yes / Welcome to the 16th edition of the Advances in Model-Based Testing Workshop (A-MOST 2020) held on March 23rd, 2020 in Porto as part of ICST 2020, the IEEE International Conference on Software Testing, Verification and Validation.

Typescript (photocopy). / Digitized by Kansas Correctional Industries / Department: Computer Science.

A validation methodology is proposed for natural language software specifications of standard graphics functions. Checks are made for consistency, completeness and lack of ambiguity in data element and function descriptions. Functions and data elements are maintained in a relational database representation. The appropriate checks are performed by sequences of database operations. The relational database manager INGRES was used to support a prototype implementation of the proposed technique. / The methodology supports the development of a scenario-based prototype from the information available in the specification. This permits various function sequences to be checked without implementation of the environment specified. / The application of a prototype implementation of the proposed methodology, to the specification of the GKS software package, demonstrates the practicability of the method. Several inconsistencies in GKS, related to the definition of data elements, have been identified.

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Development of unmanned vehicles will increase as the need to save lives rises. In both military and civilian applications, humans can be taken out of the loop through the implementation of safe and intelligent autonomous vehicles. Although hardware and software development continue to play a large role in the autonomous vehicle industry, validation of these systems will always be necessary. The ability to test these vehicles thoroughly and efficiently will ensure their proper and flawless operation. On November 3, 2007 the Defense Advanced Research Projects Agency held the Urban Challenge to drive the development of autonomous ground vehicles for military use. This event required vehicles built by teams across the world to autonomously navigate a 60 mile course in an urban environment in less than 6 hours. This thesis addresses the testing aspect of autonomous ground vehicles that exhibit the advanced behaviors necessary for operating in such an event. Specifically, the experiences of Team Victor Tango and other Urban Challenge teams are covered in detail. Testing facilities, safety measures, procedures, and validation methods utilized by these teams provide valuable information on the development of their vehicles. Combining all these aspects results in a proposed testing strategy for autonomous ground vehicles. / Master of Science

<p>Several programs exist today for calculating aerodynamic coefficients that with some simplificationsprovide fast approximations of the values for a real aircraft.Four different programs were analyzed for this report: Tornado, AVL, PANAIR and a handbook-typepreliminary method. In addition, ANSYS CFX was used for airfoil validation. For calculation of the zerolift drag, an approximation was computed in order to calculate the remaining values that were notcalculated by the software: drag contribution for fuselages, nacelles and some horizontal stabilizersand fins.Different types of aircraft were selected for trial: two commercial aircraft (Boeing 747-100 and 777-300), a TF-8A research airplane (with area rule application: some additions were made to the fuselageto prevent large variations in the cross-section when the contribution of the wing is added), a LockheedConstellation C-69 used as a military cargo airplane, a Boeing Stratocruiser used by the USAF withtwo configurations (basic and bomber), and an Aero Commander 680 Super, similar to a Cessna 162.Two airfoils (NACA2412, 0012) were also analyzed, to investigate the limitations of software designedfor three-dimensional calculations.The accuracy of the results showed that the validity of the software depends on the planform of theaircraft, as well as the simulation parameters Mach number and Reynolds number. The shape of thewing caused some of the methods to have serious difficulties in converging to valid results, orincreased the simulation time beyond acceptable limits.</p> / <p>Numera finns det olika program för beräkning av de aerodynamiska koefficienterna från en modellmed vissa förenklingar som ger en snabb approximation av värdena för ett verkligt flygplan.Fyra olika program har analyserats för denna rapport: Tornado, AVL, PANAIR och en handbokbaserad preliminär metod. Dessutom användes ANSYS CFX för validering av vingprofiler . Vidberäkningen av noll-lyft motståndet, en approximation användes för de återstående delarna som inteberäknas av de andra metoderna: motståndsbidraget från flygkroppar, gondoler och vissa horisontellastabilisatorer och fenor.Olika flygplaner har testats: två trafikflygplan (Boeing 747-100 och 777-300), ett TF-8Aforskningsflygplan (med area regel användning: några tillägg gjordes på flygkroppen för att tvärsnitteninte har stora variationer när bidraget från vingen läggas), ett Lockheed Constellation C-69, ett BoeingStratocruiser som används av USAF i två konfigurationer (den vanliga och bombplan), och ett AeroCommander 680 Super, som liknar ett Cessna 162. Två vingprofiler (NACA 2412, 0012) analyseradesockså, för att kontrollera begränsningarna av programmen avsedd för tredimensionella beräkningar.Riktigheten av resultaten visade att giltigheten av programmen beror på formen av flygplanernasvingar, samt de simulationernas parametrar: Mach nummer och Reynolds nummer. Formen på vingenorsakade några av de metoderna att ha stora svårigheter med konvergensen till giltiga resultat, ellerökat simulering tid över acceptabla gränser.</p>

Several programs exist today for calculating aerodynamic coefficients that with some simplificationsprovide fast approximations of the values for a real aircraft.Four different programs were analyzed for this report: Tornado, AVL, PANAIR and a handbook-typepreliminary method. In addition, ANSYS CFX was used for airfoil validation. For calculation of the zerolift drag, an approximation was computed in order to calculate the remaining values that were notcalculated by the software: drag contribution for fuselages, nacelles and some horizontal stabilizersand fins.Different types of aircraft were selected for trial: two commercial aircraft (Boeing 747-100 and 777-300), a TF-8A research airplane (with area rule application: some additions were made to the fuselageto prevent large variations in the cross-section when the contribution of the wing is added), a LockheedConstellation C-69 used as a military cargo airplane, a Boeing Stratocruiser used by the USAF withtwo configurations (basic and bomber), and an Aero Commander 680 Super, similar to a Cessna 162.Two airfoils (NACA2412, 0012) were also analyzed, to investigate the limitations of software designedfor three-dimensional calculations.The accuracy of the results showed that the validity of the software depends on the planform of theaircraft, as well as the simulation parameters Mach number and Reynolds number. The shape of thewing caused some of the methods to have serious difficulties in converging to valid results, orincreased the simulation time beyond acceptable limits. / Numera finns det olika program för beräkning av de aerodynamiska koefficienterna från en modellmed vissa förenklingar som ger en snabb approximation av värdena för ett verkligt flygplan.Fyra olika program har analyserats för denna rapport: Tornado, AVL, PANAIR och en handbokbaserad preliminär metod. Dessutom användes ANSYS CFX för validering av vingprofiler . Vidberäkningen av noll-lyft motståndet, en approximation användes för de återstående delarna som inteberäknas av de andra metoderna: motståndsbidraget från flygkroppar, gondoler och vissa horisontellastabilisatorer och fenor.Olika flygplaner har testats: två trafikflygplan (Boeing 747-100 och 777-300), ett TF-8Aforskningsflygplan (med area regel användning: några tillägg gjordes på flygkroppen för att tvärsnitteninte har stora variationer när bidraget från vingen läggas), ett Lockheed Constellation C-69, ett BoeingStratocruiser som används av USAF i två konfigurationer (den vanliga och bombplan), och ett AeroCommander 680 Super, som liknar ett Cessna 162. Två vingprofiler (NACA 2412, 0012) analyseradesockså, för att kontrollera begränsningarna av programmen avsedd för tredimensionella beräkningar.Riktigheten av resultaten visade att giltigheten av programmen beror på formen av flygplanernasvingar, samt de simulationernas parametrar: Mach nummer och Reynolds nummer. Formen på vingenorsakade några av de metoderna att ha stora svårigheter med konvergensen till giltiga resultat, ellerökat simulering tid över acceptabla gränser.

At Ball State University Dr. Wayne Zage and Professor Dolores Zage are working on a Design metrics project to develop a metrics approach for analyzing software design.The purpose of this thesis is to test the hypotheses of this metric by calculating the De external design component, and to show the correlation of errors and stress points in the design phase for a large Ada Software, professionally developed at Computer Sciences Corporation.From these studies we can relatively conclude that De does indicate the error-prone module. Since the D(G) is comprised of an internal and external component it is necessary to evaluate Di to support this hypothesis on a large project. Just by viewing the external complexity, the metric does a relatively good job of pointing out high error modules, with only viewing 10% of the modules we found 33% of the errors.Comparing the results of STANFINS-R and the results of the BSU projects, the BSU projects did better in finding the errors 33% verus 53%. However in the STANFINS project, we had a better success rate of finding the error modules. Of the modules highlighted 72% did contain errors. Thus if we loosened the criteria for selection of error prone modules we might have had a large percentage of the errors captured. / Department of Computer Science

Orientador: Manuel de Jesus Mendes / Dissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia eletrica e de Computação / Made available in DSpace on 2018-08-04T07:59:18Z (GMT). No. of bitstreams: 1 Damasceno_LucianoLanca_M.pdf: 3606058 bytes, checksum: 6c7876317b16dec5e767a2941f0c8211 (MD5) Previous issue date: 2005 / Resumo: A popularização da Internet criou expectativas e promessas quanto ao uso mais inteligente dos dados disponíveis, culminando na necessidade de interoperabilidade entre aplicações. O uso de padrões de metadados comuns, descrevendo a semântica dos sistemas e suas capacidades possibilitaram a interoperabilidade entre sistemas de informações distribuídos. No entanto, a incompatibilidade entre metamodelos exige uma arquitetura de metadados que suporte esta diversidade. Meta-Object Facility (MOF) é um padrão aberto, suportando e definindo diferentes tipos de metamodelos. Um formato comum de intercâmbio de metadados independente de middleware era necessário, XML Metadata Interchange (XMI) foi especificado como resposta a esta necessidade. Esta dissertação apresenta um sistema de repositório de metadados e metamodelos baseados em MOF, possuindo ferramentas de suporte para validação dos metadados intercambiados através de XMI e visualização de metadados e metamodelos MOF. Com o objetivo de validar o sistema, o resultado deste trabalho foi aplicado em uma iniciativa de governo eletrônico. Ambientes de tecnologia de informação governamentais se destacam pela heterogeneidade, complexidade e pela forte presença de soluções adaptadas para as diferentes unidades administrativas / Abstract: The increase of Internet popularity creates hopes and promises as the use of available data becomes more intelligent, culminating in the need of interoperability among applications. The use of common metadata standards, describing the semantics and capabilities of the systems, enables interoperability of distributed information systems. However, metamodels incompatibility demands a metadata architecture that supports this diversity. Meta Object Facility (MOF) is an open standard, supporting and defining different kinds of metamodels. Furthermore, it was necessary a common metadata interchange format independent of middleware. XMI was specified as an answer to this need. This dissertation presents a MOF metadata repository system, having support tools to validate the interchanged metadata and to visualize the stored metamodels and metadata. In order to validate the system; the result of this work was applied in an electronic government initiative. Information technology of governmental environments is cleared by the heterogeneity, complexity, and strong presence of the adjusted solutions to the different administrative units / Mestrado / Engenharia de Computação / Mestre em Engenharia Elétrica