Active control of composite structures has primarily focused on vibration control and other small-scale deformations. For use in morphing aircraft structures, a composite 'smart joint' is proposed, employing both shape memory alloy and shape memory polymer to replace a conventional rotary actuator. This joint functions as a discrete member capable of both actuation and structural rigidity in user programmable states, with large-scale tip deflections on the order of 10-20% camber. A strain energy model is used to prescribe joint deflection in terms of thermally varying material properties across the thickness of the joint, allowing the designer of a morphing system to select electrical power input and element composition as based on deflection, response speed, and load capacity. This model discretizes the transformation into a multiple step shape change maneuver using the tri-phase process to determine deflection both when heated and when set into its cooled state. Comparison with a finite element model confirms thermodynamics analysis as well as deflection accurate within 2% of analytically predicted behavior.
Methodology for design of an active rigidity joint
Journal of Intelligent Material Systems and Structures ; 20 , 3 ; 311-327
2009
17 Seiten, 47 Quellen
Article (Journal)
English
aktive Regelung , carbonfaserverstärkter Kunststoff , Finite-Elemente-Methode , Flugzeugbau , Flugzeugzelle , Formgedächtniseffekt , Formgedächtnislegierung , intelligente Regelung , mathematisches Modell , mechanische Spannungsverteilung , piezoelektrischer Werkstoff , Regelungsanalyse , Schwingungsregelung , Simulationsmodell , Spannungs-Dehnungs-Verhalten , starre Verbindung , Steifigkeit , Verformungsenergie
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