Tensegrity is the name given to a system of interconnected bars and tendons that can form a flexible self-standing structure. Its flexibility is due to the ability of the bars to move near-independent to each other, movement that can be caused by controlled tension forces in the tendons or external forces such as gravity. However, a balance of sorts must be maintained - if a tendon were to go slack, the entire structure could become unstable and collapse on itself. This thesis looks at placing a tensegrity structure in orbit around the Earth. As a spacecraft's orbit is moved further away from the Earth, the strength of the Earth's gravity field lessens. Ideally, such a flexible structure would be placed far enough away from the Earth so that the gravity field would have too weak an impact on its individual elements to cause major distortions. However, the author recognizes that altitudes below 2,000 km, where the Earth's gravity field is still very prevalent, are the most common altitudes used by orbiting spacecraft today. The goal of this thesis is to analyze the distortions of the tensegrity structure at these lower altitudes, and also look at methods for controlling these distortions. / Ph. D.

Northern Sweden is one of the largest hosts for mineral resources in Europe and always has been an interesting area for researchers from various disciplines of Earth sciences. This dissertation is a comprehensive summary of three case study papers on airborne VLF, gravity gradient and magnetic data in the area. In the first paper, tensor VLF data is extracted from an old data set which contains only the total and the vertical magnetic components. The anomalous part of the horizontal magnetic field components is computed by a Hilbert transform of the vertical magnetic field. The normal part of the horizontal magnetic field component is computed as a function of total, vertical and anomalous part of horizontal magnetic fields. The electric field is also calculated for TE mode and impedance tensor and apparent resistivity are computed. In addition tippers are calculated for two transmitters and inverted by a 3D inversion algorithm. Comparison of the estimated model and geology map of bedrock shows that lower resistivity zones are correlated with mineralizations. The second paper deals with the internal consistency of airborne gravity gradient data. The six components of the data are estimated from a common potential function. It is shown that the data is adequately consistent but at shorter land clearances the difference between the estimated data and the original data is larger. The technique is also used for computing the Bouguer anomaly from terrain corrected FTG data. Finally the data is inverted in 3D, which shows that the estimated density model in shallow depth is dominated by short wave length features. Inversion of TMI data is the topic of the third paper where a new type of reference model for 3D inversion of magnetic data is proposed by vertically extending the estimated magnetization of a 2D terrain magnetization model. The final estimated 3D result is compared with the magnetization model where no reference model is used. The comparison shows that using the reference model helps the high magnetization zones in the estimated model at shallow depths to be better correlated with measured high remanent magnetization from rock samples. The high magnetization zones are also correlated with gabbros and volcanic metasediments.

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ExoCube is the latest National Science Foundation (NSF) funded space weather CubeSat and is a collaboration between PolySat, Scientific Solutions Inc. (SSI), the University of Wisconsin, NASA Goddard and SRI International. The 3U will carry a mass spectrometer sensor suite, EXOS, in to low earth orbit (LEO) to measure neutral and ionized particles in the exosphere and thermosphere. Measurements of neutral and ion particles are directly impacted by the angle at which they enter EXOS and which leads to pointing requirements. A combination of a gravity gradient system with a momentum bias wheel is proposed to meet pointing requirements while reducing power requirements and overall system complexity. A MATLAB simulation of dynamic and kinematic behavior of the system in orbit is implemented to guide system design and verify that the pointing requirements will be met. The problem of achieving the required three-axis pointing is broken into four phases: detumbling, initial attitude acquisition, wheel spin-up, and attitude maintenance. Ultimately, this configuration for attitude control in a CubeSat could be applied to many future missions with the simulation serving as a design tool for CubeSat developers.

Made available in DSpace on 2014-06-11T19:25:29Z (GMT). No. of bitstreams: 0 Previous issue date: 2011-07-13Bitstream added on 2014-06-13T19:32:38Z : No. of bitstreams: 1 pereira_aj_me_guara.pdf: 1147049 bytes, checksum: 5c149bbd658e37d0e33085f764c18b50 (MD5) / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / Uma abordagem analítica para o movimento rotacional de satélites artificiais estabilizados por rotação é apresentada, considerando os satélites em órbita elíptica e a influência conjunta do torque aerodinâmico, o torque de gradiente de gravidade, o torque magnético residual e o torque magnético devido às correntes de Foucault. Modelos matemáticos são apresentados para todos os torques e os componentes médios de cada torque são determinados para um período orbital. O torque médio já inclui os principais efeitos de cada torque sobre o movimento rotacional e são necessários nas equações do movimento. As equações do movimento são descritas em termos do módulo da velocidade angular de rotação do satélite, da declinação e da ascensão reta do eixo de rotação do satélite. Uma solução analítica para as equações do movimento rotacional é determinada, considerando os valores do torques externos médios em um período orbital, sendo válida para um período orbital. Por esta solução observa-se que o torque gradiente de gravidade e torque magnético devido às correntes de Foucault afetam o módulo da velocidade angular de rotação, contribuindo também para as variações temporais da ascensão reta e declinação do eixo de rotação, associadas com a precessão e deriva do eixo de rotação do satélite. O torque magnético residual e o torque aerodinâmico afetam apenas a ascensão reta e declinação do eixo de rotação, pois seu componente no eixo z são nulo. Aplicações são realizadas para os Satélites de Coleta de Dados Brasileiros SCD1 e SCD2, através de uma primeira abordagem com atualização diária dos dados de atitude e órbita e uma segunda abordagem sem a atualização diária destes dados. Os resultados mostram uma boa concordância entre os resultados obtidos pela teoria e os dados fornecidos pelo Centro de Controle de... / An analytical approach for the rotational motion of artificial satellites stabilized by rotation is presented, considering the satellites in elliptical orbit and the influence of the aerodynamic torque, gravity gradient torque, residual magnetic torque and magnetic torque due to the Foucault currents. Mathematical models for all the torques are shown and average components of each torque are determined for an orbital period. These components are needed in the equations of rotational motion. The average torque already included the main effects of each torque upon the rotational motion. The equations of rotational motion are described in terms of the satellite’s spin velocity, the declination and right ascension of the spin axis of the satellite. An analytical solution for the equations of the rotational motion is determined, considering mean values in an orbital period for the external torques. This solution is valid for an orbital period. Through this solution, it is noticed that the gravity gradient torque and the magnetic torques affects the spin velocity and the spin axis. The temporal variations of right ascension and declination of the spin axis causes the precession and drift of the spin. The residual magnetic torque and the aerodynamic torque, doesn´t affect the spin velocity because its component at z-axis is null. Applications are made for the Brazilian Data Collection Satellites SCD1 and SCD2, through a first approach with daily updates of the attitude and orbit data, and a second approach without the daily update of these data. The results show a good agreement between the results obtained by theory and data supplied by the Satellite Control Center of INPE in the first approach during 10 days. For the approach without updates, the results prove to be suitable only for 3 days of simulation. To validate the analytical solution, the pointing error (deviation from the rotational... (Complete abstract click electronic access below)

Orientadora: Maria Cecília F. P. S. Zanardi / Banca: Ana Paula Marins Chiaradia / Banca: Sandro da Silva Fernandes / Resumo: Uma abordagem analítica para o movimento rotacional de satélites artificiais estabilizados por rotação é apresentada, considerando os satélites em órbita elíptica e a influência conjunta do torque aerodinâmico, o torque de gradiente de gravidade, o torque magnético residual e o torque magnético devido às correntes de Foucault. Modelos matemáticos são apresentados para todos os torques e os componentes médios de cada torque são determinados para um período orbital. O torque médio já inclui os principais efeitos de cada torque sobre o movimento rotacional e são necessários nas equações do movimento. As equações do movimento são descritas em termos do módulo da velocidade angular de rotação do satélite, da declinação e da ascensão reta do eixo de rotação do satélite. Uma solução analítica para as equações do movimento rotacional é determinada, considerando os valores do torques externos médios em um período orbital, sendo válida para um período orbital. Por esta solução observa-se que o torque gradiente de gravidade e torque magnético devido às correntes de Foucault afetam o módulo da velocidade angular de rotação, contribuindo também para as variações temporais da ascensão reta e declinação do eixo de rotação, associadas com a precessão e deriva do eixo de rotação do satélite. O torque magnético residual e o torque aerodinâmico afetam apenas a ascensão reta e declinação do eixo de rotação, pois seu componente no eixo z são nulo. Aplicações são realizadas para os Satélites de Coleta de Dados Brasileiros SCD1 e SCD2, através de uma primeira abordagem com atualização diária dos dados de atitude e órbita e uma segunda abordagem sem a atualização diária destes dados. Os resultados mostram uma boa concordância entre os resultados obtidos pela teoria e os dados fornecidos pelo Centro de Controle de... (Resumo completo, clicar acesso eletrônico abaixo) / Abstract: An analytical approach for the rotational motion of artificial satellites stabilized by rotation is presented, considering the satellites in elliptical orbit and the influence of the aerodynamic torque, gravity gradient torque, residual magnetic torque and magnetic torque due to the Foucault currents. Mathematical models for all the torques are shown and average components of each torque are determined for an orbital period. These components are needed in the equations of rotational motion. The average torque already included the main effects of each torque upon the rotational motion. The equations of rotational motion are described in terms of the satellite's spin velocity, the declination and right ascension of the spin axis of the satellite. An analytical solution for the equations of the rotational motion is determined, considering mean values in an orbital period for the external torques. This solution is valid for an orbital period. Through this solution, it is noticed that the gravity gradient torque and the magnetic torques affects the spin velocity and the spin axis. The temporal variations of right ascension and declination of the spin axis causes the precession and drift of the spin. The residual magnetic torque and the aerodynamic torque, doesn't affect the spin velocity because its component at z-axis is null. Applications are made for the Brazilian Data Collection Satellites SCD1 and SCD2, through a first approach with daily updates of the attitude and orbit data, and a second approach without the daily update of these data. The results show a good agreement between the results obtained by theory and data supplied by the Satellite Control Center of INPE in the first approach during 10 days. For the approach without updates, the results prove to be suitable only for 3 days of simulation. To validate the analytical solution, the pointing error (deviation from the rotational... (Complete abstract click electronic access below) / Mestre

This master´s thesis deals with the determination of vertical gravity gradient in the shaft below the infantry bunker TS - 73 "Polom" located in village Babí. After performing position, elevation and gravity measurements detailed points, representing the two vertical profiles were calculated gravity, vertical gravity gradient, block densities ang gravity anomalies depending on the depth. Other outputs work as a topographic map and a map of full Bouguer anomalies for the wider area of the location and interpretive geologic profile.

Gravity gradient tensor (GGT) data contains the second derivatives of the Earth’s gravitational potential in three orthogonal directions. GGT data can be measured either using land, airborne, marine or space platforms. In the last two decades, the applications of GGT data in hydrocarbon exploration, mineral exploration and structural geology have increased considerably. This work focuses on developing new interpretation techniques for GGT data as well as pseudo-gravity gradient tensor (PGGT) derived from measured magnetic field. The applications of developed methods are demonstrated on a GGT data set from the Vredefort impact structure, South Africa and a magnetic data set from the Särna area, west central Sweden. The eigenvectors of the symmetric GGT can be used to estimate the position of the causative body as well as its strike direction. For a given measurement point, the eigenvector corresponding to the maximum eigenvalue points approximately toward the center of mass of the source body. For quasi 2D structures, the strike direction of the source can be estimated from the direction of the eigenvectors corresponding to the smallest eigenvalues. The same properties of GGT are valid for the pseudo-gravity gradient tensor (PGGT) derived from magnetic field data assuming that the magnetization direction is known. The analytic signal concept is applied to GGT data in three dimensions. Three analytic signal functions are introduced along x-, y- and z-directions which are called directional analytic signals. The directional analytic signals are homogenous and satisfy Euler’s homogeneity equation. Euler deconvolution of directional analytic signals can be used to locate causative bodies. The structural index of the gravity field is automatically identified from solving three Euler equations derived from the GGT for a set of data points located within a square window with adjustable size. For 2D causative bodies with geometry striking in the y-direction, the measured gxz and gzz components of GGT can be jointly inverted for estimating the parameters of infinite dike and geological contact models. Once the strike direction of 2D causative body is estimated, the measured components can be transformed into the strike coordinate system. The GGT data within a set of square windows for both infinite dike and geological contact models are deconvolved and the best model is chosen based on the smallest data fit error. / Felaktigt tryckt som Digital Comprehensive Summaries of Uppsala Dissertations from the Faculty of Science and Technology 730