1,721,083 research outputs found
Determinazione delle Derivate Aerodinamiche Propulsive nelle Equazioni di Equilibrio e Stabilità del Velivolo
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A Comparative design of a MIMO Neural Adaptive Rate Damping for a Nonlinear Helicopter Model
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4D trajectory optimization with weather forecast parameters
No full textThis paper presents a 4-Dimensional Trajectory (4DT) optimization tool to be implemented within an innovative Flight Management System (FMS) developed to control a commercial airliner along the optimal reference trajectory, respecting spatial and temporal constraints. The 4DT optimization tool includes weather forecast parameters based on the Global Forecast System (GFS) model, and it generates a trajectory that minimizes the aircraft fuel consumption by solving an Optimal Control Problem (OCP), using the Chebyshev Pseudospectral numerical direct collocation scheme. The advantages
of the implementation of real atmosphere data in the optimization process are evaluated through simulations performed in the Multipurpose Aircraft Simulation Laboratory (MASLab), on a Boeing 747-100 model equipped with a complete Automatic Flight Control System (AFCS) suite. The results, for a
Rome to Turin climb-cruise-descent flight mission, show that the reference trajectory generated with the novel optimization tool allows increased 4DT tracking performances and a fuel consumption reduction of 2.3%
Structure Design for the Elettra Twin Flyer Prototype
Full text linkThis paper presents different structural solutions compared
under the same manoeuvrability and operativity requirements.
The structures to be analysed are chosen from an initial set,
selected among many solutions which fulfil the dimensional
requirements. The airship, in fact, has to be big enough to
accommodate a pre-determined volume of payload, has to
accommodate the motors in pre-defined locations to allow a
good manoeuvrability while limiting the structural
deformations, must be able to house all the systems necessary
for its operation and should be able to contain enough volume of
helium as to sustain at least the 95 % of the structure weight.
To minimize the costs of the structural analysis two
configurations has been selected as the most representative of
the many configurations proposed: the non-rigid double-hull
(Figure 1) and the rigid soap-shape airship (Figure 2). Among
the available aeronautical technologies, the aluminium truss and
the carbon sandwich structures have been considered for the
exoskeleton of the soap-shape airship. On the other hand, the
structure of the double-hull is too complex to be realized by
standard aluminium components, so only the carbon sandwich
solution has been analysed
Attitude Control of a Flexible Satellite Using a Neural Network Optimal Controller for the Suppression of the Vibrations
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Three-body Moon-Mars transfer with revisited weak stability boundary concept and aerobraking capture
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