The X-53 A Summary of the Active Aeroelastic Wing Flight Research Program

Pendleton, Ed; Flick, Pete; Paul, Donald B.; Dryden, Nasa; Griffin, Kenneth

doi:10.2514/6.2007-1855

Cited by 45 publications

(21 citation statements)

References 14 publications

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“…The control power increment with increased wing flexibility was proved by Pendleton, Bessette, Field, Griffin, and Miller (2000), Pendleton et al (2007) and Pendleton, Lee, and Wasserman (1992). Multiple control surfaces were mounted on an F-16 Agile Falcon and a stiffness-reduced F/A-18.…”

Section: Introductionmentioning

confidence: 99%

Active aeroelastic wing application on a forward swept wing configuration

Xue

2019

Engineering Applications of Computational Fluid Mechanics

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Active aeroelastic wing is introduced to benefit the forward swept wing (FSW) aeroelastic performance owing to the FSW's elaborate aeroelastic problem.In this research, a computational aeroelastic (CAE) code was developed to conduct aeroelastic simulations, which presents challenges of data interpolation and flow capturing since torsional deformations instead of bending dominate in FSW deformation and separations on FSW occur earlier due to the boundary layer accumulation. Two simulations are conducted to verify the adaptability and accuracy of CAE method on FSW. CAE simulations are conducted on a straight FSW with control surfaces in two phases. The results from first phase obtained at Mach 0.8 demonstrate that negative deflection of LE and positive deflection of TE can effectively depress the torsion angle and root-bending moment at identical lift. Deflections of LE 0°, TE +20°can reduce LE and TE wingtip displacement by 36.53% and 39.87%, respectively, resulting in 78.97% decline of torsion angle. The second-phase calculations, conducted at Mach 0.9 at different dynamic pressures, illustrate depression of FSW torsion and deformation by LE and TE downward deflection. The LE and TE control effectiveness is always beyond 1 and the control power of the FSW increases with increasing dynamic pressure.

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Section: Introductionmentioning

confidence: 99%

Active aeroelastic wing application on a forward swept wing configuration

Xue

2019

Engineering Applications of Computational Fluid Mechanics

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“…The wing morphing technique may provide further enhancements in aircraft performance to satisfy various demanding criteria for diverse missions. In the literature Nguyen et al, 2015;Pendleton et al, 2007;, it is reported that the morphing technology can enhance aerodynamic characteristics and reduce structural weight and acoustic noise of aircraft. Moreover, wing morphing may reinforce flight safety by improving stall characteristics and gust load alleviation.…”

Section: Introduction 11 Background and Brief Historical Reviewmentioning

confidence: 99%

“…One example of modern morphing aircraft development programs is the Active Aeroelastic Wing (AAW) research program (Pendleton et al, 2007). The morphing technique was implemented to a full-scale F/A-18 fighter aircraft (see Natsuki TSUSHIMA* and Masato TAMAYAMA* *Aeronautical Technology Directorate, Japan Aerospace Exploration Agency 6-13-1 Osawa, Mitaka, Tokyo 181-0015, Japan E-mail: tsushima.natsuki@jaxa.jp Tsushima and Tamayama, Mechanical Engineering Reviews, Vol.6, No.2 (2019) [DOI: 10.1299/mer.19-00197] Fig.…”

Section: Introduction 11 Background and Brief Historical Reviewmentioning

confidence: 99%

Recent researches on morphing aircraft technologies in Japan and other countries

Tsushima

Tamayama

2019

Mechanical Engineering Reviews

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Morphing aircraft technology has recently gained attention of many research groups by its potential for aircraft performance improvement and economic flight. Although the performance of conventional control surfaces is usually compromised in off-design flight conditions, the morphing technique may achieve optimal flight performance in various operations by to adaptively altering the wing shape during flight. This paper aims to provide a comprehensive review on morphing aircraft/wing technology, including morphing mechanisms or structures, skins, and actuation techniques as element technologies. Moreover, experimental and numerical studies on morphing technologies applying those elemental technologies are also introduced. Recent research on these technologies are particularly focused on in this paper with comparisons between developments in Japan and other countries. Although a number of experimental and numerical studies have been conducted by various research groups, there are still various challenges to overcome in individual elemental technologies for a whole morphing aircraft or wing systems. This review helps for researchers working in the field related to morphing aircraft technology to sort out current developments for morphing aircraft.

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“…1 In the 2000's, the Active Aeroelastic Wing research program also investigated a similar technology to induce wing twist in order to improve roll maneuverability of a modified F/A-18 aircraft. 2 Wing shaping control concepts for drag reduction are being studied by NASA to leverage wing flexibility for aerodynamic performance. 3,4 By re-twisting a flexible wing and using variable camber aerodynamic flight control surfaces, aircraft wings can have the mission-adaptive capability to optimize L/D throughout a flight envelope.…”

Section: Introductionmentioning

confidence: 99%

Large Deflection Aeroelasticity and Aeroelastic Lifting Line Theory for Examination of Aerodynamic Effects and Nonlinear Limit Cycle Oscillations

Nguyen

Ting

2018

2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This paper investigates the effects of nonlinear large deflection bending on the aerodynamic performance and aeroelasticity of a high aspect ratio flexible wing. A nonlinear large deflection theory is developed for aeroelasticity to account for large deflection bending. An analysis is conducted to compare the nonlinear bending theory with the linear bending theory. The results show that the nonlinear bending theory is length-preserving whereas the linear bending theory causes a non-physical effect of lengthening of the wing structure under the no axial load condition. A modified lifting line theory is developed to compute the lift and drag coefficients of a wing structure undergoing a large bending deflection. The lift and and drag coefficients are more accurately estimated by the nonlinear bending theory due to its length-preserving property. The nonlinear bending theory yields a lower lift and higher induced drag than the linear bending theory. The nonlinear large deflection bending also can affect the structural dynamics of a high aspect ratio wing significantly. Limit cycle oscillations are a nonlinear phenomenon which arises from geometric nonlinearity and other sources of nonlinearities. Large deflection can manifest itself in limit cycle oscillations whereby linear flutter behaviors can result in an increase in the bending deflection up to a point where the geometric nonlinearity due to the large deflection begins to set in that results in limit cycle oscillations.

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The X-53 A Summary of the Active Aeroelastic Wing Flight Research Program

Cited by 45 publications

References 14 publications

Active aeroelastic wing application on a forward swept wing configuration

Active aeroelastic wing application on a forward swept wing configuration

Recent researches on morphing aircraft technologies in Japan and other countries

Large Deflection Aeroelasticity and Aeroelastic Lifting Line Theory for Examination of Aerodynamic Effects and Nonlinear Limit Cycle Oscillations

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