Dynamic characteristics of a Benchmark models program supercritical wing

Dansberry, Bryan E.

doi:10.2514/6.1992-2368

Cited by 17 publications

(13 citation statements)

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“…dsw (10) where SW is the work done on the system by an arbitrary infinitesimal (or virtual) displacement of the generalized coordinates. This virtual work includes the work done by nonconservative forces (e.g., damping) and external forces.…”

Section: Applying the Principle Of Virtual Workmentioning

confidence: 99%

“…and performing the differentiation described in Eqn(10) results in the following expressions for the generalized aerodynamic forces. Pressure distribution over wing section.636American Institute of Aeronautics and Astronautics Where L, M ; , and H s are the lift, pitching moment about the reference point, x , and the control surface moment about its hinge-line, respectively.…”

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confidence: 99%

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Modeling the Benchmark Active Control Technology wind-tunnel model for application to flutter suppression

Martin

1996

21st Atmospheric Flight Mechanics Conference

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This paper describes the formulation of a model of the dynamic behavior of the Benchmark Active Controls Technology (BACT) wind-tunnel model for application to design and analysis of flutter suppression controllers. The model is formed by combining the equations of motion for the BACT wind-tunnel model with actuator models and a model of wind-tunnel turbulence. The primary focus of this paper is the development of the equations of motion from first principles using Lagrange's equations and the principle of virtual work. A numerical form of the model is generated using values for parameters obtained from both experiment and analysis. A unique aspect of the BACT wind-tunnel model is that it has upper-and lower-surface spoilers for active control. Comparisons with experimental frequency responses and other data show excellent agreement and suggest that simple coefficient-based aerodynamics are sufficient to accurately characterize the aeroelastic response of the BACT wind-tunnel model. The equations of motion developed herein have been used to assist the design and analysis of a number of flutter suppression controllers that have been successfully implemented. (Author) AbstractThis paper describes the formulation of a model of the dynamic behavior of the Benchmark Active Controls Technology (BACT) wind-tunnel model for application to design and analysis of flutter suppression controllers. The model is formed by combining the equations of motion for the BACT wind-tunnel model with actuator models and a model of wind-tunnel turbulence. The primary focus of this paper is the development of the equations of motion from first principles using Lagrange's equations and the principle of virtual work. A numerical form of the model is generated using values for parameters obtained from both experiment and analysis. A unique aspect of the BACT wind-tunnel model is that it has upper-and lower-surface spoilers for active control. Comparisons with experimental frequency responses and other data show excellent agreement and suggest that simple coefficient-based aerodynamics arc sufficient to accurately characterize the aeroelastic response of the BACT wind-tunnel model. The equations of motion developed herein have been used to assist the design and analysis of a number of flutter suppression controllers that have been successfully implemented.

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Section: Applying the Principle Of Virtual Workmentioning

confidence: 99%

mentioning

confidence: 99%

Modeling the Benchmark Active Control Technology wind-tunnel model for application to flutter suppression

Martin

1996

21st Atmospheric Flight Mechanics Conference

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“…Wind tunnel experiments were performed in order to obtain data to validate computational fluid dynamics codes, to verify aeroservoelastic design and analysis tools, and to provide an active control testbed. Classical, modern, and non-conventional controllers were tested with this system [13,14]. In the same period, experimental non-linear aeroelastic control studies using adaptive control schemes were performed [15].…”

Section: Introductionmentioning

confidence: 99%

A flutter suppression active controller

Marqui

Belo

Marques

2005

Proceedings of the Institution of Mechanical Engineers, Part G:

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Flutter is a dynamic aeroelastic instability that involves the interaction of aerodynamic, elastic, and inertial forces. This instability may occur in aircraft surfaces, like wings and tails, leading them to a divergent oscillatory motion. A classical two-degrees-of-freedom flutter is an interaction of bending and torsional modes of vibration of a structure. A flexible mount system has been developed for flutter tests with rigid wings in wind tunnels. This flexible mount has to provide a well-defined two-degrees-of-freedom system on which rigid wings encounter flutter. Active control schemes for flutter suppression can be tested using this experimental set-up. An aeroelastic model is formulated to simulate the aeroelastic behaviour of this system. The equations of motion are developed using Lagrange's equations and the Principle of Virtual Work, resulting in a state space representation. This is a convenient way to determine pitch and plunge time responses for several initial conditions and velocities. Using this model, a state feedback controller of the form u ¼ 2Kx is determined. The wind tunnel model is a rectangular wing with a NACA 0012 airfoil section and a trailing edge control surface as actuator. The main goal is to suppress flutter and to maintain the stability of the closed loop system.

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“…The BSCW was tested in the NASA Transonic Dynamics Tunnel (TDT) 16 as part of the Benchmark Models Program (BMP) 17,18,19 on a Pitch and Plunge Apparatus (PAPA) and later as a testbed for hardware checkout of the Oscillating TurnTable (OTT) system. 8 The model is shown mounted in the wind tunnel during testing on the OTT, Figure 2.…”

Section: Wind Tunnel Model and Facilitymentioning

confidence: 99%

Experimental data from the Benchmark SuperCritical Wing wind tunnel test on an oscillating turntable

Heeg

Piatak

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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The Benchmark SuperCritical Wing (BSCW) wind tunnel model served as a semi-blind testcase for the 2012 AIAA Aeroelastic Prediction Workshop (AePW). The BSCW was chosen as a testcase due to its geometric simplicity and flow physics complexity. The data sets examined include unforced system information and forced pitching oscillations. The aerodynamic challenges presented by this AePW testcase include a strong shock that was observed to be unsteady for even the unforced system cases, shock-induced separation and trailing edge separation. The current paper quantifies these characteristics at the AePW test condition and at a suggested benchmarking test condition. General characteristics of the model's behavior are examined for the entire available data set.

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Dynamic characteristics of a Benchmark models program supercritical wing

Cited by 17 publications

References 0 publications

Modeling the Benchmark Active Control Technology wind-tunnel model for application to flutter suppression

Modeling the Benchmark Active Control Technology wind-tunnel model for application to flutter suppression

A flutter suppression active controller

Experimental data from the Benchmark SuperCritical Wing wind tunnel test on an oscillating turntable

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