High-Bandwidth Morphing Actuator for Aeroelastic Model Control

The design and testing of a high-bandwidth continuous actuator for aeronauticalapplications is presented hereinafter. The actuator has a dual goal of controlling both the aeroelasticbehaviour and the flight mechanics of the model in which it is installed. In order to achieve theseaims, the actuation bandwidth of the active aerofoil, as well as its static camber variation, have to besufficiently high. The camber morph is achieved by using tailored piezoelectric patches in a sandwichconfiguration with a linear trailing edge slider to allow the necessary compliance. The morphingactuator is designed for a NACA 0018 aerofoil with a chord of 300mmand a span of 40 mm. Static anddynamic experimental tests are carried out on a prototype, and a camber variation control techniqueis implemented. It is proved that the actuator bandwidth is up to 25 Hz and the equivalent maximumdeflection is 15 degrees. This solution is shown to be a viable light-weight alternative to theconventional brushless/servo-motor approach currently used in aeroelastic models.

[1]  Jennifer L. Pinkerton,et al.  A Feasibility Study To Control Airfoil Shape , 1997 .

[2]  Gianluca Amendola,et al.  Numerical and experimental validation of a full scale servo-actuated morphing aileron model , 2018 .

[3]  Jonathan E. Cooper,et al.  Flutter control using vibration test data: theory, rig design and preliminary results , 2012 .

[4]  Daniel J. Inman,et al.  Synergistic Smart Morphing Aileron , 2013 .

[5]  Sergio Ricci,et al.  Active Aeroelastic Control Over a Multisurface Wing: Modeling and Wind-Tunnel Testing , 2007 .

[6]  P. Guillaume,et al.  The PolyMAX Frequency-Domain Method: A New Standard for Modal Parameter Estimation? , 2004 .

[7]  Daniel G. Cole,et al.  High Performance ‘‘V-stack’’ Piezoelectric Actuator , 2004 .

[8]  John E. Mottershead,et al.  Design and wind tunnel test of a MODular aeroelastic FLEXible wing (MODFLEX) , 2016 .

[9]  Manfred Morari,et al.  Design, realization and structural testing of a compliant adaptable wing , 2015 .

[10]  Marco Debiasi,et al.  Measurements of a Symmetric Wing Morphed by Macro Fiber Composite Actuators , 2016 .

[11]  Paul H. Mirick,et al.  Low-cost piezocomposite actuator for structural control applications , 2000, Smart Structures.

[12]  Daniel J. Inman,et al.  Novel, Bidirectional, Variable-Camber Airfoil via Macro-Fiber Composite Actuators , 2010 .

[13]  Shijun Guo,et al.  A review of modelling and analysis of morphing wings , 2018, Progress in Aerospace Sciences.

[14]  Joseph S Browning,et al.  F-16 Ventral Fin Buffet Alleviation Using Piezoelectric Actuators , 2012 .

[15]  E. Crawley,et al.  Static Aeroelastic Control Using Strain Actuated Adaptive Structures , 1991 .

[16]  Moti Karpel,et al.  Analysis and Wind Tunnel Testing of a Piezoelectric Tab for Aeroelastic Control Applications , 2006 .

[17]  Ron Barrett,et al.  Design and Testing of a Subsonic All-Moving Adaptive Flight Control Surface , 1997 .

[18]  Earl H. Dowell,et al.  Experimental and Theoretical Study on Aeroelastic Response of High-Aspect-Ratio Wings , 2001 .

[19]  Karl Johan Åström,et al.  PID Controllers: Theory, Design, and Tuning , 1995 .

[20]  Ron Barrett,et al.  All-moving active aerodynamic surface research , 1995 .

[21]  Marco Debiasi,et al.  Deformation of the Upper and Lower Surfaces of an Airfoil by Macro Fiber Composite Actuators , 2013 .

[22]  Ron Barrett,et al.  Missile flight control using active flexspar actuators , 1995, Smart Structures.