-06-30DOI: 10.15866/irease.v16i3.22632
Michael Joevian, Sheila Tobing, Rainer Louis Surjadi, Kenneth Timothy, Adrianus Indrat Aria
Numerous investigations on flapping wing motion have been conducted over the last two decades. The study of flapping wing motion was inspired by the possibility of using it to design and develop micro air vehicles. The application of flapping wing motion in power generation systems has attracted attention recently because of the growing need to replace fossil fuels with renewable energy sources. This research examines the effect of pitch oscillation frequency on the propulsion of a tandem flapping foils power generation system. Herein, the 2D models of tandem foils pitching with reduced frequencies f* of 0.04, 0.14, and 0.18 are used for parametric investigation. The results reveal that f* = 0.18 offers the optimal lift force among other reduced frequencies and 2.91% lower drag force compared to f* = 0.14.
{"title":"Numerical Analysis of Reduced Frequency on Flapping Tandem Foils","authors":"Michael Joevian, Sheila Tobing, Rainer Louis Surjadi, Kenneth Timothy, Adrianus Indrat Aria","doi":"10.15866/irease.v16i3.22632","DOIUrl":"https://doi.org/10.15866/irease.v16i3.22632","url":null,"abstract":"Numerous investigations on flapping wing motion have been conducted over the last two decades. The study of flapping wing motion was inspired by the possibility of using it to design and develop micro air vehicles. The application of flapping wing motion in power generation systems has attracted attention recently because of the growing need to replace fossil fuels with renewable energy sources. This research examines the effect of pitch oscillation frequency on the propulsion of a tandem flapping foils power generation system. Herein, the 2D models of tandem foils pitching with reduced frequencies f* of 0.04, 0.14, and 0.18 are used for parametric investigation. The results reveal that f* = 0.18 offers the optimal lift force among other reduced frequencies and 2.91% lower drag force compared to f* = 0.14.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"126 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136300269","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 : 2023-06-30DOI: 10.15866/irease.v16i3.22588
Sergey Kravchenko, Nikolay Kuleshov, Ilmars Blumbergs, Natalia Kravchenko, Vladimir Shestakov, Daria Panova, Aya Medany
Since 2019, Riga Technical University, Institute of Aeronautics, in partnership with Cryogenic and vacuum systems Ltd (Ventspils), executed the European Regional Development Fund Project No. 1.1.1.1/18/A/133 “Prototype development of transportable in multimodal traffic mobile space testing facility Metamorphosis.” In the process of realization of the project, the analysis of the technical failure risk was provided. Most risk components were detached, and several measures for risk prevention were performed. During the testing of the prototype, it turned out that significant vibration and shock loads acted on the prototype during movement, so some design changes were made. The development of the variational vacuum system calculation model allowed the project team to find the solutions and successfully finish the tests, proofing the concept of the mobile thermal vacuum test facility. This article describes the problem and the search for a solution and shows its implementation.
{"title":"Some Results of the Mobile Space Testing Facility Metamorphosis Prototype Design, Development and Test","authors":"Sergey Kravchenko, Nikolay Kuleshov, Ilmars Blumbergs, Natalia Kravchenko, Vladimir Shestakov, Daria Panova, Aya Medany","doi":"10.15866/irease.v16i3.22588","DOIUrl":"https://doi.org/10.15866/irease.v16i3.22588","url":null,"abstract":"Since 2019, Riga Technical University, Institute of Aeronautics, in partnership with Cryogenic and vacuum systems Ltd (Ventspils), executed the European Regional Development Fund Project No. 1.1.1.1/18/A/133 “Prototype development of transportable in multimodal traffic mobile space testing facility Metamorphosis.” In the process of realization of the project, the analysis of the technical failure risk was provided. Most risk components were detached, and several measures for risk prevention were performed. During the testing of the prototype, it turned out that significant vibration and shock loads acted on the prototype during movement, so some design changes were made. The development of the variational vacuum system calculation model allowed the project team to find the solutions and successfully finish the tests, proofing the concept of the mobile thermal vacuum test facility. This article describes the problem and the search for a solution and shows its implementation.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136300271","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}
During night flights of unmanned aerial vehicles, determining the location of the device during take-off and landing and the possibility of injury to maintenance personnel from a rotating propeller poses a certain problem. The problem is especially pronounced with a large diameter of rotor blade, which is difficult to highlight with a strobe light. The article describes the design of the rotor blade tip’s illumination system, which can be placed on propellers of any diameter without an additional battery source. This allows not only to make these lighting systems maintenance-free but also to fly in extreme conditions of low temperatures. This novelty will be especially useful when operating in the Arctic, where the polar night lasts for several months and there are very low ambient temperatures.
{"title":"The System of Rotor Blade Tip’s Illumination for Unmanned Aerial Vehicles","authors":"Vadim Carev, Sergey Tkachenko, Andrey Shpilevoy, Aleksandr Kaychenov, Dmitriy Ozhigin, Nurbol Kaliaskarov","doi":"10.15866/irease.v16i3.23537","DOIUrl":"https://doi.org/10.15866/irease.v16i3.23537","url":null,"abstract":"During night flights of unmanned aerial vehicles, determining the location of the device during take-off and landing and the possibility of injury to maintenance personnel from a rotating propeller poses a certain problem. The problem is especially pronounced with a large diameter of rotor blade, which is difficult to highlight with a strobe light. The article describes the design of the rotor blade tip’s illumination system, which can be placed on propellers of any diameter without an additional battery source. This allows not only to make these lighting systems maintenance-free but also to fly in extreme conditions of low temperatures. This novelty will be especially useful when operating in the Arctic, where the polar night lasts for several months and there are very low ambient temperatures.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136300272","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 : 2023-06-30DOI: 10.15866/irease.v16i3.23400
James Julian, Waridho Iskandar, Fitri Wahyuni, Muhammad Ilham Adhynugraha, Fadilah Hasim
This study discusses the aerodynamics of the R-HAN 122 rocket and the modification of the nose shape using computational methods. Fluid flow simulation uses the RANS equation, which has been adjusted for compressible fluid flow. The turbulence model in this study is the standard k-ε. The analysis has been carried out in two dimensions. The mesh used is a structured mesh type using quadrilateral element shapes. The number of mesh elements used in this study is 2×105. The nose models in this study have been ogive (baseline), cone, and hemisphere. The fluid flow velocity in this study is Mach 1.602. The nose cone and the hemisphere shape can increase the Cl of the R-HAN 122 rocket at 4º
{"title":"Numerical Study on Aerodynamics Characteristics of R-HAN122 Along with Nose Modification","authors":"James Julian, Waridho Iskandar, Fitri Wahyuni, Muhammad Ilham Adhynugraha, Fadilah Hasim","doi":"10.15866/irease.v16i3.23400","DOIUrl":"https://doi.org/10.15866/irease.v16i3.23400","url":null,"abstract":"This study discusses the aerodynamics of the R-HAN 122 rocket and the modification of the nose shape using computational methods. Fluid flow simulation uses the RANS equation, which has been adjusted for compressible fluid flow. The turbulence model in this study is the standard k-ε. The analysis has been carried out in two dimensions. The mesh used is a structured mesh type using quadrilateral element shapes. The number of mesh elements used in this study is 2×105. The nose models in this study have been ogive (baseline), cone, and hemisphere. The fluid flow velocity in this study is Mach 1.602. The nose cone and the hemisphere shape can increase the Cl of the R-HAN 122 rocket at 4º<AoA<10º. However, the R-HAN 122 Cd rocket increases when the nose shape is modified into a cone or hemisphere shape. The optimum AoA at baseline R-HAN 122 and cone-shaped nose is 6º. When the nose rocket shape of the R-HAN 122 is modified with a hemisphere shape, it will produce an optimum AoA of 8°. The shockwave is formed around the R-HAN 122, which changes the density and Mach number in the shockwave area. The cone-shaped nose receives the slightest pressure, while the hemisphere-shaped nose receives the highest pressure.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"141 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136300270","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 : 2023-06-30DOI: 10.15866/irease.v16i3.23569
Subbaramu Shivaramaiah, Mahesh K. Varpe
Performance of a NASA 37 transonic compressor stage with a symmetric Airfoil Vortex Generator (AVG) positioned in the upstream of rotor is investigated through a numerical simulation. Steady state flow simulations were performed with k-ω SST turbulence model in ANSYS CFX flow solver. Grid independence study for the baseline compressor was performed besides CFD predicted performance characteristics were validated against available experimental data. The results of parametric study shows that AVG is able to improve compressor stall margin with a penalty on the stage efficiency. Incorporation of an AVG on the casing surface upstream of rotor reduces its specific work capacity, incurs flow losses and decreases stage peak efficiency by 3.34%. However few AVG configurations have negligible reduction, nearly 0.27-0.4%, in stage efficiency compared to baseline case. At near stall operating point, an AVG affects both rotor and stator flow field. An AVG under loads rotor tip region and decreases tip leakage mass flow rate, leading to the reduction of flow blockage. The flow swallowing capacity of the stator passage increases by diffusing the flow considerably to a low velocity. Consequently, AVG is able to increase the compressor stage stall margin by 8.06%.
{"title":"Aerodynamic Performance and Stability of a Transonic Axial Compressor Stage with an Airfoil Vortex Generator","authors":"Subbaramu Shivaramaiah, Mahesh K. Varpe","doi":"10.15866/irease.v16i3.23569","DOIUrl":"https://doi.org/10.15866/irease.v16i3.23569","url":null,"abstract":"Performance of a NASA 37 transonic compressor stage with a symmetric Airfoil Vortex Generator (AVG) positioned in the upstream of rotor is investigated through a numerical simulation. Steady state flow simulations were performed with k-ω SST turbulence model in ANSYS CFX flow solver. Grid independence study for the baseline compressor was performed besides CFD predicted performance characteristics were validated against available experimental data. The results of parametric study shows that AVG is able to improve compressor stall margin with a penalty on the stage efficiency. Incorporation of an AVG on the casing surface upstream of rotor reduces its specific work capacity, incurs flow losses and decreases stage peak efficiency by 3.34%. However few AVG configurations have negligible reduction, nearly 0.27-0.4%, in stage efficiency compared to baseline case. At near stall operating point, an AVG affects both rotor and stator flow field. An AVG under loads rotor tip region and decreases tip leakage mass flow rate, leading to the reduction of flow blockage. The flow swallowing capacity of the stator passage increases by diffusing the flow considerably to a low velocity. Consequently, AVG is able to increase the compressor stage stall margin by 8.06%.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"604 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136300273","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 : 2021-04-30DOI: 10.15866/IREASE.V14I2.19363
C. Pardo, J. Pabón, Marlen Fonseca Vigoya
{"title":"Study of the Detonation Wave in a Rotating Detonation Combustor Using Hydrogen and Mixtures Ethylene-Acetylene","authors":"C. Pardo, J. Pabón, Marlen Fonseca Vigoya","doi":"10.15866/IREASE.V14I2.19363","DOIUrl":"https://doi.org/10.15866/IREASE.V14I2.19363","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"334 1","pages":"64"},"PeriodicalIF":0.0,"publicationDate":"2021-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77972907","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 : 2021-04-30DOI: 10.15866/IREASE.V14I2.19303
A. Varyukhin, V. Zakharchenko, M. Gordin, F. Ismagilov, V. Vavilov, D. Gusakov, R. Karimov
{"title":"Conceptual Design of Electric Machines for a Serial Hybrid Propulsion System of Commuter Airliner","authors":"A. Varyukhin, V. Zakharchenko, M. Gordin, F. Ismagilov, V. Vavilov, D. Gusakov, R. Karimov","doi":"10.15866/IREASE.V14I2.19303","DOIUrl":"https://doi.org/10.15866/IREASE.V14I2.19303","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"1 1","pages":"80"},"PeriodicalIF":0.0,"publicationDate":"2021-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74858271","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 : 2021-04-30DOI: 10.15866/IREASE.V14I2.19209
Meriem Abidi, H. Fizazi, Nourredine Boudali
{"title":"Clustering of Remote Sensing Data Based on Spherical Evolution Algorithm","authors":"Meriem Abidi, H. Fizazi, Nourredine Boudali","doi":"10.15866/IREASE.V14I2.19209","DOIUrl":"https://doi.org/10.15866/IREASE.V14I2.19209","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"49 1","pages":"72"},"PeriodicalIF":0.0,"publicationDate":"2021-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74606135","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 : 2021-04-30DOI: 10.15866/IREASE.V14I2.19596
S. B. M. Zaki, M. Cho, Nobuyuki Kaya
{"title":"Adaptive Array Antenna in Ground Station Control System for Massive LEO CubeSat Constellation Tracking","authors":"S. B. M. Zaki, M. Cho, Nobuyuki Kaya","doi":"10.15866/IREASE.V14I2.19596","DOIUrl":"https://doi.org/10.15866/IREASE.V14I2.19596","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"96 1","pages":"97"},"PeriodicalIF":0.0,"publicationDate":"2021-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82225758","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 : 2021-04-30DOI: 10.15866/IREASE.V14I2.20082
R. Rozenberg, A. Tobisová, A. Seňová, G. Izaríková, D. Blasko
{"title":"Assessing Environmental and Health Impact: Fires in Civil Aircraft","authors":"R. Rozenberg, A. Tobisová, A. Seňová, G. Izaríková, D. Blasko","doi":"10.15866/IREASE.V14I2.20082","DOIUrl":"https://doi.org/10.15866/IREASE.V14I2.20082","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"47 1","pages":"51"},"PeriodicalIF":0.0,"publicationDate":"2021-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75328282","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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