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}
Pub Date : 1900-01-01DOI: 10.13164/CONF.READ.2018.15
P. Deák, Michał Kowalik
The main goal was to establish results of the individual joint strength characteristics used in composite laminate structure, in order to be used for design computations in airframe structures. A carbon-epoxy composite specimen includes a brass sleeve that is used to connect other metal parts by a bolt, used on light-weight category aircrafts. 11 specimens were tested and pulled by a tensile test machine. The tension mechanisms associated with failure modes of bolted joints in advanced composites is explained. The work is based on experimental test observations, performed by Instron 8516 servo-hydraulic testing machine and analyzed further by Digital Image Correlation (DIC) technique to define failure load of this metal-composite interconnection. Comparison of DIC results is made in parallel with test recorded data as verification. Conclusions include a failure analysis and observations learned during the experiment.
{"title":"Composite aircraft joint experimental testing with digital image correlation","authors":"P. Deák, Michał Kowalik","doi":"10.13164/CONF.READ.2018.15","DOIUrl":"https://doi.org/10.13164/CONF.READ.2018.15","url":null,"abstract":"The main goal was to establish results of the individual joint strength characteristics used in composite laminate structure, in order to be used for design computations in airframe structures. A carbon-epoxy composite specimen includes a brass sleeve that is used to connect other metal parts by a bolt, used on light-weight category aircrafts. 11 specimens were tested and pulled by a tensile test machine. The tension mechanisms associated with failure modes of bolted joints in advanced composites is explained. The work is based on experimental test observations, performed by Instron 8516 servo-hydraulic testing machine and analyzed further by Digital Image Correlation (DIC) technique to define failure load of this metal-composite interconnection. Comparison of DIC results is made in parallel with test recorded data as verification. Conclusions include a failure analysis and observations learned during the experiment.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"21 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":"120984441","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.2018.5
M. Pontecorvo
: Currently, a research team in the University of Brighton, in collaboration with the European Space Agency (ESA), is developing a pulsating heat pipe that will eventually be launched and tested in space, with the International Space Station (ISS) as destination, for research into passive thermal devices and their behaviour in a vacuum. The approved pulsating heat pipe design incorporates one titanium plate, which is classified as a metal, and one aluminum-oxide sapphire plate that is classified as a ceramic. At the moment, the team is faced with the challenge of bonding the two plates together since, using convectional manufacturing methods, the parts fail due to the high level of induced stress. A research into manufacturing processes to bond together titanium and sapphire is essential to ensure that the final device will operate for several weeks (maybe even months) without leaking and the need for maintenance. The project explores potential manufacturing processes aimed to bond together these materials and subsequently propose a solution. Furthermore, static and thermal analyses are carried out with the aid of SolidWorks to exploit potential points of failure due to stress concentrations induced by cooling after bonding. The results indicate that both titanium and sapphire are capable of sustaining the induced stresses but, due to the complex geometry of the pulsating heat pipe at the contact surface, the bonding agent is likely to fail due to the induced stresses.
{"title":"Design of manufacturing simulations of a flatplate pulsating heat pipe","authors":"M. Pontecorvo","doi":"10.13164/conf.read.2018.5","DOIUrl":"https://doi.org/10.13164/conf.read.2018.5","url":null,"abstract":": Currently, a research team in the University of Brighton, in collaboration with the European Space Agency (ESA), is developing a pulsating heat pipe that will eventually be launched and tested in space, with the International Space Station (ISS) as destination, for research into passive thermal devices and their behaviour in a vacuum. The approved pulsating heat pipe design incorporates one titanium plate, which is classified as a metal, and one aluminum-oxide sapphire plate that is classified as a ceramic. At the moment, the team is faced with the challenge of bonding the two plates together since, using convectional manufacturing methods, the parts fail due to the high level of induced stress. A research into manufacturing processes to bond together titanium and sapphire is essential to ensure that the final device will operate for several weeks (maybe even months) without leaking and the need for maintenance. The project explores potential manufacturing processes aimed to bond together these materials and subsequently propose a solution. Furthermore, static and thermal analyses are carried out with the aid of SolidWorks to exploit potential points of failure due to stress concentrations induced by cooling after bonding. The results indicate that both titanium and sapphire are capable of sustaining the induced stresses but, due to the complex geometry of the pulsating heat pipe at the contact surface, the bonding agent is likely to fail due to the induced stresses.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"10 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":"134206635","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.2018.8
P. Kaľavský, R. Rozenberg, P. Petríček, V. Socha, L. Socha
The article deals with the issue of alternative ways of extraction and insertion of persons by helicopters using rope and non-rope procedures. The article provides a current general overview of rope and non-rope procedures for insertion of persons in places where a helicopter cannot touch down, as well as an overview of techniques used for extraction/transport of persons from places not permitting helicopter touchdown. The article lists advantages and disadvantages of individual methods and their applicability in the helicopter emergency medical service. The main contribution of the article is the comparison of time indicators when inserting and transporting persons by helicopters with the use of rope procedures during typical model situations. For the purposes of comparing rope procedures have been created three typical model situations for inserting two persons from a hovering helicopter and two typical model situations for extracting four persons and their transportation on board. During creating these model situations, we have taken into consideration the most frequently used rope procedures within HEMS in civil, military and police sectors of the Slovak Republic. Total insertion/extraction time was considered the basic piece of data for the comparison. Time data were obtained from flight tests, actual training, technical documentation data and on the basis of the expert estimate. Rope procedures were compared among each other and among three types of helicopters most used for these purposes in the Slovak Republic: Mi-17 LPZS, Bell-429 and AGUSTA A109K2. Processed conclusions from the comparison of each model situation within the considered alternative rope ways of extraction and insertion of persons by helicopters and the conclusions drawn from the performance comparison of HEMS helicopters in the Slovak Republic within these model situations are a significant contribution to the determination of procedures in the framework of rescue missions.
{"title":"Rope procedures for extraction and insertion of persons used by helicopter emergency medical service","authors":"P. Kaľavský, R. Rozenberg, P. Petríček, V. Socha, L. Socha","doi":"10.13164/CONF.READ.2018.8","DOIUrl":"https://doi.org/10.13164/CONF.READ.2018.8","url":null,"abstract":"The article deals with the issue of alternative ways of extraction and insertion of persons by helicopters using rope and non-rope procedures. The article provides a current general overview of rope and non-rope procedures for insertion of persons in places where a helicopter cannot touch down, as well as an overview of techniques used for extraction/transport of persons from places not permitting helicopter touchdown. The article lists advantages and disadvantages of individual methods and their applicability in the helicopter emergency medical service. The main contribution of the article is the comparison of time indicators when inserting and transporting persons by helicopters with the use of rope procedures during typical model situations. For the purposes of comparing rope procedures have been created three typical model situations for inserting two persons from a hovering helicopter and two typical model situations for extracting four persons and their transportation on board. During creating these model situations, we have taken into consideration the most frequently used rope procedures within HEMS in civil, military and police sectors of the Slovak Republic. Total insertion/extraction time was considered the basic piece of data for the comparison. Time data were obtained from flight tests, actual training, technical documentation data and on the basis of the expert estimate. Rope procedures were compared among each other and among three types of helicopters most used for these purposes in the Slovak Republic: Mi-17 LPZS, Bell-429 and AGUSTA A109K2. Processed conclusions from the comparison of each model situation within the considered alternative rope ways of extraction and insertion of persons by helicopters and the conclusions drawn from the performance comparison of HEMS helicopters in the Slovak Republic within these model situations are a significant contribution to the determination of procedures in the framework of rescue missions.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"39 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":"131609332","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.2018.18
Karel Třetina, T. Cäsar
{"title":"Diagnostic parameters determination of aircraft hydraulic system","authors":"Karel Třetina, T. Cäsar","doi":"10.13164/CONF.READ.2018.18","DOIUrl":"https://doi.org/10.13164/CONF.READ.2018.18","url":null,"abstract":"","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"217 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":"115590065","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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