Currently, it is uncertain how well a typical ground-based simulator's hexapod motion system can simulate the aggressive motion during airplane upset. To address this issue, this thesis attempts to improve simulator motion for upset recovery simulation by defining new motion fidelity criteria, implementing body frame filtering, and improving an existing adaptive motion drive algorithm. The successfully improved adaptive algorithm was used to conduct a paired comparison experiment to study the effects of trade-offs between translational and rotational motion cues on pilot subjective fidelity and upset recovery performance. Analysis of the experimental data found that pilots generally rejected motion with false lateral cues and they preferred the presence of rotational cues for moderate roll angles. Also, performance analysis suggested that roll cues helped improve lateral control. Overall, pilots preferred to have simulator motion during upset simulation and significant improvements in performance were observed when simulator motion was present.

Thesis (M.S.)--University of Tennessee, Knoxville, 2004. / Title from title page screen (viewed Sept. 27, 2004). Thesis advisor: R.B. Richards. Document formatted into pages (xi, 83 p. : ill. (some col.)). Vita. Includes bibliographical references (p. 63-65).

Die globale Erwärmung als auch neue Regularien und Richtlinien zwingen die Flugzeughersteller und die Fluggesellschaften ihre Emissionen über den kompletten Life-Cycle einen Flugzeuges zu reduzieren. Über den Life-Cycle eines Flugzeuges gesehen, fallen während der Nutzungsphase eines Flugzeuges mit 98% CO2 die meisten Emissionen an (Airbus Operations GmbH 2009). Dementsprechend stellt die Nutzungsphase den größten Hebel dar, um eine deutliche Senkung der Emissionen umzusetzen. Nach dem Advisory Council for Aeronautics in Europe (ACARE) lässt sich eine Reduktion der Emissionen während der Nutzungsphase vorzugsweise durch aerodynamische Verbesserungen, eine Gewichtsreduktion, neue Flugzeugkonzepte und eine erhöhte Kapazität innerhalb der Flugzeugkabine umsetzen (ACARE 2002). [... aus dem Text]

Timely identifying flight diversions is a crucial aspect of efficient multi-modal transportation. When an airplane diverts, logistics providers must promptly adapt their transportation plans in order to ensure proper delivery despite such an unexpected event. In practice, the different parties in a logistics chain do not exchange real-time information related to flights. This calls for a means to detect diversions that just requires publicly available data, thus being independent of the communication between different parties. The dependence on public data results in a challenge to detect anomalous behavior without knowing the planned flight trajectory. Our work addresses this challenge by introducing a prediction model that just requires information on an airplane's position, velocity, and intended destination. This information is used to distinguish between regular and anomalous behavior. When an airplane displays anomalous behavior for an extended period of time, the model predicts a diversion. A quantitative evaluation shows that this approach is able to detect diverting airplanes with excellent precision and recall even without knowing planned trajectories as required by related research. By utilizing the proposed prediction model, logistics companies gain a significant amount of response time for these cases.

Os passageiros têm reclamado da diminuição do conforto na classe econômica dos aviões comerciais. A autoridade aeronáutica brasileira instituiu um selo de qualidade, mas as empresas aéreas brasileiras mantêm os mesmos arranjos internos em seus aviões. Estadissertaçãotrata da avaliação do espaço entre as poltronas e a sua influência no conforto dos passageiros em vôos comerciais. Realizaram-se avaliações da usabilidade utilizando-se um simulador de cabine para treinamento de tripulantes e um avião B737-300. Os resultados indicam uma forte relação entre os níveis de conforto e o passo (medida de repetição das fileiras de poltronas ao longo do avião). / Passengers have complained about reduction on economy class comfort levels on commercial airplanes. The Brazilian Aeronautical Authority has instituted a quality seal, but the airlines maintain the same interior layouts in their airplanes. This dissertation is about the evaluation of the space between seats and its influence in passengers comfort on commercial flights. Usability evaluations have been carried out in a cabin simulator for airline crew training and a B737-300 airplane. The results show a strong connection between the comfort levels and the seat pitch (distance separating seat rows along the airplane).

Os passageiros têm reclamado da diminuição do conforto na classe econômica dos aviões comerciais. A autoridade aeronáutica brasileira instituiu um selo de qualidade, mas as empresas aéreas brasileiras mantêm os mesmos arranjos internos em seus aviões. Estadissertaçãotrata da avaliação do espaço entre as poltronas e a sua influência no conforto dos passageiros em vôos comerciais. Realizaram-se avaliações da usabilidade utilizando-se um simulador de cabine para treinamento de tripulantes e um avião B737-300. Os resultados indicam uma forte relação entre os níveis de conforto e o passo (medida de repetição das fileiras de poltronas ao longo do avião). / Passengers have complained about reduction on economy class comfort levels on commercial airplanes. The Brazilian Aeronautical Authority has instituted a quality seal, but the airlines maintain the same interior layouts in their airplanes. This dissertation is about the evaluation of the space between seats and its influence in passengers comfort on commercial flights. Usability evaluations have been carried out in a cabin simulator for airline crew training and a B737-300 airplane. The results show a strong connection between the comfort levels and the seat pitch (distance separating seat rows along the airplane).

Orientador: Kamal Abdel Radi Ismail / Dissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecânica / Made available in DSpace on 2018-08-18T00:17:32Z (GMT). No. of bitstreams: 1 Matsuo_CarolinaAkemiSepulveda_M.pdf: 9560878 bytes, checksum: cc02ac79665887e2f83f47e4a06e3d8c (MD5) Previous issue date: 2011 / Resumo: Os Veículos Aéreos Não Tripulados (VANT's) possuem uma variedade de aplicações, seja monitoramento de incêndios florestais, linhas de energia, tráfego, aglomerações humanas, como também ser usado de alvo aéreo em aplicações militares. Mesmo que ainda seja um pouco restrita à aplicação civil por falta de regulamentação, tais veículos estão sendo desenvolvidos e estudados em âmbito acadêmico. A particularidade deste trabalho é o desenvolvimento de um Veículo Aéreo Não Tripulado para o uso em pulverização aeroagrícola visando reduzir os riscos de operação de vôo tripulado agrícola. Dessa maneira, é apresentada a metodologia usada para desenvolver o projeto, descrevendo o procedimento utilizado para determinar a razão peso-potência e carga alar, e as características geométricas do VANT. Os cálculos da aerodinâmica, desempenho e da estabilidade longitudinal estática do veículo são feitos analiticamente, sendo que na etapa de projeto aerodinâmico, é feita a otimização do aerofólio NACA 4415, e calculado os parâmetros aerodinâmicos do veículo completo. Além disso, por ser não tripulado, é feita a seleção do Sistema de Controle de Vôo de forma a atender os requisitos da missão. Nos cálculos do projeto são usadas as normas técnicas de homologação como a RBHA (Requisitos Brasileiros de Homologação de Aeronaves) a qual remetem às principais normas internacionais: FAR (Federal Aircraft Regulation), dos Estados Unidos da América, e a norma JAR (Joint Airworthiness Regulation). Por ser utilizado na pulverização de defensivos agrícolas é apresentada a tecnologia de aplicação dos mesmos utilizados em aeronaves tripuladas, e feito a escolha do sistema de pulverização para o veículo / Abstract: The Unmanned Aerial Vehicles (UAV's) have a variety of applications, wether monitoring of forest fires, power lines, traffic, crowds, but also can be used for aerial target military applications. Even though it is still somewhat restrict to civil application because of lack of regulation, such vehicles are being developed and studied in the academic sphere. The particularity of this work is the development of an Unmanned Aerial Vehicle for use in aerial spraying to reduce the risks of manned agricultural operation. Thus, It is presented the methodology used to determine the thrust to weight ratio and wing loading, and geometric characteristics of the UAV. Analytical calculus of aerodynamic and vehicle performance are made, and in the step aerodynamic design is made the optimization of the airfoil NACA 4415 and calculated the aerodynamic parameters of the whole vehicle. Moreover, being unmanned, it is made the selection of the Flight Control System to attend mission requirements. Technical standards for approval are used to design calculations as the RBHA (Brazilian Requirements for Approval of Aircraft) wich refer to the main international standards: FAR (Federal Aviation Regulation) of United States of America, and JAR (Joint Airworthiness Regulation).Whereas is used in the spraying of pesticides, it is presented the technology of application used in manned aircraft, and the choice of the spray system for vehicle / Mestrado / Termica e Fluidos / Mestre em Engenharia Mecânica

O modelo de avaliação da camada limite dinâmica e térmica foi implementado, no presente trabalho, em um código numérico para o cálculo do coeficiente de transferência de calor convectivo sobre aerofólios de uso aeronáutico com formação de gelo. Foram considerados, no modelo da camada limite turbulenta, os efeitos da rugosidade equivalente do grão de areia ks, e transição entre o regime laminar e turbulento foi avaliada por dois modelos, um abrupto e um suave. Para a transição suave foi utilizada uma função intermitência proposta por (ABU-GHANNAM; SHAW, 1980). O código desenvolvido neste trabalho foi acoplado aos módulos do código ONERA com o objetivo de simular as formas de gelo em aerofólios para diversas condições de escoamento do ar com conteúdo de água. As formas de gelo obtidas foram comparadas com dados experimentais de Shine Bond (1994) e com resultados de simulações dos códigos LEWICE, TRAJICE e ONERA (KIND, 2001). Os resultados das simulações do presente trabalho apresentaram boa semelhança com os resultados dos outros códigos. A simulação da previsão de formas de gelo do tipo Glaze, do presente trabalho e dos outros códigos, resultou em formas de gelo de espessura e volume menores que as formas experimentais. Foi verificado que uma previsão adequada do coeficiente de transferência de calor convectivo afeta a simulação das formas deste tipo de gelo. Um caso de Kind (2001) foi utilizado para avaliar os efeitos dos parâmetros da camada limite dinâmica e térmica na formação de gelo em aerofólios. Verificou-se que a posição do início da transição do regime laminar para o turbulento, o comprimento d a transição e o valor da rugosidade afetam a forma, a espessura e o volume do gelo, e que estes parâmetros podem ser utilizados para ajustes dos modelos de camada limite para melhores previsões de formas de gelo do tipo Glaze. / The model to evaluate the momentum and thermal boundary layer was implemented, in the present work, in a numerical module to calculate the convective heat transfer coecient over aeronautical airfoils with ice accretion. It was considered, in the turbulent boundary layer model, the eects of the equivalent sand grain roughness ks , and the laminar to turbulent transition was evaluated with two models, the abrupt and the smooth one. The smooth transition model used an intermittency function proposed by (ABU-GHANNAM; SHAW, 1980). The module developed in this work was integrated with the modules of the code ONERA in order to simulate the airfoil icing shapes for several air stream with water droplets condition. The ice shapes obtained was compared with experimental data of Shin e Bond (1994) and with simulation results for the codes LEWICE, TRAJICE e ONERA (KIND, 2001). The results of the simulations for the present work showed a good similarity with the other codes results. The Glaze icing shapes simulation, in the present work and in the other codes, resulted in icing shapes with thickness and volumes lesser than the experimental shapes. It was noted that a reasonable prediction of the convective heat transfer coecient aects the simulation of this type of ice shape. One case of Kind (2001) was used to evaluate the eects of the momentum and thermal boundary layer for the icing accreations in the airfoil. It was noted the onset position, the lenght of the laminar-turbulent transition, and the sand grain roughness value aects the icing shape, thickness and volume and this parameters might be used to adjust the boundary layer models in order to get better predictions of Glaze icing shapes.

The purpose of this study is to make an analysis of the extent of the airplane industry in the immediate area of Fort Worth, Texas, to determine the need, if any, of adding a course in Airplane Industry to the curriculum of the Technical High School of Fort Worth, Texas.

This diploma thesis deals with a design of single-engine, multi-purpose, transport airplane in Normal category, given by CS/FAR 23. Design is created in highest constructional and technological accordance with L 410 airplane series. Thesis determines airplanes conceptual layout, basic dimensions, basic weight and center of gravity analysis, aerodynamic and aerostatic foundation, flight performances and airplane properties. Thesis arranges various versions of cabin layouts and describes power plant installation and landing gear construction. Results of the thesis shows, that this design is advantageous in various aspects. Design is comparable with competition from perspective of its performances. Financial analysis showed, that costs of development are returnable in relatively low amount of sold airplanes, for a prices, that are lower than a prices, competition is selling similar airplanes for. Moreover, costs of maintenance are expected to be low, as a consequence of using only one engine unit.