Active Aeroelastic Control of Lifting Surfaces via Jet Reaction Limiter Control

Abstract

In this paper we present, the design and modeling of the novel nonlinear limiter control feedback control plant [Myneni et al., 1999;Corron et al., 2000;Corron & Pethel, 2002], applied for the first time here in an aeroelastic system, and actuated as a jet reaction torquer control of a wing with potentially chaotic dynamics. This study will provide a better understanding of the nonlinear dynamics of the open/closed-loop aeroelasticity of flexible wings with either steady or unsteady aerodynamic loads. The limiter control can be applied to either the plunging or pitching characteristic of the wing or to both of them. We show that the control can effectively suppress Limit Cycle Oscillations (LCO) and chaos well beyond the nominal flutter speed. This could lead to a practical implementation of the control mechanism on actual and future generation aircraft wings via implementation of a combination of propulsive/jet type forces, micro surface effectors and fluidic devices. Analysis of this control produced favorable results in the suppression of LCO amplitude and increased flutter boundaries for plunging and pitching motion. The limiting control has asymptotically zero power, and is simply implemented, making it a feasible solution to the problem of the chaotic dynamics of the oscillating airfoil.

Design of a Wind Tunnel Apparatus to Assist Flow and Aeroelastic Conrtol via Zero Net Mass Flow Actuators

“…1. For this model the aeroelastic governing equations for the 2-DOF system can be written as follows [3,12,13]:…”

Robust Nonlinear Regulation of Limit Cycle Oscillations in UAVs Using Synthetic Jet Actuators

“…LCO refer to "flutter" behaviors in UAV wings that manifest themselves as constant-amplitude oscillations [1], which result from nonlinearities inherent in the aeroelastic dynamics of the UAV system [2]. Due to these behaviors, the LCO would surpass the limiting safe flight boundaries of an aircraft [3] and could potentially lead to structural damage and catastrophes. Control applications for LCO suppression are often developed (e.g., see [4][5][6]) using mechanical deflection surfaces (e.g.…”

“…The SJA synthesize the jet flow through the alternating suction and ejection of fluid through an aperture, which is produced via pressure oscillations in a cavity [8] as shown in Figure 1. The pressure oscillations can be generated using various methods, including pistons in the SJA orifices [3] or piezoelectric diaphragms [7,9]. SJA can achieve boundary-layer flow control near the surface of a UAV wing [10], since they can provide instant actuation, unlike conventional mechanical control surfaces.…”

Lyapunov-based Adaptive Regulation of Limit Cycle Oscillations in Aircraft Wings Using Synthetic Jet Actuators

“…LCO refer to "flutter" behavior in UAV wings that manifest themselves as constant-amplitude oscillations (O'Donnell et al (2007)), which result from nonlinearities inherent in the aeroelastic dynamics of the UAV system (Satak et al (2012)). Due to these behaviors, the LCO would surpass the limiting safe flight boundaries of an aircraft (Rubillo et al (2005)) and could potentially lead to structural damage and catastrophes. Control applications for LCO suppression are often developed (e.g., see Frampton and Clark (2000); Strganac et al 2000; Platanitis and Strganac (2004)) using mechanical deflection surfaces (e.g.…”

“…1. The pressure oscillations can be generated using various methods, including pistons in the SJA orifices (Rubillo et al (2005)) or piezoelectric diaphragms (Deb et al (2005b); Mackunis et al (2013)). SJA can achieve boundary-layer flow control near the surface of a UAV wing (Milanese et al (2008)), since they can provide instant actuation, unlike conventional mechanical control surfaces.…”