Controller and aeroelasticity analysis for a morphing wing

AuthorSearch for: ; Search for: ; Search for: ; Search for: ; Search for:
Proceedings titleAIAA Atmospheric Flight Mechanics Conference 2011
ConferenceAIAA Atmospheric Flight Mechanics Conference 2011, 8 August 2011 through 11 August 2011, Portland, OR
SubjectAeroelastic instabilities; Closed loop architecture; Controller validation; Heating and cooling; Proportional-integral; Shape memory alloys(SMA); System approximation; Wind-tunnel testing; Aerodynamics; Closed loop control systems; Computer simulation; Linear systems; Mach number; Microactuators; Numerical models; Wind stress; Aeroelasticity
AbstractThe main objectives of this research work are: the design and the wind tunnel testing of a controller for a new morphing mechanism using smart materials made of Shape Memory Alloy (SMA) for the actuators, and the aero-elasticity studies for the morphing wing. The finally obtained configuration for the controller is a combination of a bi-positional controller (on-off) and a PI (proportional-integral) controller, due to the two phases (heating and cooling) of the SMA wires' interconnection. Firstly, the controller is used for the open loop development step of a morphing wing project, while, further, it is included as an internal loop in the closed loop architecture of the morphing wing system. In the controller design procedure four step are considered: 1) SMA actuators model numerical simulation for different loading force cases; 2) linear system approximation in the heating and cooling phases using Matlab's System Identification Toolbox and the numerical values obtained in the first step; 3) selecting the controller type and its tuning for each of the two SMA actuators' phases - heating and cooling; and 4) integration of the two controllers just obtained into a single controller. For the controller validation three actions are taken: 1) numerical simulation; 2) bench testing; and 3) wind tunnel testing. For the third part of this study, aeroelastic studies, the purpose is to determine the flutter conditions in order to be avoided during wind tunnel tests. These studies show that aeroelastic instabilities for the morphing configurations considered appears at Mach number 0.55, which is higher than the wind tunnel Mach number limit speed of 0.3. © 2011 by Ruxandra Botez.
Publication date
AffiliationNational Research Council Canada (NRC-CNRC)
Peer reviewedYes
NPARC number21271730
Export citationExport as RIS
Report a correctionReport a correction
Record identifier141390c9-69a2-4487-8a47-1fd60d865895
Record created2014-03-24
Record modified2016-05-09
Bookmark and share
  • Share this page with Facebook (Opens in a new window)
  • Share this page with Twitter (Opens in a new window)
  • Share this page with Google+ (Opens in a new window)
  • Share this page with Delicious (Opens in a new window)
Date modified: