Flutter Analysis of Mission-Adaptive Wing with Variable Camber Continuous Trailing Edge Flap

Nguyen, Nhan T.; Ting, Eric B.; Nguyen, Daniel; Trinh, Khanh

doi:10.2514/6.2014-0839

Cited by 27 publications

(16 citation statements)

References 7 publications

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“…In a previous study, a flutter analysis was conducted to examine the effect of increased flexibility of the GTM wing. 6 The baseline wing stiffness of the GTM is reduced by 50%. This reduced-stiffness GTM wing is referred to as the Elastic Shaped Aircraft Concept (ESAC) wing for differentiation.…”

Section: Fig 3 -Gtm Wing Configured With the Variable Camber Continumentioning

confidence: 99%

A Multi-Objective Flight Control Approach for Performance Adaptive Aeroelastic Wing

Nguyen

Tal

2015

56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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As aircraft wings become much more flexible due to the use of lightweight composites material, adverse aerodynamics at off-design performance can result from changes in wing shapes due to aeroelastic deflections. Increased drag, hence more fuel burn, is a potential consequence. Without means for aeroelastic compensation, the benefit of weight reduction from the use of lightweight material could be negated by less optimal aerodynamic performance at off-design. Performance Adaptive Aeroelastic Wing (PAAW) technology can potentially address these technical challenges for future flexible wing transports. PAAW technology leverages multidisciplinary solutions to maximize the aerodynamic performance payoff of future adaptive wing design, while addressing simultaneously operational constraints that can prevent the aerodynamic performance from being realized. These operational constraints include reduced aeroelastic stability margins, increased airframe responses to gust and maneuver loads, pilot handling qualities, and ride qualities. All of these constraints while seeking the maximum aerodynamic performance present themselves as a multi-objective flight control solution. The paper presents a multi-objective flight control approach based on a drag-cognizant optimal control method. A concept of virtual control, which was previously introduced, is implemented to address the pair-wise flap motion constraints imposed by the elastomer material. This method is shown to be able to satisfy the constraints. Real-time drag minimization control is considered to be an important consideration for PAAW technology. Drag minimization control has many technical challenges such as sensing and control. An initial outline of a real-time drag minimization control is proposed and will be further investigated in the future. A simulation study of a multi-objective flight control for a flight path angle command with aeroelastic mode suppression and drag minimization demonstrates the effectiveness of the proposed solution.

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Section: Fig 3 -Gtm Wing Configured With the Variable Camber Continumentioning

confidence: 99%

A Multi-Objective Flight Control Approach for Performance Adaptive Aeroelastic Wing

Nguyen

Tal

2015

56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…Both the engine mass and thrust can contribute to the aeroelasticity. 7 The propulsive force and moment vector are expressed in the reference frame D as…”

Section: A Propulsive Forces and Momentsmentioning

confidence: 99%

Aeroelasticity of Axially Loaded Aerodynamic Structures for Truss-Braced Wing Aircraft

Nguyen

Ting

Lebofsky

2015

56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This paper presents an aeroelastic finite-element formulation for axially loaded aerodynamic structures. The presence of axial loading causes the bending and torsional sitffnesses to change. For aircraft with axially loaded structures such as the truss-braced wing aircraft, the aeroelastic behaviors of such structures are nonlinear and depend on the aerodynamic loading exerted on these structures. Under axial strain, a tensile force is created which can influence the stiffness of the overall aircraft structure. This tension stiffening is a geometric nonlinear effect that needs to be captured in aeroelastic analyses to better understand the behaviors of these types of aircraft structures. A frequency analysis of a rotating blade structure is performed to demonstrate the analytical method. A flutter analysis of a truss-braced wing aircraft is performed to analyze the effect of geometric nonlinear effect of tension stiffening on the flutter speed. The results show that the geometric nonlinear tension stiffening effect can have a significant impact on the flutter speed prediction. In general, increased wing loading results in an increase in the flutter speed. The study illustrates the importance of accounting for the geometric nonlinear tension stiffening effect in analyzing the truss-braced wing aircraft.

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“…Numerous technologies have been investigated to address this potential. Recently, a new theme has emerged where wing flexibility is leveraged for shape optimization in order to reduce induced drag [1][2][3][4]. However, this requires precise and reliable measurements of wing bending and torsion in real-time.…”

Section: Introductionmentioning

confidence: 99%

Analysis of LPFG sensor systems for aircraft wing drag optimization

Kazemi¹,

Ishihara

2014

SPIE Proceedings

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In normal fiber, the refractive indices of the core and cladding do not change along the length of the fiber; however, by inducing a periodic modulation of refractive index along the length in the core of the optical fiber, the optical fiber grating is produced. This exhibits very interesting spectral properties and for this reason we propose to develop and integrate a distributed sensor network based on long period fiber gratings (LPFGs) technology which has grating periods on the order of 100 µm to 1 mm to be embedded in the wing section of aircraft to measure bending and torsion in real-time in order to measure wing deformation of commercial airplanes resulting in extensive benefits such as reduced structural weight, mitigation of induced drag and lower fuel consumption which is fifty percent of total cost of operation for airline industry.Fiber optic sensors measurement capabilities are as vital as they are for other sensing technologies, but optical measurements differ in important ways. In this paper we focus on the testing and aviation requirements for LPFG sensors. We discuss the bases of aviation standards for fiber optic sensor measurements, and the quantities that are measured.Our main objective is to optimize the design for material, mechanical, optical and environmental requirements. We discuss the analysis and evaluation of extensive testing of LPFG sensor systems such as attenuation, environmental, humidity, fluid immersion, temperature cycling, aging, smoke, flammability, impact resistance, flexure endurance, tensile, vitiation and shock.

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Flutter Analysis of Mission-Adaptive Wing with Variable Camber Continuous Trailing Edge Flap

Cited by 27 publications

References 7 publications

A Multi-Objective Flight Control Approach for Performance Adaptive Aeroelastic Wing

A Multi-Objective Flight Control Approach for Performance Adaptive Aeroelastic Wing

Aeroelasticity of Axially Loaded Aerodynamic Structures for Truss-Braced Wing Aircraft

Analysis of LPFG sensor systems for aircraft wing drag optimization

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