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.2018.13
Jiří Matějů
This paper shows simple method to simulate nonlinear longitudinal flight dynamic of an aircraft in the most direct way. The method is based on physical principles of an analytical-empiric flight dynamics. Non-linearity, as stall or thrust dependent on velocity, can be included. Static and dynamic stability derivatives are not required but can be computed as an output. The model is applicable for various aircraft conceptions. Higher level model, for example, based on flight tests data, can be modified by low-level analytical methods, e.g. for modification of horizontal tail area. No special simulation software is necessary. The model is compared to linear model and flight test experiment. This model, together with valuable analytical-empiric data, might be applied for fast flight dynamic computations. Model is easily accessible and understandable even with basic knowledge of flight dynamic and computer programming. The main application of the method is conceptual design when high precision is not expected, even if VLM, CFD or flight test data can improve the precision.
{"title":"Simple universal nonlinear longitudinal flight simulation with avoiding of static and dynamic stability derivatives","authors":"Jiří Matějů","doi":"10.13164/conf.read.2018.13","DOIUrl":"https://doi.org/10.13164/conf.read.2018.13","url":null,"abstract":"This paper shows simple method to simulate nonlinear longitudinal flight dynamic of an aircraft in the most direct way. The method is based on physical principles of an analytical-empiric flight dynamics. Non-linearity, as stall or thrust dependent on velocity, can be included. Static and dynamic stability derivatives are not required but can be computed as an output. The model is applicable for various aircraft conceptions. Higher level model, for example, based on flight tests data, can be modified by low-level analytical methods, e.g. for modification of horizontal tail area. No special simulation software is necessary. The model is compared to linear model and flight test experiment. This model, together with valuable analytical-empiric data, might be applied for fast flight dynamic computations. Model is easily accessible and understandable even with basic knowledge of flight dynamic and computer programming. The main application of the method is conceptual design when high precision is not expected, even if VLM, CFD or flight test data can improve the precision.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"68 4","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114034437","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.2018.1
R. Doubrava, M. Oberthor, J. Raška, P. Bělský, K. Doubrava, M. Dvořák
,
，
{"title":"Verification and numerical simulation of advanced composite inlet in compliance of airworthiness impact requirements","authors":"R. Doubrava, M. Oberthor, J. Raška, P. Bělský, K. Doubrava, M. Dvořák","doi":"10.13164/conf.read.2018.1","DOIUrl":"https://doi.org/10.13164/conf.read.2018.1","url":null,"abstract":",","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"34 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":"121877110","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.2018.6
Pratik Meghani
This paper investigates the potential of modifications in the NACA 2412 aerofoil’s geometry which could be implemented as a morphing wing in the Cessna 172SP. A 2D study on three morphing configurations: landing, take-off and stall maneuvering was conducted. The new geometries were designed using XFLR5. The initial aerodynamics characteristics were computed using XFOIL and compared to that of NACA 2412 in the Cessna 172SP. A selected configuration (landing) was tested at the University of Brighton wind tunnel facility, in comparison to XFOIL predictions. Moreover, the ESDU 07010 report was used to extrapolate the Reynold’s number to full scale, which was necessary to obtain an approximation of the aerodynamic characteristics at actual flight. The paper presents results of ANSYS FLUENT simulations for all three configurations. Results reveal that XFOIL is suitable for morphing airfoil configuration analysis but only at low Reynolds number (Re≈500,000). Adaptive aerofoil geometry improves the lift to drag (L/D) ratio by decreasing the drag coefficient; it also expands the flight envelope by delaying stall.
{"title":"A 2d aerodynamic study on morphing of the naca 2412 aerofoil","authors":"Pratik Meghani","doi":"10.13164/conf.read.2018.6","DOIUrl":"https://doi.org/10.13164/conf.read.2018.6","url":null,"abstract":"This paper investigates the potential of modifications in the NACA 2412 aerofoil’s geometry which could be implemented as a morphing wing in the Cessna 172SP. A 2D study on three morphing configurations: landing, take-off and stall maneuvering was conducted. The new geometries were designed using XFLR5. The initial aerodynamics characteristics were computed using XFOIL and compared to that of NACA 2412 in the Cessna 172SP. A selected configuration (landing) was tested at the University of Brighton wind tunnel facility, in comparison to XFOIL predictions. Moreover, the ESDU 07010 report was used to extrapolate the Reynold’s number to full scale, which was necessary to obtain an approximation of the aerodynamic characteristics at actual flight. The paper presents results of ANSYS FLUENT simulations for all three configurations. Results reveal that XFOIL is suitable for morphing airfoil configuration analysis but only at low Reynolds number (Re≈500,000). Adaptive aerofoil geometry improves the lift to drag (L/D) ratio by decreasing the drag coefficient; it also expands the flight envelope by delaying stall.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"6 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":"130079922","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.2018.4
J. Hlinka, Rostislav Koštial, Luboš Janhuba
This paper presents integrated algorithm for airborne system safety and reliability assessment. In general aviation (mostly up to EASA CS-23) and non-military unmanned aerial vehicles industry, safety and reliability assessment process still relays almost exclusively on human judgment. Recommended practices define processes for system modelling and safety assessing are based on analyst understanding of a particular system. That is difficult and time-consuming process. Commercial computation aids are extremely expensive with restricted (or closed) access to the solution algorithms. Together with this problem, rapid development of modern airborne systems, their increasing complexity, elevates level of interconnection. Therefore, safety and reliability analyses have to continuously evolve and adapt to the extending complexity. Growing expansion brings in the field of unnamed aerial vehicles systems which consist of items without relevant reliability testing. Presented algorithm utilizes graph theory and fuzzy logic in order to develop integrated computerized mean for reliability analysis of sophisticated, highly interconnected airborne systems. Through the usage of graph theory, it is possible to create model of particular systems and its sub-systems in the form of universal data structure. Algorithm is conceived as fuzzy expert system, that emulates decision making of a human expert. That brings opportunity to partially quantify system attributes and criticality. Criticality evaluation increases level of assessment correlation with real state of system and its attributes.
{"title":"Integrated method utilizing graph theory and fuzzy logic for safety and reliability assessment of airborne systems","authors":"J. Hlinka, Rostislav Koštial, Luboš Janhuba","doi":"10.13164/CONF.READ.2018.4","DOIUrl":"https://doi.org/10.13164/CONF.READ.2018.4","url":null,"abstract":"This paper presents integrated algorithm for airborne system safety and reliability assessment. In general aviation (mostly up to EASA CS-23) and non-military unmanned aerial vehicles industry, safety and reliability assessment process still relays almost exclusively on human judgment. Recommended practices define processes for system modelling and safety assessing are based on analyst understanding of a particular system. That is difficult and time-consuming process. Commercial computation aids are extremely expensive with restricted (or closed) access to the solution algorithms. Together with this problem, rapid development of modern airborne systems, their increasing complexity, elevates level of interconnection. Therefore, safety and reliability analyses have to continuously evolve and adapt to the extending complexity. Growing expansion brings in the field of unnamed aerial vehicles systems which consist of items without relevant reliability testing. Presented algorithm utilizes graph theory and fuzzy logic in order to develop integrated computerized mean for reliability analysis of sophisticated, highly interconnected airborne systems. Through the usage of graph theory, it is possible to create model of particular systems and its sub-systems in the form of universal data structure. Algorithm is conceived as fuzzy expert system, that emulates decision making of a human expert. That brings opportunity to partially quantify system attributes and criticality. Criticality evaluation increases level of assessment correlation with real state of system and its attributes.","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"71 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":"127313222","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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