This thesis develops methods to identify periodic solutions to the n-body problem by representing gravitational orbits with Fourier series. To find periodic orbits, a minimization function was developed that compares the second derivative of the Fourier series with Newtonian gravitation acceleration and modifies the Fourier coefficients until the orbits match. Software was developed to minimize the function and identify the orbits using gradient descent and quadratic curves. A Newtonian gravitational simulator was developed to read the initial orbit data and numerically simulate the orbits with accurate motion integration, allowing for comparison to the Fourier series orbits and investigation of their stability. The orbits found with the programs correlate with orbits from literature, and a number remain stable when simulated. / February 2016

Satellite networks provide an alternative to terrestrial networks where cost and lack of infrastructure are driving parameters. For a satellite network to be cost effective one needs to be able to increase the efficiency of the network: this is accomplished by focusing on the parameters that affect the performance of the system and improving on them where possible. The factors affecting the network performance include the capacity, the propagation delay, the protocol used, and the channel error rate, among others. There are various ways to implement a satellite network depending on the satellite orbit, the architecture used, the access technique used, the radio interfaces used, etc. This thesis work describes the chosen satellite standard, Digital Video Broadcasting – Return Channel via Satellite (DVB-RCS) and the associated Medium Access Control (MAC) protocols. Two protocols were designed and investigated under ideal channel conditions, these being the Combined Free/Demand Assigned Multiple Access with Piggy Backing – Packet Dropping (CF/DAMA-PB-PD) protocol; and the Combined Free/Demand Assigned Multiple Access with Piggy Backing – Prioritised Earliest Deadline First (CF/DAMA-PB-PEDF) protocol, both derived from the Combined Free/Demand Assigned Multiple Access with Piggy Backing (CF/DAMA-PB) protocol. The multimedia traffic models for voice, video and web classes are described, validated through simulations and presented; these provide the heterogeneous vi traffic required for evaluating the performance of the satellite system implemented and the designed protocols. Under the multimedia traffic, CF/DAMA-PB-PD was shown to excel in average packet delay reduction while reducing the overall system throughput. The CF/DAMA-PB-PEDF does not contribute to an improvement over the CF/DAMA-PB-PD protocol. The effects of a non-ideal channel on the CF/DAMA-PB-PD protocol was investigated and presented along with the design of three MAC protocols that take the channel characteristics into account to improve on the system performance. The cross-layer interactions, more specifically the interaction between the physical and data–link layers, were used, investigated and presented. The channel state information in terms of signal-to-noise ratio (SNR) was used to improve the system performance. The five protocols evaluated under non-ideal channel conditions were the CF/DAMA-PB, CF/DAMA-PB-PD, CF/DAMA-PB-BSNRF, CF/DAMA-PB-DD and the CF/DAMA-PB-BSNRF+DD. The best overall performance, both in average packet delay while maintaining good QoS levels and throughput was shown to be that of the CF/DAMA-PB-DD protocol. / Thesis (M.Sc.Eng.)-University of KwaZulu-Natal, Durban, 2010.

Thesis (Ph. D.)--University of Hawaii at Manoa, 1991. / Includes bibliographical references (leaves 152-154) / Microfiche. / xvi,154 leaves, bound ill. 29 cm

Let G be a compact Lie group and let π be an irreducible representation of G of highest weight λ. We study the operator-valued Fourier transform of the product of the j-function and the pull-back of ?? by the exponential mapping. We show that the set of extremal points of the convex hull of the support of this distribution is the coadjoint orbit through ?? + ??. The singular support is furthermore the union of the coadjoint orbits through ?? + w??, as w runs through the Weyl group. Our methods involve the Weyl functional calculus for noncommuting operators, the Nelson algebra of operants and the geometry of the moment set for a Lie group representation. In particular, we re-obtain the Kirillov-Duflo correspondence for compact Lie groups, independently of character formulae. We also develop a "noncommutative" version of the Kirillov character formula, valid for noncentral trigonometric polynomials. This generalises work of Cazzaniga, 1992.

Paper discusses the expected uncertainty of orbital parameters of binary stars as measured by the space-based gravitational wave observatory LISA (Laser Interferometer Space Antenna) and how the inclusion of spin in the model of the binary stars affects the uncertainty. The uncertainties are found by calculating the received gravitational wave from a binary pair and then performing a linear least-squares parameter estimation. The case of a 1500 solar mass black hole that is 20 years from coalescing with a 1000 solar mass black hole--both of which are 50 x 10^6 light years away--is analyzed, and the results show that the inclusion of spin has a negligible effect upon the angular resolution of LISA but can increase the accuracy in mass and distance measurements by factors of 15 and 65, respectively.

We review the concept of invariant measure and study conditions under which linear combinations of averages along periodic orbits are dense in the space of invariant measures. / Revisamos el concepto de medida invariante y estudiamos condiciones bajo las cuales combinaciones lineales de promedios a lo largo de órbitas periódicas son densas en el espacio de medidas invariantes.

Made available in DSpace on 2015-12-10T14:22:59Z (GMT). No. of bitstreams: 0 Previous issue date: 2015-07-28. Added 1 bitstream(s) on 2015-12-10T14:29:14Z : No. of bitstreams: 1 000852063.pdf: 2040130 bytes, checksum: 458621c7faa04b8c2ac8a4f58adf2130 (MD5) / Neste trabalho, estudamos o problema da viabilidade de missões espaciais em ambiente de detritos espaciais. Geralmente, um veículo espacial em curso de colisão com um detrito espacial é destruído ou danificado e tem sua missão prejudicada. A preservação destas missões depende da capacidade do satélite de evitar a colisão, como por exemplo, através de uma manobra orbital conhecida como manobra evasiva. Neste estudo, estabelecemos estratégias de manobras evasivas realizadas por um satélite através de um sistema de propulsão, cuja eficiência é medida por parâmetros tecnológicos. Os parâmetros tecnológicos são configurados no planejamento da missão, e descrevem a quantidade de combustível a bordo e a capacidade de expelir propelente do sistema de propulsor. As manobras evasivas foram estudadas para serem aplicadas de tal forma que o satélite escape do detrito espacial sem a evasão da sua órbita nominal de missão, e para este objetivo, incluímos uma propulsão de controle e tratamos o sistema de propulsão como uma perturbação na órbita do satélite. Também foi estabelecido, para realizar manobras evasivas econômicas, uma propulsão que é ligada em uma fração do tempo total disponível para a manobra. Esta fração de tempo é definida como um tempo de pulso de propulsão. As manobras evasivas são estudadas por simulações numéricas da dinâmica de um detrito e um veículo espacial sob a ação da força gravitacional da Terra e de perturbações orbitais oriundas de um sistema de propulsão e da atmosfera da Terra. Nestas simulações calculamos as condições de colisão do detrito e do satélite, que ocorrem ao redor da Terra, e utilizamos para criar catálogos de parâmetros tecnológicos acessíveis ao satélite para escapar destas colisões / We studied the problem of the viability of space missions in debris environment space. Generally, a space vehicle in collision course with a space debris is destroyed or damaged and has impaired their mission. The preservation of these missions depends on the satellite capacity to avoid the collision, for example by an orbital maneuver known as evasive maneuver. In this study, we established strategies evasive maneuvers performed by a satellite via a propulsion system, whose efficiency is measured by technological parameters. Technological parameters are set in the planning of the mission, and describe the amount of fuel on board and the ability to expel propellant propulsion system. The evasive maneuvers were studied to be applied in such a way that the satellite escape the space debris without evasion of its nominal orbit mission, and for this purpose, include a propulsion control and treat the propulsion system as a disturbance in the orbit of satellite. It has also been established, to perform evasive maneuvers driven, propulsion which is connected at a fraction of the total time available for the maneuver. This fraction of time is defined as a propulsion pulse time. The evasive maneuvers are studied by numerical simulations of the dynamics of a debris and a vehicle space under the action of the Earth's gravitational and orbital perturbations arising from a propulsion system and the Earth's atmosphere. In these simulations calculate the debris of the collision conditions and the satellite, which occur around the Earth, and used to create technological parameters catalogs accessible to the satellite to escape these collisions

Submitted by DANIEL MARTIN GASLAC GALLARDO (dmgg7900@hotmail.com) on 2016-12-13T16:40:12Z No. of bitstreams: 1 gaslac.pdf: 23986592 bytes, checksum: 41ffd339aeeb8444e4703d37a1753df4 (MD5) / Approved for entry into archive by Felipe Augusto Arakaki (arakaki@reitoria.unesp.br) on 2016-12-20T13:16:25Z (GMT) No. of bitstreams: 1 gallhardo_dmg_me_guara.pdf: 23986592 bytes, checksum: 41ffd339aeeb8444e4703d37a1753df4 (MD5) / Made available in DSpace on 2016-12-20T13:16:25Z (GMT). No. of bitstreams: 1 gallhardo_dmg_me_guara.pdf: 23986592 bytes, checksum: 41ffd339aeeb8444e4703d37a1753df4 (MD5) Previous issue date: 2016-10-11 / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / Os novos dados obtidos do sistema de Plut˜ao, durante sua passagem pelo sistema em julho de 2015, est˜ao sendo enviados pela sonda New Horizons. Plut˜ao possui um conjunto de cinco sat´elites, Caronte (forma um sistema bin´ario com Plut˜ao), Estige, Nix, C´erberos e Hidra. A recente descoberta desses dois pequenos sat´elites, Estige e C´erberos, faz com que seja necess´ario reestudar essa regi˜ao externa, al´em da ´orbita de Caronte. Neste trabalho analisaremos a estabilidade da regi˜ao externa do sistema Plut˜ao-Caronte para um conjunto de part´ıculas-teste da ordem de cent´ımetros e micrometros sob a influˆencia gravitacional de todos os corpos do sistema de Plut˜ao e da press˜ao de radia¸c˜ao solar (para part´ıculas de micrometros). Essas part´ıculas estar˜ao inicialmente em ´orbitas excˆentricas e inclinadas; ser˜ao assumidos diferentes valores de excentricidade e inclina¸c˜ao. Resultados mostraram que para um conjunto de part´ıculas, originalmente localizadas no plano orbital do sistema de Plut˜ao, 10% colidiram com os corpos maiores e 25% foram ejetadas. J´a para o sistema de part´ıculas com ´orbitas inclinadas (I = 96.2 ◦ ), a maioria dessas part´ıculas s˜ao est´aveis. Apresentaremos os resultados obtidos para outros valores de inclina¸c˜ao e faremos a compara¸c˜ao com os resultados obtidos para um conjunto de part´ıculas microm´etricas da ordem de 1, 5 e 10µm. / The new data from the Pluto system during its passage through the system in July 2015, are being sent by the spacecraft NewHorizons. Pluto has a set of five satellites, Charon (forms a binary system with Pluto), Styx, Nix, Kerberos, Hydra. The recent discovery of these two small satellites, Styx and Kerberos, makes it necessary to restudy this outer region beyond the orbit of Charon. In this work we analyze the stability of the outer region Pluto-Charon system for a set of particle-test centimeters order and micron under gravitational influence of all bodies Pluto system and solar radiation pressure (for particle microns). These particles are initially eccentric and inclined orbits; They are assumed different eccentricity values and inclination. Results showed that for a set of particles originally located in orbital plane of Pluto system collided with 10% larger bodies and 25% were ejected. As for the particle system with inclined orbits (I = 96.2◦ ), most of these particles are stable. We present the results obtained for other of inclination values and make a comparison with the results obtained for a set of micrometric particles of the order of 1, 5 and 10µm.

Orientador: Silvia Maria Giuliatti Winter / Banca: Valério Carruba / Banca: Rodney da Silva Gomes / Resumo: Neste trabalho analisamos numericamente a região externa do sistema Plutão-Caronte através da insercão de partículas-teste inicialmente em 'orbitas do tipo-P prógradas e retrógradas, no sistema formado por Plutão, Caronte, Nix e Hidra. Destas integracões numéricas foram geradas grades semi-eixo maior em função da excentricidade definindo-se regiões de partículas em orbitas estáveis e regiões de colisão e escape. Na vizinhança dos satélites Nix e Hidra foram identificadas regiões caóticas, em que partículas localizadas dentro desta região têm suas excentricidades e semi-eixo maiores aumentados e escapam ou colidem com um corpo massivo do sistema. Um conjunto de partículas permaneceram em regiões próximas das orbitas de Nix e Hidra, possivelmente coorbitais de Nix e Hidra. Para ambos os casos, prógrado e retrógrado, a região estável"é maior na região externa do sistema, após a órbita de Hidra, dependendo do valor da excentricidade. Também foram realizadas simulações numéricas inserindo satélites hipotéticos massivos além da órbita de Caronte e os efeitos causados nas órbitas de Nix e Hidra foram analisados. Um estudo numérico preliminar dos efeitos da Press˜ao de Radiac¸ ˜ao Solar em partículas com raios de 1μm, 3μm, 5μm e 10μm foi realizado. Este estudo mostrou que partículas sob os efeitos do Arrasto de Poynting-Robertson deca'ıram em 1,45 × 106 anos (partículas de 1μm de raio) e 1,45 × 107 anos (partíıculas de 10μm de raio), enquanto que a Pressão de Radiac¸ ˜ao causou variacões das excentricidades das partículas fazendo com que em alguns casos houvesse colisões com o planeta. / Abstract: In this work we performed a numerical analysis of the the outer region of the Pluto-Charon system by the insertion of a sample of test particles initially in P-type prograde and retrograde orbits, in the system formed by Pluto, Charon, Nix and Hydra. These numerical integrations generated diagrams of semi-major axis versus eccentricity which define regions of particles in stable orbits and regions of collision and escape. In the vicinity of the satellites Nix and Hydra were identified chaotic regions, where particles located in this region have their eccentricities and semi-major axis increased provoking an ejection or collision with a massive body of the system. A set of particles remained in regions near the orbits of Nix and Hydra, possibly coorbitais with them. For both cases, prograde and retrograde, the "stable" region is larger in the outer region of the system, after Hydra's orbit, depending on the value of eccentricity. Numerical simulations were also performed by inserting some massive hypothetical satellites beyond the Charon's orbit and the effects on the orbits of Nix and Hydra were analyzed. A preliminary numerical study of the effects of the solar radiation force on a sample of particles with radii of 1μm, 3μm, 5μm e 10μm was performed. This study showed that particles under the effects of the Poynting-Robertson drag decay on a time scale between 1.45×106 years (particles of 1μm in radius) and 1.45×107 years (particles of 10μm in radius), while the radiation pressure caused variations of the eccentricities of the particles causing in some cases collisions with the planet. / Mestre

Orientador: Patricio Anibal Letelier Sotomayor / Dissertação (mestrado) - Universidade Estadual de Campinas, Instituto de Fisica Gleb Wataghin / Made available in DSpace on 2018-08-04T20:14:31Z (GMT). No. of bitstreams: 1 Fernandes_RafaelMonteiro_M.pdf: 6930880 bytes, checksum: bc2d3294a7be01c0e28037221d2d4b4d (MD5) Previous issue date: 2005 / Resumo: Não informado / Abstract: Not informed. / Mestrado / Física das Particulas Elementares e Campos / Mestre em Física