Pub Date : 1900-01-01DOI: 10.13164/CONF.READ.2018.10
Nina Malalan, P. Zikmund
A research about different ways of encoding the distance information with vibrotactile feedback was done as part of a bigger project with the aim of designing a device which would help the pilot to achieve greater precision during the flight. Different kinds of stall warning devices and structural additions were already designed in the field of aviation, lingering only over attentional guidance. Therefore, a lack of spatial and movement guidance was detected. This paper lingers on this research which aimed to encode and evaluate haptic guiding methods.
{"title":"Vibration feedbacks in pilot-aircraft haptic interaction","authors":"Nina Malalan, P. Zikmund","doi":"10.13164/CONF.READ.2018.10","DOIUrl":"https://doi.org/10.13164/CONF.READ.2018.10","url":null,"abstract":"A research about different ways of encoding the distance information with vibrotactile feedback was done as part of a bigger project with the aim of designing a device which would help the pilot to achieve greater precision during the flight. Different kinds of stall warning devices and structural additions were already designed in the field of aviation, lingering only over attentional guidance. Therefore, a lack of spatial and movement guidance was detected. This paper lingers on this research which aimed to encode and evaluate haptic guiding methods.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"12 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":"123323126","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: 10.13164/conf.read.2018.7
P. Augustin
Simulation of fatigue crack growth in the bottom flange of twin turboprop commuter aircraft wing spar is described in this paper. Analysed crack propagation scenario represents real wing fullscale fatigue test failure. Computational model of bottom flange was prepared using threedimensional fracture mechanics software FRANC3D. Calculation of crack growth under the variable amplitude loading was performed in AFGROW code using the NASGRO equation and Wheeler retardation model. It was verified with the results of wing spar specimen fatigue test and fractograpic analysis of fatigue fracture from this experiment. Computational model was applied in the prognostic algorithm of structure health monitoring system. NOMENCLATURE a crack length da/dN crack growth rate G shear modulus K stress intensity factor KC fracture toughness Kop opening stress intensity factor Kth threshold stress intensity factor range R stress ratio constraint factor Poisson’s ratio O flow stress YS tensile yield strength
{"title":"Simulation of fatigue crack propagation in the wing main spar flange","authors":"P. Augustin","doi":"10.13164/conf.read.2018.7","DOIUrl":"https://doi.org/10.13164/conf.read.2018.7","url":null,"abstract":"Simulation of fatigue crack growth in the bottom flange of twin turboprop commuter aircraft wing spar is described in this paper. Analysed crack propagation scenario represents real wing fullscale fatigue test failure. Computational model of bottom flange was prepared using threedimensional fracture mechanics software FRANC3D. Calculation of crack growth under the variable amplitude loading was performed in AFGROW code using the NASGRO equation and Wheeler retardation model. It was verified with the results of wing spar specimen fatigue test and fractograpic analysis of fatigue fracture from this experiment. Computational model was applied in the prognostic algorithm of structure health monitoring system. NOMENCLATURE a crack length da/dN crack growth rate G shear modulus K stress intensity factor KC fracture toughness Kop opening stress intensity factor Kth threshold stress intensity factor range R stress ratio constraint factor Poisson’s ratio O flow stress YS tensile yield strength","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"24 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":"130510196","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: 10.13164/CONF.READ.2018.2
Rostislav Koštial, Luboš Janhuba, J. Hlinka
Aircraft leading edge is one of the most important subjects of aircraft scheduled maintenance. Leading edge as part of the slot on transport aircraft is not critical to fatigue stress in most of the cases. However, leading edge is extremely vulnerable to the accidental damage in combination with environmental damage. Maintenance is usually provided by visual inspection before every flight. Nevertheless, development of anti-icing system based on contact electrical heating opens possibility to thermographic Nondestructive Testing (NDT) methods usage. These methods could detect minor damages, which are visually undetectable especially in the case of composite materials. This paper describes possibility of thermographic methods (using anti-icing system) application as mean of leading edge minor damage detection.
{"title":"Aircraft leading edges minor damages detection based on thermographic survey of electrical anti-icing system","authors":"Rostislav Koštial, Luboš Janhuba, J. Hlinka","doi":"10.13164/CONF.READ.2018.2","DOIUrl":"https://doi.org/10.13164/CONF.READ.2018.2","url":null,"abstract":"Aircraft leading edge is one of the most important subjects of aircraft scheduled maintenance. Leading edge as part of the slot on transport aircraft is not critical to fatigue stress in most of the cases. However, leading edge is extremely vulnerable to the accidental damage in combination with environmental damage. Maintenance is usually provided by visual inspection before every flight. Nevertheless, development of anti-icing system based on contact electrical heating opens possibility to thermographic Nondestructive Testing (NDT) methods usage. These methods could detect minor damages, which are visually undetectable especially in the case of composite materials. This paper describes possibility of thermographic methods (using anti-icing system) application as mean of leading edge minor damage detection.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"57 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":"133643004","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: 10.13164/CONF.READ.2018.16
A. Nõmmik
The beginning of the twenty-first century in air transportation is characterized by increasing competition between (regular, i.e. not low-cost) airlines, which in its turn affects the low cost airlines by necessitating for them the operating of aircraft with larger seat capacity also on local routes, with the goal of operating the aircraft at lower cost per available seat kilometer. Taking into account the importance of air connections for the regional economy, the local authorities are obligated to support regional airports and impose public service obligations on some routes. This study examines the regional aircraft development after the air transportation market liberalization, while also delving into the background of differences in environments of operation in Europe and United States. To evaluate the regional routes’ equipment competitiveness, this research is focusing on to the regional aircraft fuel consumption which is the considerable factor for airline’s operating costs. Analysis of the differences between operating environments in Europe and the United States is based on an earlier review of the research findings on development of the markets after liberalization, and the role regional aircraft in air transportation system. Also, the comparisons of the profitability and airlines’ strategies in both regions are given. The results provide insights into the main drivers of regional aircraft design and development from the demand’s point of view.
{"title":"Trends in development of aircraft for regional routes: impact on the european air transportation system","authors":"A. Nõmmik","doi":"10.13164/CONF.READ.2018.16","DOIUrl":"https://doi.org/10.13164/CONF.READ.2018.16","url":null,"abstract":"The beginning of the twenty-first century in air transportation is characterized by increasing competition between (regular, i.e. not low-cost) airlines, which in its turn affects the low cost airlines by necessitating for them the operating of aircraft with larger seat capacity also on local routes, with the goal of operating the aircraft at lower cost per available seat kilometer. Taking into account the importance of air connections for the regional economy, the local authorities are obligated to support regional airports and impose public service obligations on some routes. This study examines the regional aircraft development after the air transportation market liberalization, while also delving into the background of differences in environments of operation in Europe and United States. To evaluate the regional routes’ equipment competitiveness, this research is focusing on to the regional aircraft fuel consumption which is the considerable factor for airline’s operating costs. Analysis of the differences between operating environments in Europe and the United States is based on an earlier review of the research findings on development of the markets after liberalization, and the role regional aircraft in air transportation system. Also, the comparisons of the profitability and airlines’ strategies in both regions are given. The results provide insights into the main drivers of regional aircraft design and development from the demand’s point of view.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"28 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":"128944410","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: 10.13164/CONF.READ.2018.9
F. Löffelmann, Jan Šplíchal
A miniaturized heat switch is a device under the development dedicated to control automatic cooling of a space instrument box. The design study presented in this paper focuses on a stiffness issue of the switch base plate which should assure good thermal contact with the instrument box. Due to inner deformations of the switch, base plate deforms which might decrease contact area needed to the heat transfer. Thus several design concepts of the copper base plate were investigated and multimaterial additive manufacturing was reviewed. One approach was to decrease deformations of existing geometry by multi-material design by local exchange of copper with steel, first by engineering intuition, then by the stiffness based topology optimization, and finally with the layer-wise topology optimization better respecting manufacturing possibilities. Another approach was to change the geometry and use the topology optimization constrained with a flatness of the base plate but with single material. Finally, deformation changes of all the variants were compared.
{"title":"Design study of the heat switch base plate with single and multi-material topology optimization","authors":"F. Löffelmann, Jan Šplíchal","doi":"10.13164/CONF.READ.2018.9","DOIUrl":"https://doi.org/10.13164/CONF.READ.2018.9","url":null,"abstract":"A miniaturized heat switch is a device under the development dedicated to control automatic cooling of a space instrument box. The design study presented in this paper focuses on a stiffness issue of the switch base plate which should assure good thermal contact with the instrument box. Due to inner deformations of the switch, base plate deforms which might decrease contact area needed to the heat transfer. Thus several design concepts of the copper base plate were investigated and multimaterial additive manufacturing was reviewed. One approach was to decrease deformations of existing geometry by multi-material design by local exchange of copper with steel, first by engineering intuition, then by the stiffness based topology optimization, and finally with the layer-wise topology optimization better respecting manufacturing possibilities. Another approach was to change the geometry and use the topology optimization constrained with a flatness of the base plate but with single material. Finally, deformation changes of all the variants were compared.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"144 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":"128627585","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: 10.13164/CONF.READ.2018.12
J. Mašek, D. Koutný, R. Popela
Three parts a disk with inner holes and two cylinders with thin-wall web of 0.325 mm and 1.625 mm were produced by Selective laser melting technology from a copper alloy Cu7.2Ni1.8Si1Cr powder. Based on the previous experience with this copper material, the fabrication was successfully processed with up to 5 % dimensional accuracy according to CAD model. The fabricated samples were tested in an experimental thermo-vacuum chamber to reveal the material thermal conductivity since no data are freely available. Based on the reference samples testing, the evaluation process was upgraded by considering a heat transfer by radiation. The measured thermal conductivity of the SLM produced alloy Cu7.2Ni1.8Si1Cr was 3.4 times lower than the value of a bulk material AMPCOLOY 944 with a similar chemical composition.
{"title":"Thermal conductivity of Cu7.2Ni1.8Si1Cr copper alloy produced via SLM and ability of thin-wall structure fabrication","authors":"J. Mašek, D. Koutný, R. Popela","doi":"10.13164/CONF.READ.2018.12","DOIUrl":"https://doi.org/10.13164/CONF.READ.2018.12","url":null,"abstract":"Three parts a disk with inner holes and two cylinders with thin-wall web of 0.325 mm and 1.625 mm were produced by Selective laser melting technology from a copper alloy Cu7.2Ni1.8Si1Cr powder. Based on the previous experience with this copper material, the fabrication was successfully processed with up to 5 % dimensional accuracy according to CAD model. The fabricated samples were tested in an experimental thermo-vacuum chamber to reveal the material thermal conductivity since no data are freely available. Based on the reference samples testing, the evaluation process was upgraded by considering a heat transfer by radiation. The measured thermal conductivity of the SLM produced alloy Cu7.2Ni1.8Si1Cr was 3.4 times lower than the value of a bulk material AMPCOLOY 944 with a similar chemical composition.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"23 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":"133721486","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: 10.13164/CONF.READ.2018.11
A. Kwiek
A blended learning is a method which combines a few teaching methods. Usually it is a mix of classic teaching approach with using of online tools. A Nearpod is technology enhanced learning (TEL) tool which allows for creating an interactive presentation which can be delivered in a real time session or in a self-paced mode. The presentation can be displayed on a student’s computer or mobile phone. This paper presents how students experience can be enhanced by the implementation of a blended learning in aircraft design lectures. And how a Nearpod can be integrated into those lectures to help students develop such skills as creativity, critical thinking and problem solving, which are vital for aircraft design project and students’ further career in the aerospace sector. This study focuses on aeronautical students studying at the University of Brighton in School of Computing Engineering and Mathematics. Students group includes BEng., MEng. and BSc. Top-Up students who were enrolled in level 6 module ME351 Aircraft Design and Management Project. Results reveal that students' attendance is higher than traditional lectures and the most favorite and helpful activities are quizzes & polls, draw it and fill blanks. Aerospace engineering students prefer Nearpod activities where they can choose an answer or draw it rather than writing it.
{"title":"Teaching aircraft design through a blended learning method in a higher education","authors":"A. Kwiek","doi":"10.13164/CONF.READ.2018.11","DOIUrl":"https://doi.org/10.13164/CONF.READ.2018.11","url":null,"abstract":"A blended learning is a method which combines a few teaching methods. Usually it is a mix of classic teaching approach with using of online tools. A Nearpod is technology enhanced learning (TEL) tool which allows for creating an interactive presentation which can be delivered in a real time session or in a self-paced mode. The presentation can be displayed on a student’s computer or mobile phone. This paper presents how students experience can be enhanced by the implementation of a blended learning in aircraft design lectures. And how a Nearpod can be integrated into those lectures to help students develop such skills as creativity, critical thinking and problem solving, which are vital for aircraft design project and students’ further career in the aerospace sector. This study focuses on aeronautical students studying at the University of Brighton in School of Computing Engineering and Mathematics. Students group includes BEng., MEng. and BSc. Top-Up students who were enrolled in level 6 module ME351 Aircraft Design and Management Project. Results reveal that students' attendance is higher than traditional lectures and the most favorite and helpful activities are quizzes & polls, draw it and fill blanks. Aerospace engineering students prefer Nearpod activities where they can choose an answer or draw it rather than writing it.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"33 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":"127545873","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: 10.13164/conf.read.2018.17
Jan Šplíchal, J. Hlinka
This paper is focused on Structural Health Monitoring (SHM) for aerospace use. It analyses the performance of commercially available finite element (FE) software packages for the simulation of propagation of ultrasonic guided waves (UGW) in typical aerospace structures. The purpose of the research is to support activities leading to the introduction of UGW based health monitoring on aerospace structures, as well as to support the design of future structures with integrated health monitoring. Activities are demonstrated on panels with growing complexity (adding different materials, sensors, damage types etc.). FE simulations are used to identify “detection areas” of UGW sensors. This output can be directly applied to the design of future aerospace structures with an integrated SHM system (to ensure the proper planning of the placement of UGW sensors).
{"title":"Modelling of health monitoring signals and detection areas for aerospace structures","authors":"Jan Šplíchal, J. Hlinka","doi":"10.13164/conf.read.2018.17","DOIUrl":"https://doi.org/10.13164/conf.read.2018.17","url":null,"abstract":"This paper is focused on Structural Health Monitoring (SHM) for aerospace use. It analyses the performance of commercially available finite element (FE) software packages for the simulation of propagation of ultrasonic guided waves (UGW) in typical aerospace structures. The purpose of the research is to support activities leading to the introduction of UGW based health monitoring on aerospace structures, as well as to support the design of future structures with integrated health monitoring. Activities are demonstrated on panels with growing complexity (adding different materials, sensors, damage types etc.). FE simulations are used to identify “detection areas” of UGW sensors. This output can be directly applied to the design of future aerospace structures with an integrated SHM system (to ensure the proper planning of the placement of UGW sensors).","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"1 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":"115836697","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: 10.13164/conf.read.2018.3
M. Šplíchal
{"title":"Reduction in the pilot’s stress during the landing maneuver by providing accurate height information","authors":"M. Šplíchal","doi":"10.13164/conf.read.2018.3","DOIUrl":"https://doi.org/10.13164/conf.read.2018.3","url":null,"abstract":"","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"13 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":"124322195","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: 10.13164/CONF.READ.2018.14
M. Cervenka, Rostislav Koštial
This report describes optimisation method for designing sensoric layout for Active Structural Health Monitoring (A-SHM) by Ultrasonic Guided Waves (UGW) on metal and non-metal (composite) materials. The SHM sensors need to be placed optimally in order to detect structural damage with hight probability before the damage turns critical. Configuration of used optimisation algorithm for such task is not straightforward. Differential Evolution (DE) has two configuration parameters – the mutation factor F and the crossover rate CR – whose settings largely influence the solution quality the optimisation process can yield. For that matter we describe an elaborated a method to guide this selection towards good results using visual heat maps with the intent to select best DE’s variant and particular configuration to receive the most optimal SHM sensorics layout.
{"title":"Layout optimisation method for active structural health monitoring","authors":"M. Cervenka, Rostislav Koštial","doi":"10.13164/CONF.READ.2018.14","DOIUrl":"https://doi.org/10.13164/CONF.READ.2018.14","url":null,"abstract":"This report describes optimisation method for designing sensoric layout for Active Structural Health Monitoring (A-SHM) by Ultrasonic Guided Waves (UGW) on metal and non-metal (composite) materials. The SHM sensors need to be placed optimally in order to detect structural damage with hight probability before the damage turns critical. Configuration of used optimisation algorithm for such task is not straightforward. Differential Evolution (DE) has two configuration parameters – the mutation factor F and the crossover rate CR – whose settings largely influence the solution quality the optimisation process can yield. For that matter we describe an elaborated a method to guide this selection towards good results using visual heat maps with the intent to select best DE’s variant and particular configuration to receive the most optimal SHM sensorics layout.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"63 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":"122855599","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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