Active aeroelastic control of 2-D wing-flap systems operating in an incompressible flowfield and impacted by a blast pulse

Librescu, Liviu; Na, Sungsoo; Marzocca, Piergiovanni; Chung, Chanhoon; Kwak, Moon Kyu

doi:10.1016/j.jsv.2004.05.010

Cited by 45 publications

(21 citation statements)

References 19 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…(A.7) of Ref. [5] from the original implementation [4]. That is to say, in the amended version of this matrix, which can be obtained in a manner analogous to the derivation presented in Section 2, the component for the third row block would be strictly non-zero.…”

Section: Numerical Resultsmentioning

confidence: 99%

Corrigendum to: Discussion on "Active aeroelastic control of 2-D wing-flap systems operating in an incompressible flowfield and impacted by a blast pulse" by Librescu et al., Journal of Sound and Vibration 283 (3–5) (2005) 685–706 [Journal of Sound Vibration 332 (13) (2013) 3351–3358]

Mozaffari-Jovin

Firouz-Abadi

Roshanian

et al. 2014

Journal of Sound and Vibration

View full text Add to dashboard Cite

Section: Numerical Resultsmentioning

confidence: 99%

Corrigendum to: Discussion on "Active aeroelastic control of 2-D wing-flap systems operating in an incompressible flowfield and impacted by a blast pulse" by Librescu et al., Journal of Sound and Vibration 283 (3–5) (2005) 685–706 [Journal of Sound Vibration 332 (13) (2013) 3351–3358]

Mozaffari-Jovin

Firouz-Abadi

Roshanian

et al. 2014

Journal of Sound and Vibration

View full text Add to dashboard Cite

“…In the above equations, the underlined terms are associated with aerodynamic nonlinearities. Studies were conducted in [8,9] of the subcritical aeroelastic response of a two-dimensional lifting surface in a subsonic incompressible flow field that is exposed to an arbitrary explosive external excitation.…”

Section: Structural Aerodynamic Modeling Of Flapped Wing Systemmentioning

confidence: 99%

“…The explosive blast can be considered using a shock pulse length factor, r =1, while a sonic-boom pulse can be obtained by stipulating that 1 r ≠ [8,9]. …”

Section: Structural Aerodynamic Modeling Of Flapped Wing Systemmentioning

confidence: 99%

“…In this study, a robust control methodology using sliding mode control is implemented in order to: i) expand the flutter boundary and ii) decrease the response amplitude in various ranges of the flight speed. Librescu et al [9] among others implemented a flap torque to suppress flutter instability and enhance the subcritical aeroelastic response in 3DOF airfoils. Marzocca et al [6] implemented a combined linear and nonlinear proportional and velocity control scheme in conjunction with a flap; they revealed the possible expansion of the flutter boundary and lower response amplitude in the post-flutter range.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Sliding mode robust control of supersonic three degrees-of-freedom airfoils

Lee

Choo

et al. 2010

Int. J. Control Autom. Syst.

Self Cite

View full text Add to dashboard Cite

The robust aeroelastic control of a three-degrees-of-freedom (3DOF) linear and non-linear wing-flap system under sliding mode control (SMC) and operation in supersonic flight speeds is presented. Open-and closed-loop aeroelastic responses to blast and sonic-boom excitation in the wingflap system with uncertainty, as well as flutter analysis, are investigated along with the implementation of a Sliding Mode Observer (SMO). The effectiveness of control in reducing the amplitude of oscillation and preventing flutter instability is demonstrated. NOMENCLATURE a = Non-dimensional elastic axis position measured from the mid-chord, positive aft B = Ratio of the nonlinear to the linear pitching stiffness M, H, K= Mass, damping, and stiffness matrices b = Half-chord length e = Non-dimensional leading-edge flap position measured from the mid-chord, positive aft , a c F F = Aerodynamic and control load vectors , , h α β = Plunging, pitching, and flap displacements , I I α β = Mass moment of inertia per unit span of the wing-flap system about the elastic axis (EA) and of the flap about the flap axis (FA) of rotation, respectively , , h k k k α β = Stiffness parameters in plunging, torsional stiffness of the wing and flap about the EA , , ea L M H β = Total lift per span, aerodynamic moment, and hinge moment , , a ea l m h β = Non-dimensional aerodynamic lift, moment, and torque m = Airfoil mass per unit span M F , M f = Flutter speed and flight speed ρ ∞ = undisturbed density , U V ∞ = free stream speed and its nondimensional counterpart , r r α β = Non-dimensional radii of gyration of the wingflap system about EA , S x α α = Static unbalance about EA and its nondimensional counterpart , S x β β = Static unbalance about FA and its nondimensional counterpart , t τ = Time variable and its nondimensional counterpart κ = Polytropic gas coefficient

show abstract

“…Weisshaar [22] presented the new shape changes technology in wing surface area and controlled airfoil camber for morphing aircraft design to provide high performance. Librescu et al [23] presented and implemented the combined control law of active aero-elastic control in 2-D wing-flap systems to suppress the flutter instability. In this paper, the FGM shell might be embedded with magnetostrictive material to work as the adaptive structures; the maximum flutter value of center deflection amplitude with magnetostrictive FGM shell might be predicted and controlled into smaller value in supersonic air flow.…”

Section: Introductionmentioning

confidence: 99%

Effects of Varied Shear Correction on the Thermal Vibration of Functionally-Graded Material Shells in an Unsteady Supersonic Flow

Hong

2017

Aerospace

View full text Add to dashboard Cite

Abstract:A model is presented for functionally-graded material (FGM), thick, circular cylindrical shells under an unsteady supersonic flow, following first-order shear deformation theory (FSDT) with varied shear correction coefficients. Some interesting vibration results of the dynamics are calculated by using the generalized differential quadrature (GDQ) method. The varied shear correction coefficients are usually functions of FGM total thickness, power law index, and environment temperature. Two parametric effects of the environmental temperature and FGM power law index on the thermal stress and center deflection are also presented. The novelty of the paper is that the maximum flutter value of the center deflection amplitude can be predicted and occurs at a high frequency of applied heat flux for a supersonic air flow.

show abstract

Active aeroelastic control of 2-D wing-flap systems operating in an incompressible flowfield and impacted by a blast pulse

Cited by 45 publications

References 19 publications

Corrigendum to: Discussion on "Active aeroelastic control of 2-D wing-flap systems operating in an incompressible flowfield and impacted by a blast pulse" by Librescu et al., Journal of Sound and Vibration 283 (3–5) (2005) 685–706 [Journal of Sound Vibration 332 (13) (2013) 3351–3358]

Corrigendum to: Discussion on "Active aeroelastic control of 2-D wing-flap systems operating in an incompressible flowfield and impacted by a blast pulse" by Librescu et al., Journal of Sound and Vibration 283 (3–5) (2005) 685–706 [Journal of Sound Vibration 332 (13) (2013) 3351–3358]

Sliding mode robust control of supersonic three degrees-of-freedom airfoils

Effects of Varied Shear Correction on the Thermal Vibration of Functionally-Graded Material Shells in an Unsteady Supersonic Flow

Contact Info

Product

Resources

About