In this study, a variable pitch axial flow fan is designed and analysed for Ankara Wind Tunnel (AWT). In order to determine the loss caharacteristics of AWT, an algorithm is developed and the results are validated. Also some pressure and velocity measurements are made at the fan section to find the losses experimentally. After completion of the fan design, analyses are made at different volumetric flowrates and blade angles including the design point and the performance characteristics of the fan are obtained and thereafter the operating range of the tunnel is deterimened.

Made available in DSpace on 2016-04-28T14:16:37Z (GMT). No. of bitstreams: 1 Vivian Scatolin.pdf: 24058709 bytes, checksum: 0c9438735be0e55834207c2a48b9c41e (MD5) Previous issue date: 2008-10-21 / The establishment of the aerospace science in Brazil is the subject of this investigation under the perspective of Science History. Mainly by analyzing official documents and legislation, we search for the ideas and concepts that guided the actions in three distinct moments: when Casimiro Montenegro Filho created the Aeronautics Technological Institute in the 1940 decade, known by the nationalism of the Vargas era; on the research efforts that permitted the foundation of the aircraft maker Embraer during the development-oriented decade of 1950 and the beginning of the Brazilian military dictatorship; and in the elaboration of the Brazilian space program, between the dictatorial regime and re-democratization. It starts from the hypothesis that the factor which led to the wellsucceeded nowadays performance of the country on building aircraft was the adoption of a model based on the tripod science teaching research industrial production. Meanwhile, in the space sector, internal difficulties and others imposed by international circumstances impede the goals of the Brazilian Complete Space Mission from being fully achieved. The relevancy of this work relies on the understanding that aviation and the reaching of space constitute state projects for the national modernization / A institucionalização da ciência aeroespacial no Brasil é o objeto desta investigação sob a perspectiva da história da ciência. Por meio da análise principalmente de documentos oficiais e da legislação, procurou-se apreender as concepções presentes em três momentos distintos: quando da criação, por Casimiro Montenegro Filho, do Instituto Tecnológico de Aeronáutica na década de 1940, marcada pelo nacionalismo da Era Vargas; no esforço de pesquisa que propiciou a fundação da Embraer durante o desenvolvimentismo da década de 1950 e o início da ditadura militar, e na formulação do programa espacial brasileiro, entre o regime ditatorial e a redemocratização. Parte-se da hipótese de que o fator que levou ao atual bem sucedido desempenho do país na fabricação de aeronaves foi a aplicação de um modelo baseado no tripé ensino de ciência pesquisa produção industrial. Enquanto isso, no setor espacial, dificuldades internas e impostas pelo contexto internacional impedem que os objetivos da Missão Espacial Completa Brasileira sejam plenamente alcançados. A relevância deste trabalho reside na compreensão de que a aviação e o acesso ao espaço constituem projetos do Estado para a modernização nacional

The nonlinear simulation model of an unmanned aerial vehicle (UAV) in MATLAB&reg / /Simulink&reg / environment is developed by taking into consideration all the possible major system components such as actuators, gravity, engine, atmosphere, wind-turbulence models, as well as the aerodynamics components in the 6 DOF equations of motion. Trim and linearization of the developed nonlinear model are accomplished and various related analyses are carried out. The model is validated by comparing with a similar UAV data in terms of open loop dynamic stability characteristics. Using two main approaches / namely, classical and optimal, linear controllers are designed. For the classical approach, Simulink Response Optimization (SRO) tool of MATLAB&reg / /Simulink&reg / is utilized, whereas for the optimal controller approach, linear quadratic (LQ) controller design method is implemented, again by the help of the tools put forth by MATLAB&reg / . The controllers are designed for control of roll, heading, coordinated turn, flight path, pitch, altitude, and airspeed, i.e., for the achievement of all low-level control functions. These linear controllers are integrated into the nonlinear model, by carrying out gain scheduling with respect to airspeed and altitude, controller input linearization regarding the perturbed states and control inputs, and anti integral wind-up scheme regarding the possible wind-up of the integrators in the controller structures. The responses of the nonlinear model controlled with the two controllers are compared based on the military flight control requirements. The advantages and disadvantages of these two frequently used controllers in industry are investigated and discussed. These results are to be evaluated by the designers themselves based on the design criteria of a project that is worked on.

This thesis describes the development of a series of codes for trim and longitudinal stability analysis of a helicopter in forward flight. In general, particular use of these codes can be made for parametric investigation of the effects of the external and internal systems integrated to UH-60 helicopters. However, in this thesis the trim analysis results are obtained for a clean UH-60 configuration and the results are compared with the flight test data that were acquired by ASELSAN, Inc. The first of the developed trim codes, called TRIM-CF, is based on closedform equations which give the opportunity of having quick results. The second code stems from the trim code of Prouty. That code is modified and improved during the course of this study based on the theories outlined in [3], and the resultant code is named TRIM-BE. These two trim codes are verified by solving the trim conditions of the example helicopter of [3]. Since it is simpler and requires fewer input parameters, it is more often more convenient to use the TRIM-CF code. This code is also verified by analyzing the Bo105 helicopter with the specifications given in [2]. The results are compared with the Helisim results and flight test data given in this reference. The trim analysis results of UH-60 helicopter are obtained by the TRIM-CF code and compared with flight test data. A forward flight longitudinal dynamic stability code, called DYNA-STAB, is also developed in the thesis. This code also uses the methods presented in [3]. It solves the longitudinal part of the whole coupled matrix of equations of motion of a helicopter in forward flight. The coupling is eliminated by linearization. The trim analysis results are used as inputs to the dynamic stability code and the dynamic stability characteristics of a forward flight trim case of the example helicopter [3] are analyzed. The forward flight stability code is applied to UH-60 helicopter. The codes are easily applicable to a helicopter equipped with external stores. The application procedures are also explained in this thesis.

Engineers have long been inspired by nature's flyers. Such animals navigate complex environments gracefully and efficiently by using a variety of evolutionary adaptations for high-performance flight. Biologists have discovered a variety of sensory adaptations that provide flow state feedback and allow flying animals to feel their way through flight. A specialized skeletal wing structure and plethora of robust, adaptable sensory systems together allow nature's flyers to adapt to myriad flight conditions and regimes. In this work, motivated by biology and the successes of bio-inspired, engineered aerial vehicles, linear quadratic control of a flexible, morphing wing design is investigated, helping to pave the way for truly autonomous, mission-adaptive craft. The proposed control algorithm is demonstrated to morph a wing into desired positions. Furthermore, motivated specifically by the sensory adaptations organisms possess, this work transitions to an investigation of aircraft wing load identification using structural response as measured by distributed sensors. A novel, recursive estimation algorithm is utilized to recursively solve the inverse problem of load identification, providing both wing structural and aerodynamic states for use in a feedback control, mission-adaptive framework. The recursive load identification algorithm is demonstrated to provide accurate load estimate in both simulation and experiment. / Graduation date: 2012