The purpose of the present work is the development of a linearized aeroelastic modeling and analysis for a launch vehicle in the neighborhood of a transonic flight condition. A two-dimensional airfoil transonic case selected from the technical literature (specifically, a MBB-A3 supercritical airfoil in unsteady transonic regime) has been studied to validate the procedure for identifying the linearized unsteady aerodynamics. The present methodology has been successively performed for the system identification of the linearized aerodynamics of the VEGA European small launch vehicle in a transonic flow phase and in presence of an angle of attack. This has been achieved by performing several prescribed modal-transient boundary conditions on a Euler-based computational-fluid-dynamics code and postprocessing the input/output data in the frequency domain. Finally, both a standard eigenanalysis and an iterative eigenanalysis have been performed to study the aeroelastic stability on the linearized model of the launch vehicle in transonic flow. The nature of the methodology is quite general and can be applied in the neighborhood of any arbitrary parametric flight condition of a launch vehicle. Copyright © 2005 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Linearized aeroelastic analysis for a launch vehicle in transonic flight conditions / F., Capri; Mastroddi, Franco; A., Pizzicaroli. - In: JOURNAL OF SPACECRAFT AND ROCKETS. - ISSN 0022-4650. - STAMPA. - 43:(2006), pp. 92-104. [10.2514/1.13867]

Linearized aeroelastic analysis for a launch vehicle in transonic flight conditions

MASTRODDI, Franco;
2006

Abstract

The purpose of the present work is the development of a linearized aeroelastic modeling and analysis for a launch vehicle in the neighborhood of a transonic flight condition. A two-dimensional airfoil transonic case selected from the technical literature (specifically, a MBB-A3 supercritical airfoil in unsteady transonic regime) has been studied to validate the procedure for identifying the linearized unsteady aerodynamics. The present methodology has been successively performed for the system identification of the linearized aerodynamics of the VEGA European small launch vehicle in a transonic flow phase and in presence of an angle of attack. This has been achieved by performing several prescribed modal-transient boundary conditions on a Euler-based computational-fluid-dynamics code and postprocessing the input/output data in the frequency domain. Finally, both a standard eigenanalysis and an iterative eigenanalysis have been performed to study the aeroelastic stability on the linearized model of the launch vehicle in transonic flow. The nature of the methodology is quite general and can be applied in the neighborhood of any arbitrary parametric flight condition of a launch vehicle. Copyright © 2005 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
2006
Airfoils; Boundary conditions
01 Pubblicazione su rivista::01a Articolo in rivista
Linearized aeroelastic analysis for a launch vehicle in transonic flight conditions / F., Capri; Mastroddi, Franco; A., Pizzicaroli. - In: JOURNAL OF SPACECRAFT AND ROCKETS. - ISSN 0022-4650. - STAMPA. - 43:(2006), pp. 92-104. [10.2514/1.13867]
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/71842
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