Os simuladores de vôo têm sido uma importante ferramenta para treinamento de pilotos e análise de vôo sem ter que se desembolsar grandes quantias monetárias, economizando combustível e evitando acidentes. Conseqüentemente, a demanda por simuladores de vôo tem aumentado tanto na indústria quanto na pesquisa. Com o intuito de futuramente construir um simulador de vôo, foi desenvolvido um projeto para elaboração de um software capaz de simular uma aeronave em vôo, do ponto de vista de dinâmica de vôo. O software SIMAERO foi desenvolvido na linguagem de programação C++ e simula a dinâmica de vôo de uma aeronave. Esta simulação consiste em resolver as equações de movimento da aeronave, utilizando o modelo matemático de equações diferenciais ordinárias proposto por ETKIN & REID, et al (1996). O modelo matemático é solucionado através do método de integração numérica Runge-Kutta de 4ª ordem conforme apresentado em CONTE (1977). Como parâmetros de entrada são informadas as seguintes características da aeronave: dados geométricos, dados aerodinâmicos e derivadas de estabilidade. Os resultados das simulações são apresentados em gráficos cartesianos e gravados em arquivos. Os gráficos são úteis para que possa ser feita uma posterior análise do comportamento da aeronave. Os arquivos gravados com os resultados das simulações podem ser utilizados em alguma aplicação futura, como sinas de entrada para uma plataforma de simulação, por exemplo. Neste trabalho será descrito como o SIMAERO foi desenvolvido e ao final serão apresentados alguns resultados obtidos. / Flight simulators have been an important tool for pilots training and for flight analyses, without having to spend a high quantity of money, saving gas and prevent accidents. Because of this, the demand for flight simulators has increased both in industry and in research centers. With the objective of in future build a flight simulator, a project to develop a software that is able to simulate the dynamics of flight of a flying aircraft was developed. The SIMAERO software was developed using C++ and its principal functionality is to simulate the dynamics of flight of an aircraft. This simulation basically is the solution of the system of motion equations of the aircraft, using the mathematical model described by ETKIN & REID, et al (1996). The mathematical model is solved using the 4th order Runge-Kutta numeric integration method, as presented in CONTE (1977). For the simulation, the geometric data, the aerodynamic data, and the dimensional derivates are passed to the software as input arguments. The results of the simulations are displayed as cartesians graphics and recorded as data files. The graphics are useful for visual analyses of the aircraft behavior, and the file, with the results of the simulation, can be used as input data for ground based simulator, for example. In this work, the development of the software SIMAERO will be presented, and then some results of the simulation of one aircraft will be shown.

La thèse porte sur l'étude de générateurs utilisant un cerf-volant pour capter l'énergie éolienne. Ces systèmes permettent de générer de l'énergie éolienne sans avoir besoin de construire les pylônes et les fondations étant nécessaires pour construire une éoliennes classiques.Ces systèmes on commencé à être étudiés il y a une dizaine d'années, une vingtaine d'entreprises et à peu près autant d'universités étudient le problème. Il existe plusieurs types de générateurs étudiés mais jusqu'ici, aucun système n'a démontré que son concept est économiquement viable.La grande variété de systèmes étant étudiés fait penser aux débuts de l'aviation, ou toutes sortes de concepts ont été testés. Il a fallu environ 50 ans de développements de prototypes entre 1870 et 1910 pour que le principe de fonctionnement des avions se standardise autour de celui qui est est encore utilisé aujourd'hui. Pendant cette période, un grand nombre de concepts ont été testés et beaucoup d'erreurs ont étés faites au niveau de la conception du modèle, des techniques expérimentales utilisées et du management des projet.Les systèmes étudiés de génération d'énergie utilisant des cerf-volants tentent répondre à un même cahier des charges d'une vingtaine de façons différentes. Ceci fait penser que le concept de génération d'énergie n'a pas trouvé un principe de fonctionnement optimal et qu'il n'en est qu'à une phase de prospection de concepts.En cela, le récent essor des générateurs cerf-volants ressemble beaucoup au débuts de l'aviation. Nous avons donc cherché à comprendre les erreurs ayant été faites lors des débuts de l'aviation pour essayer de mieux comprendre les erreurs qui pourraient être faites avec les systèmes de générateurs cerf-volants.Cette étude a permis de fixer quelques règles de travail qui ont servi pour développer les prototypes mis au point pendant de thèse.Une soufflerie à été construite pour tester dans des environnements restreints plusieurs modèles de cerf-volants. Plusieurs objectifs ont été atteints pendant la thèse, entre autres le contrôle de la puissance générée par un cerf-volant volant en présence de rafales de vent et l'étude d'un plan de vol permettant au cerf-volant de rester en vol sans vent et sans utiliser d'énergie embarquée.Au total, 13 prototypes ont été mis au point pendant cette thèse, un brevet est en cours de dépôt et une entreprise utilisant les résultats de la thèse est en train d'être créée. / The PhD focuses on the study of electric generators using a kite to capture wind energy. These systems generate wind energy without having to build the towers and foundations are needed to build conventional wind turbines.These systems started being studied around ten years ago, twenty companies and nearly as many universities are studying the problem. There are several types of generators studied, but so far, none has demonstrated that the concept is economically viable.The variety of systems being studied is reminiscent of early aviation, because many kinds of different concepts were tested. It took about 50 years of development of prototypes between 1870 and 1910 for the principle of operation of aircraft got standardized around one that is still used today. During this period, a large number of concepts have been tested and many mistakes have made ​​on the model design, the experimental techniques and on the management of the project.The nowadays studied kite power systems tries to answer to the same specifications by around twenty different ways. This suggests that the concept of power generation has not yet found an optimal principle of functioning and that it is only at a phase of concepts exploration.The recent surge of kite power systems reminds of the early days of aviation. We sought to understand the mistakes that were made ​​during the early days of aviation to try to understand the mistakes that could be made with modern kite power systems.This study has set some guidelines that were used for developing the prototypes built during thesis .A wind tunnel was built for testing in simplified environments several models of kites. Several objectives were achieved during the thesis, including the control of the power generated by a kite flying in the presence of wind gusts and the study of a flight plan allowing the kite to stay in flight without wind and without the use of embedded energy.A total of 13 prototypes were developed during this thesis, a patent is being filed and a company using the results of the thesis is being created.

Os simuladores de vôo têm sido uma importante ferramenta para treinamento de pilotos e análise de vôo sem ter que se desembolsar grandes quantias monetárias, economizando combustível e evitando acidentes. Conseqüentemente, a demanda por simuladores de vôo tem aumentado tanto na indústria quanto na pesquisa. Com o intuito de futuramente construir um simulador de vôo, foi desenvolvido um projeto para elaboração de um software capaz de simular uma aeronave em vôo, do ponto de vista de dinâmica de vôo. O software SIMAERO foi desenvolvido na linguagem de programação C++ e simula a dinâmica de vôo de uma aeronave. Esta simulação consiste em resolver as equações de movimento da aeronave, utilizando o modelo matemático de equações diferenciais ordinárias proposto por ETKIN & REID, et al (1996). O modelo matemático é solucionado através do método de integração numérica Runge-Kutta de 4ª ordem conforme apresentado em CONTE (1977). Como parâmetros de entrada são informadas as seguintes características da aeronave: dados geométricos, dados aerodinâmicos e derivadas de estabilidade. Os resultados das simulações são apresentados em gráficos cartesianos e gravados em arquivos. Os gráficos são úteis para que possa ser feita uma posterior análise do comportamento da aeronave. Os arquivos gravados com os resultados das simulações podem ser utilizados em alguma aplicação futura, como sinas de entrada para uma plataforma de simulação, por exemplo. Neste trabalho será descrito como o SIMAERO foi desenvolvido e ao final serão apresentados alguns resultados obtidos. / Flight simulators have been an important tool for pilots training and for flight analyses, without having to spend a high quantity of money, saving gas and prevent accidents. Because of this, the demand for flight simulators has increased both in industry and in research centers. With the objective of in future build a flight simulator, a project to develop a software that is able to simulate the dynamics of flight of a flying aircraft was developed. The SIMAERO software was developed using C++ and its principal functionality is to simulate the dynamics of flight of an aircraft. This simulation basically is the solution of the system of motion equations of the aircraft, using the mathematical model described by ETKIN & REID, et al (1996). The mathematical model is solved using the 4th order Runge-Kutta numeric integration method, as presented in CONTE (1977). For the simulation, the geometric data, the aerodynamic data, and the dimensional derivates are passed to the software as input arguments. The results of the simulations are displayed as cartesians graphics and recorded as data files. The graphics are useful for visual analyses of the aircraft behavior, and the file, with the results of the simulation, can be used as input data for ground based simulator, for example. In this work, the development of the software SIMAERO will be presented, and then some results of the simulation of one aircraft will be shown.

This thesis researches dynamics in projects managed by Scrumban. It describes the creation of system dynamics simulation model, which provides insight into the relationships between system components. It also presents data, that are further analysed with the purpose of discovering patterns in behaviour of project attributes in time, such as size of the product backlog, work in progress etc. The patterns are discovered and recommended parameter settings are provided so that there is no idle time or higher defect rate than necessary. Soft factors are also included in the model, namely the development team and the customer, which have a grand effect to the model behaviour. Managment flight simulator is developed, which provides the option to experiment even to users, who are not familiar with system dynamics modelling. The thesis consists of two parts. In the first part, necessary theory of project management, system dynamics and their fusion is provided. The second part is dedicated to the process of creating the simulation model, dynamic hypothesis formulation, mathematical modelling, testing and data analysis. In consideration of the analysis results, recommended policies are provided. Last pages of the thesis describe the user interface of management flight simulator and it's controls.

There has been almost fifteen years of political controversy surrounding changes to the rules and procedures by which aircraft conduct their flight within regional Australia. Decisions based on a predominately heuristic (rule of thumb) approach to design have had many adverse consequences for the integrity of the proximity warning function. A sound mathematical model is required to establish this function on a mature engineering foundation. To achieve this, the proximity warning function has been investigated as a hybrid-system. This approach recognises the dual nature of the design: that aircraft dynamics give rise to continuous mathematical models while the communication protocols controlling proximity require discrete mathematical approaches. The blending of each aspect has yielded a deeper insight into the operational limitations and failure modes of this function. The presentation of the thesis follows a design thread through the function. It begins with a description of existing standards and implementations. Risk models are then developed. The pilot interface is recognised as a primary design constraint. Mathematical models are then developed to describe the topology of flow, proximity dynamics, and the scheduling constraints associated with visual, voice, and data-link communications required by the proximity warning function. These analyses show that many aspects of design can be bounded by analytical formulae that bring new robustness to the design and resolve some of the misconceptions arising from the often inaccurate perceptions of present airspace operations. Failure modes, unaccounted for in existing designs are found to actually aggravate failure in the very situations in which the airspace design should be robust and should act to prevent collisions. In particular, there are divergences of performance between the demands required by the system design and the ability of the pilot to deliver such performances. In some cases, these failures may be traced to policy decisions such as service between Instrument Flight Rule and Visual Flight Rule category aircraft. On the basis of the conclusions of this research, a formal engineering review of the proximity warning function is required to assure the containment of the likelihood of mid-air collision for all future operations.