CBL - Campus del Baix Llobregat

Projecte llegit

Títol: BALSELLS- JORDI VENTURA-


Estudiants que han llegit aquest projecte:


Director/a: BERTRAN ALBERTÍ, EDUARD

Departament: TSC

Títol: BALSELLS- JORDI VENTURA-

Data inici oferta: 16-09-2019     Data finalització oferta: 16-09-2019



Estudis d'assignació del projecte:
    Tipus: Individual
     
    Lloc de realització: ERASMUS
     
            Supervisor/a extern: Haithem Taha
            Institució/Empresa: Universitat de California Irvine (UCI)
            Titulació del Director/a: Ph.D. Applied Matemathics
     
    Paraules clau:
    model de roll de l'avió Control geomètric no-linial. Algebra de Lie
     
    Descripció del contingut i pla d'activitats:
    preparar la part experimental que pretén comprovar el funcionament d'un nou model de roll quan l'avió es troba en pèrdues. Aquest nou mecanisme es basa en el control geomètric no-linial i utilitza àlgebra de Lie (com ja vam veure) en el seu funcionament.
     
    Overview (resum en anglès):
    According to recent research conducted by professor
    Haithem E. Taha and Ahmed M. Hasan, there is a
    loss in the control capabilities of the ailerons when
    flying at stall regime. Not only the sensitivity of
    this control surface decreases in its ability to generate
    roll moment but it produces the opposite effect, making
    the aircraft unpredictable. In order to overcome
    this situation, an unconventional method, called LIBRA,
    has been devised, involving geometric nonlinear
    control tools such as Lie brackets. In the numerical
    simulations, this mechanism would generate up to 4
    times more rolling moment than the conventional procedure.
    The first stage of the experimental research on the
    LIBRA mechanism consists of finding out the aerodynamic
    characteristics of a small-scaled aircraft model
    in which the mechanism will be implemented as well
    as determining if there really exists a loss in the control
    capabilities when flying at stall. This experiments
    will be performed in a wind tunnel and both the forces
    and moments acting on an aircraft will have to be
    measured.
    Currently there exist in the market multi-axis load
    cells that can measure moments and forces in all directions.
    However, they have fixed capacities and they
    are very expensive and delicate. One of the main goals
    of this thesis will be the design and manufacturing of
    a modular load cell system able to measure forces and
    moments in four different axis.
    Besides, the unconventional method will be thoroughly
    described from a differential geometry perspective.
    Finally, by means of the 4-axis load cell
    system, forces and moments will be measured in different
    control configurations at stall, in order to test
    the rolling generating capabilities of the ailerons.


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