Spacecraft Stability
Mostrando 1-6 de 6 artigos, teses e dissertações.
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1. Reducing the Effects of Inaccurate Fault Estimation in Spacecraft Stabilization
ABSTRACT Reference Governor is an important component of Active Fault Tolerant Control. One of the main reasons for using Reference Governor is to adjust/modify the reference trajectories to maintain the stability of the post-fault system, especially when a series of actuator faults occur and the faulty system can not retain the pre-fault performance. Fault
J. Aerosp. Technol. Manag.. Publicado em: 2017-12
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2. Nonlinear Characteristic of Spherical Joints with Clearance
ABSTRACT: Joints in deployable structures can degrade the stiffness and the stability of spacecraft. In this study, the nonlinear stiffness of spherical joints is investigated. The traditional contact model of spherical joints based on non-conforming contact assumption is presented. A new contact model for spherical joints based on the Winkler model and geom
J. Aerosp. Technol. Manag.. Publicado em: 2015-06
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3. 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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4. Estudo comparativo de técnicas de controle de atitude em três eixos para satélites artificiais / Comparative study of three axes attitude control techniques for artificial satellites
Neste trabalho propõe-se um estudo sobre técnicas de controle de atitude para satélites estabilizados em três eixos e, através da modelagem e simulação computacional, analisar, comparar e fazer um estudo de alternativas/viabilidade de sistemas de controle de atitude (ACS) em três eixos, com base nos requisitos de missões espaciais. Para o estudo de
Publicado em: 2005
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5. Estudos de um método para cálculo de ganhos da malha de controle de atitude de um lançador de satélites / Analytical method for computing the controller gains of a satellite launcher
In this work, the VLS (Satellite Launcher Vehicle) control gains are calculated applying a frozen poles technique for each 1-second interval, allowing that a linear time invariant analysis to be executed inside each time interval during all flight phases. The system control architecture is proportional-integral with derivative feedback, making the 3 gains (p
Publicado em: 2004
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6. Use of spacecraft data to derive regions on Mars where liquid water would be stable
Combining Viking pressure and temperature data with Mars Orbital Laser Altimeter topography data, we have computed the fraction of the martian year during which pressure and temperature allow for liquid water to be stable on the martian surface. We find that liquid water would be stable within the Hellas and Argyre basin and over the northern lowlands e
The National Academy of Sciences.