Transfer Orbits
Mostrando 1-12 de 21 artigos, teses e dissertações.
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1. Trajectory Control During an Aeroassisted Maneuver Between Coplanar Circular Orbits
ABSTRACT: This paper presents the simulation results of an aeroassisted maneuver around the Earth, between coplanar circular orbits, from a geostationary orbit to a low orbit. The simulator developed considers a reference trajectory and a trajectory perturbed by external disturbances combined with non-idealities of sensors and actuators. It is able to operat
J. Aerosp. Technol. Manag.. Publicado em: 2014-06
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2. Thermal Protection System and Trajectory Optimization for Orbital Plane Change Aeroassisted Maneuver
ABSTRACT: The aim of this paper was to identify, for a specific maneuver, the optimal combination between the trajectory and the associated heat shield configuration, namely the locations and thicknesses of the ablative and reusable zones, that maximize the allowable payload mass for a spacecraft. The analysis is conducted by considering the coupling between
J. Aerosp. Technol. Manag.. Publicado em: 2013-03
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3. Pointing Algorithm for Reentry Orbit Injection with Uncontrolled Last Stage
Abstract: An essencial requirement for a launcher with uncontrolled last stage is to compute the ignition time of that stage and its attitude, in order to obtain a proper orbit transfer from a nonpropelled trajectory to a desired orbit, since such stage it cannot change its velocity profile and its direction. This article presents an algorithm that allows ac
J. Aerosp. Technol. Manag.. Publicado em: 2012-09
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4. The algorithmic weak stability boundary in earth-to-moon mission design: dynamical aspects and applicability.
This thesis consists of an extensive study of the Weak Stability Boundary (WSB) concept in low-energy Earth-to-Moon mission design within the mathematical structure provided by the Planar Circular Restricted Three-Body Problem (PCR3BP). By employing the patched three-body approach to approximate the Sun-Earth-Moon-spacecraft system, we examine and characteri
Publicado em: 2011
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5. Controle de trajetória orbital em manobras de empuxo contínuo de longo prazo / Control of orbital trajectory in maneuvers with continuous thrust of long term
Este trabalho considera o problema do controle da trajetória para manobras de transferência orbital utilizando um sistema propulsivo capaz de aplicar empuxo contínuo por um longo período de tempo. Foram analisadas não-idealidades dos propulsores e seus efeitos no sistema de controle durante a transferência orbital. Considerou-se um sistema de controle
Publicado em: 2009
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6. Control of orbital trajectory in maneuvers with continuous thrust of long term / Controle de trajetória orbital em manobras de empuxo contínuo de longo prazo
Este trabalho considera o problema do controle da trajetória para manobras de transferência orbital utilizando um sistema propulsivo capaz de aplicar empuxo contínuo por um longo período de tempo. Foram analisadas não-idealidades dos propulsores e seus efeitos no sistema de controle durante a transferência orbital. Considerou-se um sistema de controle
Publicado em: 2009
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7. Estudo de algumas aquisições orbitais usando um propulsor a plasma do tipo hall com imãs permanentes. / Estudo de algumas aquisições orbitais usando um propulsor a plasma do tipo hall com imãs permanentes.
This work aims at momentum for the acquisition of orbits of artificial satellites equipped with a Hall thruster. These devices are responsible for the transformation of the electricity used in the gas ionization in kinetic energy for the acceleration of the plasma that provides thrust to the satellite. Since mid-2002, the Plasma Laboratory of the Institute o
Publicado em: 2008
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8. Confinement by design?
The configuration space of SU(N) gauge theory is restricted to orbits with vanishing Polyakov loops of non-trivial N-ality. A practical method of constraining to this orbit space C0 is found by implementing a certain axial-type gauge. It is shown that the representative of an orbit in C0 is unique in this gauge up to time independent Abelian gauge transforma
Brazilian Journal of Physics. Publicado em: 2007-03
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9. Orbital maneuvers between the Lagrangian points and the primaries in the Earth-Sun system
This paper is concerned with trajectories to transfer a spacecraft between the Lagrangian points of the Sun-Earth system and the primaries. The Lagrangian points have important applications in astronautics, since they are equilibrium points of the equation of motion and very good candidates to locate a satellite or a space station. The planar circular restri
Journal of the Brazilian Society of Mechanical Sciences and Engineering. Publicado em: 2006-06
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10. Orbital evolution and maneuvers around non-spherical bodies / Evolução orbital e manobras em torno de corpos não-esféricos
In the last years several asteroids had their shapes identified using images from space probes or through the indirect radar data determination. In a general way, these asteroids have forms quite different from spherical. Conventional spherical harmonic representations of the gravitational potential of such bodies require expansions of high degree and order,
Publicado em: 2006
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11. Trajetórias alternativas no sistema Terra-Lua / Alternative paths in the Earth-moon system
O Problema Restrito de Três Corpos prevê a existência de várias famílias de órbitas periódicas no Sistema Terra-Lua. Neste trabalho, estudamos duas delas a Família G de órbitas periódicas diretas ao redor de L1 e a Família H2 de órbitas periódicas diretas ao redor da Lua. Nossas investigações consideraram, além do Problema Restrito de Três C
IBICT - Instituto Brasileiro de Informação em Ciência e Tecnologia. Publicado em: 08/12/2005
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12. Transferências orbitais e dinâmicas na vizinhança dos pontos lagrangianos L1 e L2 / Transfer orbits and dynamics around the lagrangian points L1 e L2
Este trabalho apresenta um estudo da dinamica na vizinhan¸ca dos pontos lagrangianos L1 e L2 no problema restrito de tres corpos nos modelos Terra-Lua e Terra-Sol. Apesar do car´ater hiperb´olico desses pontos, a redu¸cao `a variedade central permite obter ´orbitas peri´odicas e quase peri´odicas existentes ao seu redor. Este procedimento ´e realizad
IBICT - Instituto Brasileiro de Informação em Ciência e Tecnologia. Publicado em: 08/12/2005