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.File | Dimensione | Formato | |
---|---|---|---|
Saltari_On-the-control_2017.pdf
solo gestori archivio
Tipologia:
Versione editoriale (versione pubblicata con il layout dell'editore)
Licenza:
Tutti i diritti riservati (All rights reserved)
Dimensione
1.9 MB
Formato
Adobe PDF
|
1.9 MB | Adobe PDF | Contatta l'autore |
IFASD_Frontespizio_2017.pdf
solo gestori archivio
Tipologia:
Versione editoriale (versione pubblicata con il layout dell'editore)
Licenza:
Tutti i diritti riservati (All rights reserved)
Dimensione
71.65 kB
Formato
Adobe PDF
|
71.65 kB | Adobe PDF | Contatta l'autore |
I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.