GLA and Flutter Suppression for a SensorCraft Class Concept Using System Identification

Penning, Kevin B.; Love, Michael; Zink, P. Scott; Wei, Paul; Marinez, Juan; Garza, Antonio De La

doi:10.2514/6.2008-7188

Cited by 18 publications

(4 citation statements)

References 5 publications

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“…(B.69). (1) xeq (2) xeq (3) xeq (4) xeq (5) xeq (6)]; del_eq = [xeq (7) xeq (8) xeq (9) (1) xeq (2) xeq (3) xeq (4) xeq (5) xeq (6)]; del_eq = [xeq (7) xeq (8) xeq ( …”

Section: Fig 23 Simplified Wing Modelunclassified

“…Penning et al [7] investigated GLA and flutter suppression for a Sensorcraft concept using system identification. They included flexible dynamics of wing bending for a high aspect ratio blended wing-body tailless aircraft and found that deriving control laws based on the combination system identification technology and flight control law development achieves GLA and flutter suppression.…”

mentioning

confidence: 99%

See 1 more Smart Citation

Gust Load Alleviation of an Aeroelastic System Using Nonlinear Control

Lucas

Valasek

Strganac

2009

50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…(B.69). (1) xeq (2) xeq (3) xeq (4) xeq (5) xeq (6)]; del_eq = [xeq (7) xeq (8) xeq (9) (1) xeq (2) xeq (3) xeq (4) xeq (5) xeq (6)]; del_eq = [xeq (7) xeq (8) xeq ( …”

Section: Fig 23 Simplified Wing Modelunclassified

mentioning

confidence: 99%

Gust Load Alleviation of an Aeroelastic System Using Nonlinear Control

Lucas

Valasek

Strganac

2009

50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…Typically, a 15% flutter free margin is required beyond the design envelope for both civil and military aircraft [6]. Recently, towards the development of SensorCraft technology, Northrop Grumman (NG) and Lockheed Martin Aeronautics (LM Aero) have recently demonstrated in a lab setting that by system identification and control technologies peak wing-root bending moments can be reduced by 50% through active gust load alleviation and a 20% flutter-free margin for body freedom flutter can be realized [7]. The state-of-the-art and the developments in the areas of high performance active wing technology, to achieve high-altitude cruise with longer endurance, are highlighted in reports originating from various research programs [8][9][10][11].…”

Section: Introductionmentioning

confidence: 99%

Optimization of Control Surface Parameters with Augmented Flutter Boundary Constraints

Singh

McDonough

2014

AIAA Atmospheric Flight Mechanics Conference

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This paper presents the formulation and solution strategy for estimating the optimal parameters associated with the control surfaces on aircraft wings towards active aeroelastic control. In this study the optimal sizing of control surfaces is investigated in order to achieve the flutter suppression and flutter boundary extension for a given flight envelop. The objective of the optimization process is to minimize the control gain norms (control force requirement) while satisfying the constraints on closed loop eigenvalues, which defines the extension of the open loop flutter boundary. The proposed optimization approach relies on modest size of matrices which consists of frequency response transfer functions that may be available from embedded sensors and actuators on the aircraft wings. This optimization process is demonstrated by using numerical receptances obtained from the aeroelastic models of wings having single and multiple control surfaces and by solving optimization problems associated with single input, multi-input state feedback and output feedback problems with augmented flutter boundary constraints. It is anticipated that such an approach may be useful in design phase of aircraft wings and may facilitate optimal placement and sizing of control surfaces, for a given wing configuration, towards enhanced flight performance.

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“…Figure 2b depicts the flying-wing and mount system in the final configuration used in Test 598 where GLA and body freedom flutter suppression control laws were successfully demonstrated. [5][6][7][8][9] The Joined-Wing SensorCraft (JWS) wind-tunnel tests built on the systems, procedures, and lessons learned from the flying-wing tests. As shown in figure 1, three tests of the JWS 10,11 were conducted.…”

Section: Introductionmentioning

confidence: 99%

Aeroservoelastic Wind-Tunnel Tests of a Free-Flying, Joined-Wing SensorCraft Model for Gust Load Alleviation

Scott

Castelluccio

Coulson

et al. 2011

52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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A team comprised of the Air Force Research Laboratory (AFRL), Boeing, and the NASA Langley Research Center conducted three aeroservoelastic wind-tunnel tests in the Transonic Dynamics Tunnel to demonstrate active control technologies relevant to large, flexible vehicles. In the first of these three tests, a full-span, aeroelastically scaled, windtunnel model of a joined-wing SensorCraft vehicle was mounted to a force balance to acquire a basic aerodynamic data set. In the second and third tests, the same wind-tunnel model was mated to a new, two-degree-of-freedom, beam mount. This mount allowed the fullspan model to translate vertically and pitch. Trimmed flight at -10% static margin and gust load alleviation were successfully demonstrated. The rigid body degrees of freedom required that the model be flown in the wind tunnel using an active control system. This risky mode of testing necessitated that a model arrestment system be integrated into the new mount. The safe and successful completion of these free-flying tests required the development and integration of custom hardware and software. This paper describes the many systems, software, and procedures that were developed as part of this effort. The balance and free flying wind-tunnel tests will be summarized. The design of the trim and gust load alleviation control laws along with the associated results will also be discussed.

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GLA and Flutter Suppression for a SensorCraft Class Concept Using System Identification

Cited by 18 publications

References 5 publications

Gust Load Alleviation of an Aeroelastic System Using Nonlinear Control

Gust Load Alleviation of an Aeroelastic System Using Nonlinear Control

Optimization of Control Surface Parameters with Augmented Flutter Boundary Constraints

Aeroservoelastic Wind-Tunnel Tests of a Free-Flying, Joined-Wing SensorCraft Model for Gust Load Alleviation

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