Commande en boucle fermee sur un profil d'aile deformable dans la soufflerie Price-Paidoussis.

摘要

The purpose of the ATR-42 project is to apply the concept of morphing wings by fabricating a morphing composite wing model of the Regional Transport Aircraft-42 to reduce drag and improve the aerodynamic performance. A control-command system coupled to an actuator mechanism will morph the wing skin. However, for best results, the control of the deformation must be studied carefully to insure the precision. Thus, a dual digitalexperimental approach is required. The solution proposed in this paper focuses on the controlled deformation of the upper wing of the ATR-42. A composite wing model with morphing capabilities was built and tested in the wind tunnel to evaluate its aerodynamic performance and serve as reference. A deformation mechanism, consisting of two engines and two camshafts, was subsequently designed and integrated within this model to obtain the optimum wing shapes according to the different flight condition. A control loop position was modeled in Matlab / Simulink and implemented experimentally to control the mechanism. Two types of results have been obtained. The first set concerned regulation and the second concerned aerodynamics. The control loop has achieved the desired skin displacement with an accuracy of 5%. Deformations of the upper skin were performed by a actuation system driven by motors, limitations supply were assured by the regulation architecture. For several flight conditions, the pressure measurements, validated with simulation results, have confirmed a reduction of the induced drag, compared to the original ATR-42 airfoil drag reduction.