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PATEL ET AL. 1265 Fig. 1 Schematic of a DBD plasma actuator showing asymmetric electrode arrangement, dielectric layer, and location of plasma formation. The actuator location is referenced to the junction of the exposed and covered electrodes. plasma actuator, the actuator used in the present study, consists of two electrodes that are separated by a dielectric material. One of the electrodes is typically exposed to the surrounding air and the other is fully encapsulated by a dielectric material. Figure 1 shows a schematic illustration of the electrode configuration for the DBD plasma actuator. When an ac voltage (5 kHz) is supplied to the electrodes at sufficiently high amplitude levels (3–12 kV peak to peak), the air ionizes in the region of the largest electric field potential. This typically occurs at the edge of the electrode that is exposed to the air and spreads out over the area projected by the covered electrode, directing momentum into the surrounding air. The process of ionizing the air in this configuration is classically known as a dielectric barrier discharge [9]. The basis of the DBD plasma actuator configuration is that the ionized air (plasma) in the presence of an electric field gradient produces a body force on the ambient air [10], which induces a virtual aerodynamic shape over the surface around the actuator. The body- force vector can be tailored for a given application by configuring the orientation and design of the electrode geometry. Enloe et al. [10] showed that the formation of the plasma is a dynamic process that varies in time and space during the ac cycle. Orlov et al. [11] recently developed a lumped circuit model from which the space–time- dependent body force can be computed. This model provides insight in the dependence of the body force on the ac frequency and amplitude, wave-form shape, and electrode geometry. Plasma examples of flow control applications using the DBD plasma actuators include exciting three-dimensional boundary-layer instabilities on a sharp cone at Mach 3.5 [12], lift augmentation on wings [13], separation control for low-pressure turbine blades [14], leading-edge separation control on wing sections [15], phased plasma arrays for unsteady flow control [16], and control of the dynamic stall vortex on oscillating airfoils [17]. More recently, the use of plasma actuators has been demonstrated for air vehicle control through applications such as plasma flaps and slats [18], smart plasma slat [19], and plasma-optimized airfoil [20]. In the plasma slat application, Corke et al. [18] demonstrated the use of the plasma actuator on the leading edge of a two-dimensional NACA 0015 airfoil in a manner that mimics the effect of a movable leading-edge slat of a conventional high-lift system. In the smart plasma slat application by Patel et al. [19], the system presented in [18] was further developed to include closed-loop control using a single high- bandwidth pressure sensor and a feedback controller for autonomous sense and control of incipient flow separation and wing stall. A majority of plasma flow control research to date has focused on controlling flow separation over two-dimensional geometries. These early studies clearly showed that plasma actuators could delay separation and increase the stall angle of attack and maximize lift coefficient of the lifting surfaces. Only recently have researchers been looking at applying plasma flow control to create aerodynamic control moments on air vehicle surfaces. The present work explores the application of a DBD plasma actuator for controlling the longitudinal dynamics of a three- dimensional UCAV with a 47-deg leading-edge sweep. The UCAV configuration chosen for this study is based on a previously examined U.S. Air Force–Boeing 1303 UCAV design. Figure 2 shows the details of the 1303 UCAV wing used in this study. The vehicle is basically a blended wing body on which the fuselage is blended smoothly with the wing, with a varying cross-section along the span and 30- deg trailing-edge sweep angle. In its conventional configuration, the 1303 UCAV features movable flap and split ailerons at the trailing edge to control the vehicle. The goal of this research is to demonstrate the feasibility of a plasma wing: a flying wing that uses plasma flow control technology to create aerodynamic control moments of sufficient magnitude so that conventional moving aerodynamic controls could be eliminated. Because the 1303 UCAV contains a 47-deg leading-edge sweep, a discussion on the leading-edge vortex (LEV) is relevant to touch upon. Fig. 2 planform of the 2.31%-scale full-span wing model used for flow visualization studies, b) a photograph of the 2.31%-scale full-span wing model, c) a photograph of the 4.16%-scale half-span wing model used for plasma actuator experiments, and d) a photograph of the 4.16%-scale half-span wing model with conventional flap and split ailerons. The 1303 UCAV wing models used in the present study: a) aPDF Image | Plasma Actuators for Hingeless Aerodynamic Control of an Unmanned Air Vehicle
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