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Presently, aerial photography remains a popular method for surveillance of landscapes, and its uses continually grow as it is used to monitor trends in areas such as plant distribution and urban construction. The use of computer vision, or more specifically stereo vision, is one common method of gathering this information. By mounting a stereo vision system on the wings of an unmanned aircraft it becomes very useful tool. This technique however, becomes less accurate as stereo vision baselines become longer, aircraft wing spans are increased, and aircraft wings become increasingly flexible. Typically, ideal stereo vision systems involve stationary cameras with parallel fields of view. For an operational aircraft with a stereo vision system installed, stationary cameras can not be expected because the aircraft will experience random atmospheric turbulence in the form of gusts that will excite the dominate frequencies of the aircraft. A method of stereo image rectification has been developed for cases where cameras that will be allowed to deflect on the wings of an fixed wing aircraft that is subjected to random excitation. The process begins by developing a dynamic model the estimates the behavior of a flexible stereo vision system and corrects images collected at maximum deflection. Testing of this method was performed on a flexible stereo vision system subjected to resonance excitation where a reduction in stereo vision distance error is shown. Successful demonstration of this ability is then repeated on a flying wing aircraft by the using a modal survey to understand its behavior. Finally, the flying wing aircraft is subjected to random excitation and a least square fit of the random excitation signal is used to determine points of maximum deflection suitable for stereo image rectification. Using the same techniques for image rectification in resonance excitation, significant reductions in stereo distance errors are shown. / Master of Science

学位授与大学：京都大学 ; 取得学位: 博士(工学) ; 学位授与年月日: 2007-09-25 ; 学位の種類: 新制・課程博士 ; 学位記番号: 工博第2843号 ; 請求記号: 新制/工/1418 ; 整理番号: 25528 / The unsteady buffeting forces and the gust response prediction of bridges in the atmospheric turbulent flows is recently attracted more attention due to uncertainties in both experiment and analytical theory. The correction functions such as the aerodynamic admittance function and the spatial coherence function have been supplemented to cope with limitations of the quasi-steady theory and strip one so far. Concretely, so-called single-variate quasi-steady aerodynamic admittance functions as the transfer functions between the wind turbulence and induced buffeting forces, as well as coherence of wind turbulence has been widely applied for the gust response prediction. Recent literatures, however, pointed out that the coherence of force exhibits higher than that of turbulence. These correction functions, in the other words, contain their uncertainties which are required to be more understanding. Proper orthogonal decomposition (POD), known as the Karhunen-Loeve decomposition has been applied popularly in many engineering fields. Main advantage of the POD is that the multi-variate correlated random fields/processes can be decomposed and described in such simplified way as a combination of limited number of orthogonally low-order dominant eigenvectors (or turbulent modes) which is convenient and applicable for order-reduced representation, simulation of the random fields/processes such as the turbulent fields, turbulent-induced force fields and stochastic response prediction as well. The POD and its proper transformations based on either zero-time-lag covariance matrix or cross spectral one of random fields/processes have been branched by either the covariance proper transformation (CPT) in the time domain or the spectral proper transformation (SPT) in the frequency domain. So far, the covariance matrix-based POD and its covariance proper transformation in the time domain has been used almost in the wind engineering topics due to its simplification in computation and interpretation. In this research, the unsteady buffeting forces and the gust response prediction of bridges with emphasis on the POD applications have been discussed. Investigations on the admittance function of turbulent-induced buffeting forces and the coherence one of the surface pressure as well as the spatial distribution and correlation of the unsteady pressure fields around some typically rectangular cylinders in the different unsteady flows have been carried out thanks to physical measurements in the wind tunnel. This research indicated effect of the bluff body flow and the wind-structure interaction on the higher coherence of buffeting forces than the coherence of turbulence, thus this effect should be accounted and undated for recent empirical formulae of the coherence function of the unsteady buffeting forces. Especially, the multi-variate nonlinear aerodynamic admittance function has been proposed in this research, as well as the temporo-spectral structure of the coherence functions of the wind turbulence and the buffeting forces has been firstly here using the wavelet transform-based coherence in order to detect intermittent characteristics and temporal correspondence of these coherence functions. In POD applications, three potential topics in the wind engineering field have been discussed in the research: (i) analysis and identification, modeling of unsteady pressure fields around model sections; (ii) representation and simulation of multi-variate correlated turbulent fields and (iii) stochastic response prediction of structures and bridges. Especially, both POD branches and their proper transformations in the time domain and the frequency one have been used in these applications. It found from these studies that only few low-order orthogonal dominant modes are enough accuracy for representing, modeling, simulating the correlated random fields (turbulence and unsteady surface pressure, unsteady buffeting forces), as well as predicting stochastic response of bridges in the time and frequency domains. The gust response prediction of bridges has been formulated in the time domain at the first time in this research using the covariance matrix-based POD and its covariance proper transformation which is very promising to solve the problems of the nonlinear and unsteady aerodynamics. Furthermore, the physical linkage between these low-order modes and physical causes occurring on physical models has been interpreted in some investigated cases. / Kyoto University (京都大学) / 0048 / 新制・課程博士 / 博士(工学) / 甲第13372号 / 工博第2843号 / 新制||工||1418(附属図書館) / 25528 / UT51-2007-Q773 / 京都大学大学院工学研究科社会基盤工学専攻 / (主査)教授 松本 勝, 教授 河井 宏允, 准教授 白土 博通 / 学位規則第4条第1項該当

Orientador: Douglas Domingues Bueno / Resumo: Os fenômenos associados aos sistemas aeroelásticos definem uma importante classe de problemas envolvida no projeto de aeronaves. Algumas análises podem ser realizadas utilizando a formulação no domínio da frequência, porém, para alguns problemas específicos a análise no domínio do tempo mostra-se mais conveniente, especialmente para projeto de controladores e inclusão de não linearidades. Em particular, forças aerodinâmicas não estacionárias são tipicamente obtidas no domínio da frequência reduzida. Tais formulações não permitem de maneira direta, através de uma transformada inversa, obter modelos matemáticos no domínio do tempo e, portanto, é necessário o uso de um método de aproximação, como o de Roger-Abel. No entanto, uso deste método de aproximação apresenta algumas lacunas com relação ao significado físico e escolha dos parâmetros de atraso. Desta forma, o presente texto explora a influência dos estados de atraso demonstrando que é responsável pela correção da fase entre o movimento e as forças aerodinâmicas resultantes e, também, propõe uma forma de avaliação da qualidade da aproximação obtida. A partir da aproximação das cargas aerodinâmicas se obtém o modelo matemático do sistema aeroelástico, e através de simulações numéricas computacionais, tem-se a resposta do sistema aeroelástico no domínio do tempo devido à cargas de rajada $1-cosseno$. A partir da análise da resposta à rajada é possível avaliar condições em que a rajada se apresenta de maneira mais crítica para... (Resumo completo, clicar acesso eletrônico abaixo) / Abstract: The phenomena associated with the aeroelastic systems define an important class of problems involved in aircraft design. Some analyzes may be performed in the frequency domain, however, for some specific problems time domain analysis is more convenient, especially for controller design and the inclusion of nonlinearities. In particular, non-stationary aerodynamic forces are typically obtained in the reduced frequency domain. Such formulations do not allow, by means of an inverse transform, to obtain mathematical models in the time domain, and therefore it is necessary to use an approximation method, such as that of Roger-Abel. However, the use of this approximation method presents some gaps with respect to the physical meaning and choice of lag parameters. In this way, the present text explores the influence of the lag states demonstrating that it is responsible for the correction of the phase between the movement and the resulting aerodynamic forces and also proposes a method to evaluate the quality of the approximation achieved. From the approximation of the aerodynamic loads the mathematical model of the aeroelastic system is obtained, and through computational numerical simulations, has the response of the aeroelastic system in the time domain due to the 1-cosine gust load. From the analysis of the response to the gust, it is possible to evaluate conditions in which the gust is presented in a more critical way for the study system. / Mestre