Fully-coupled equations of nonlinear rigid-body motion and linearized structural dynamics of flexible aircraft are presented using a coordinate system verifying the practical mean-axis constraints. Linearized equations around aeroelastic trim conditions are obtained and implemented for complex configurations described by a Finite Element Method structural model and by a Doublet Lattice Method aerodynamic model. A state-space representation of the linearized system is ultimately obtained using a rational function approximation of small-disturbance fully-unsteady aerodynamics. The state-space flexible aircraft model simultaneously includes rigid-body, elastic, and aerodynamic state variables, and can be used to study integrated flight dynamic/aeroelastic stability as well as response to both control inputs and gust disturbances. The model is applied to a representative flying-wing configuration to design an optimum controller for body freedom flutter suppression and gust alleviation. Open-loop and closed-loop numerical results are presented to point out influence of coupling effects between rigid-body and elastic degrees-of-freedom on control of flexible vehicles.

On the control of aeroelastic/flight dynamic integrated stability of maneuvering aircraft / Saltari, F.; Mastroddi, F.; Riso, C.; De Matteis, G.; Colaianni, S.. - STAMPA. - 3:(2017), pp. 1971-1986. (Intervento presentato al convegno International Forum of Aeroelasticity and Structural Dynamics 2017 tenutosi a Como; Italy nel June 25-28 2017).

On the control of aeroelastic/flight dynamic integrated stability of maneuvering aircraft

Saltari, F.
Software
;
Mastroddi, F.
Methodology
;
Riso, C.
Methodology
;
De Matteis, G.;
2017

Abstract

Fully-coupled equations of nonlinear rigid-body motion and linearized structural dynamics of flexible aircraft are presented using a coordinate system verifying the practical mean-axis constraints. Linearized equations around aeroelastic trim conditions are obtained and implemented for complex configurations described by a Finite Element Method structural model and by a Doublet Lattice Method aerodynamic model. A state-space representation of the linearized system is ultimately obtained using a rational function approximation of small-disturbance fully-unsteady aerodynamics. The state-space flexible aircraft model simultaneously includes rigid-body, elastic, and aerodynamic state variables, and can be used to study integrated flight dynamic/aeroelastic stability as well as response to both control inputs and gust disturbances. The model is applied to a representative flying-wing configuration to design an optimum controller for body freedom flutter suppression and gust alleviation. Open-loop and closed-loop numerical results are presented to point out influence of coupling effects between rigid-body and elastic degrees-of-freedom on control of flexible vehicles.
2017
International Forum of Aeroelasticity and Structural Dynamics 2017
flexible aircraft; flight dynamic/aeroelastic coupling; flutter suppression; gust alleviation; finite element method; double lattice method
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
On the control of aeroelastic/flight dynamic integrated stability of maneuvering aircraft / Saltari, F.; Mastroddi, F.; Riso, C.; De Matteis, G.; Colaianni, S.. - STAMPA. - 3:(2017), pp. 1971-1986. (Intervento presentato al convegno International Forum of Aeroelasticity and Structural Dynamics 2017 tenutosi a Como; Italy nel June 25-28 2017).
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/964796
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