The main focus of this research is the generation of a computational aeroelastic model for a macrofiber composite actuated micro air vehicle. Two M8528-P1 actuators were used to deform the surface of a forward-swept thin, compliant composite wing. The general approach, which included MATLAB, ABAQUS, and Athena Vortex Lattice, is described. The planform design and initial flight testing are discussed. The computational model was validated first with static tests, and then quasi-static wind-tunnel tests were used to validate the aeroelastic model. Digital image correlation was used to compare the expected and measured displacements of the wing. Flight loads were also compared for various angles of attack. The results indicated good agreement for angles of attack well within the standard flight envelope, despite small discrepancies in geometry.
Aeroelastic Model for Macrofiber Composite Actuators on Micro Air Vehicles
Journal of Aircraft ; 54 , 1 ; 199-208
2016-06-06
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Aeroelastic Model for Macrofiber Composite Actuators on Micro Air Vehicles
Online Contents | 2017
|Aeroelastic Model for Macrofiber Composite Actuators on Micro Air Vehicles
Online Contents | 2016
|UAV Aeroelastic Control Using Redundant Micro-Actuators
NTIS | 2003
|British Library Online Contents | 2010
|Nonlinear Aeroelastic Effects in Flapping Wing Micro Air Vehicles
British Library Conference Proceedings | 2008
|