Morphing Wing Aerodynamic Control via Macro-Fiber-Composite Actuators in an Unmanned Aircraft

The article presents a research in the field of morphing wings (adaptive wing geometry) developed over a prototype of micro-unmanned air vehicle based on smart materials technology. This morphing wing will optimize the aircraft performance features. Modifying the curvature of the wing, the micro-unmanned air vehicles will adjust its performance in an optimum mode to cruise flight condition as well as in the phases of takeoff and landing. The installation of mechanical elements for control surfaces in small size aircraft means, on some occasions, an extra complexity. In addition, it takes into account an increase in aircraft weight. In this research, the adaptive wing geometry is based on macro-fiber composites, so that its position on the inner surfaces of the wing allows the appropriate modification of the curvature, adapting them to the flight profile. This research will present the conceptual design of the vehicle, computational calculations, experimental results of the wind tunnel testing, validations using non-intrusive techniques (particle image velocimetry) and a theoretical–experimental analysis of the macro-fiber composite effects over the wing. An Arduino board will perform the control parameters of the macro-fiber composite deformation. With these analytical, computational, and experimental results, the most relevant conclusions are presented.

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A novel unmanned aircraft with solid-state control surfaces: Analysis and flight demonstration

Journal of Intelligent Material Systems and Structures ◽

10.1177/1045389x12459592 ◽

2012 ◽

Vol 24 (2) ◽

pp. 147-167 ◽

Cited By ~ 32

Author(s):

Onur Bilgen ◽

Lauren M Butt ◽

Steven R Day ◽

Craig A Sossi ◽

Joseph P Weaver ◽

...

Keyword(s):

Solid State ◽

Wind Tunnel ◽

Fiber Composite ◽

Aerodynamic Characteristics ◽

Unmanned Aircraft ◽

Ocean Engineering ◽

Remotely Piloted Aircraft ◽

Macro Fiber Composite ◽

Wing Morphing ◽

Control Surfaces

This article presents a completely servo-less, piezoelectric controlled, wind tunnel and flight tested, remotely piloted aircraft that has been developed by the 2010 Virginia Tech Wing Morphing Design Team (a senior design project between the Departments of Mechanical Engineering and Aerospace and Ocean Engineering). A type of piezocomposite actuator, the Macro-Fiber Composite, is used for changing the camber of all control surfaces on the aircraft. The aircraft is analyzed theoretically for its aerodynamic characteristics to aid the design of the piezoelectric control surfaces. A vortex lattice analysis complemented the database of aerodynamic derivatives used to analyze control response. Steady-state roll rates were measured in a wind tunnel and were compared to a similar aircraft with servomotor actuated control surfaces. The theoretical analysis and wind tunnel testing demonstrated the stability and control authority of the concept, culminating in the first flight of the completely Macro-Fiber Composite controlled aircraft on 29 April 2010. An electric motor-driven propulsion system is used to generate thrust, and all systems are powered with a single lithium polymer battery. This vehicle became the first completely Macro-Fiber Composite controlled, flight tested aircraft. It is also known to be the first fully solid-state piezoelectric material controlled, nontethered, flight tested fixed-wing aircraft.

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Macro-fiber composite actuators for a swept wing unmanned aircraft

The Aeronautical Journal ◽

10.1017/s0001924000003055 ◽

2009 ◽

Vol 113 (1144) ◽

pp. 385-395 ◽

Cited By ~ 38

Author(s):

O. Bilgen ◽

K. B. Kochersberger ◽

D. J. Inman

Keyword(s):

Wind Tunnel ◽

Smart Materials ◽

Shape Control ◽

Fiber Composite ◽

Unmanned Aircraft ◽

Control Surface ◽

Swept Wing ◽

Roll Control ◽

Macro Fiber Composite ◽

Lift And Drag

Abstract The purpose of the research presented here is to exploit actuation via smart materials to perform shape control of an aerofoil on a small aircraft and to determine the feasibility and advantages of smooth control surface deformations. A type of piezoceramic composite actuator known as Macro-Fiber Composite (MFC) is used for changing the camber of the wings. The MFC actuators were implemented on a 30° swept wing, 0·76m wingspan aircraft. The experimental vehicle was flown using two MFC patches in an elevator/aileron (elevon) configuration. Preliminary flight and wind-tunnel testing has demonstrated the stability and control of the concept. Flight tests were performed to quantify roll control using the MFC actuators. Lift and drag coefficients along with pitch and roll moment coefficients were measured in a low-speed, open-section wind tunnel. A vortex-lattice analysis complemented the database of aerodynamic derivatives used to analyse control response. The research, for the first time, successfully demonstrated that piezoceramic devices requiring high voltages can be effectively employed in small air vehicles without compromising the weight of the overall system.

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