Chaotic motions of a two-dimensional airfoil with cubic nonlinearity in supersonic flow

Zhou, Liangqiang; Chen, Yushu; Chen, Fangqi

doi:10.1016/j.ast.2012.01.001

Cited by 22 publications

(14 citation statements)

References 24 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In the flight of reentry vehicle, large deformation of the elastic wing may possibly occur due to severe aerodynamic load, resulting in cubic hard spring nonlinearity of the wing structure (Zhou, Chen, & Chen, 2013). For supersonic and hypersonic flow, the piston theory is widely used to calculate the aerodynamics acting on a lifting surface (Zhou et al, 2013).…”

Section: Flutter Model Of Two-dimensional Wing With Propulsion Systemmentioning

confidence: 99%

See 1 more Smart Citation

Finite-time fault-tolerant control for flutter of wing

Gao

Cai

Nan

2016

Control Engineering Practice

View full text Add to dashboard Cite

Section: Flutter Model Of Two-dimensional Wing With Propulsion Systemmentioning

confidence: 99%

“…For supersonic and hypersonic flow, the piston theory is widely used to calculate the aerodynamics acting on a lifting surface (Zhou et al, 2013). Without considering structural damping, applying the piston theory, substituting Eq.…”

Section: Flutter Model Of Two-dimensional Wing With Propulsion Systemmentioning

confidence: 99%

Finite-time fault-tolerant control for flutter of wing

Gao

Cai

Nan

2016

Control Engineering Practice

View full text Add to dashboard Cite

“…Piston theory is widely applied in calculating aerodynamic force acting on lifting surface in supersonic flow. 24 Employing piston theory, the aerodynamic force and moment acting on airfoil can be described as where M∞ is the Mach number; γ¯ is the aerodynamic correction factor, γ¯=M∞M∞ 2-1; κ is the ratio of specific heat; and x0 is the nondimensional distance from leading edge to elastic axis.…”

Section: Airfoil Flutter Model and The Ftc Problemmentioning

confidence: 99%

“…Without concerning about structural damping, the aeroelastic equation of two-dimensional airfoil system can be deduced by Lagrange method, as expressed below 24 where q(t)=[h(t)θ(t)] T is the generalized displacement vector; A∼, B∼, C∼ and D∼ are the inertia, aerodynamic damping, aerodynamic stiffness, and structural stiffness matrices, respectively; and u ( t ) = [ δ LEout , δ LEin ] T is the control input. Parameters in equation (6) can be expressed as …”

Section: Airfoil Flutter Model and The Ftc Problemmentioning

confidence: 99%

A finite-time H-infinite adaptive fault-tolerant controller considering time delay for flutter suppression of airfoil flutter

Gao

Chen

Han

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

To suppress airfoil flutter, a lot of control methods have been proposed, such as classical control methods and optimal control methods. However, these methods did not consider the influence of actuator faults and control delay. This paper proposes a new finite-time H∞ adaptive fault-tolerant flutter controller by radial basis function neural network technology and adaptive fault-tolerant control method, taking into account actuator faults, control delay, modeling uncertainties, and external disturbances. The theoretic section of this paper is about airfoil flutter dynamic modeling and adaptive fault-tolerant controller design. Lyapunov function and linear matrix inequality are employed to prove the stability of the proposed control method of this paper. The numeral simulation section further proves the effectiveness and robustness of the proposed control algorithm of this paper.

show abstract

“…The numerical modeling of supersonic flow around the airfoils has been the topic of wide research, in the engineering applications [3]. The combination of analytical and numerical methods is conceivable by study of chaotic motions [4].…”

Section: Introductionmentioning

confidence: 99%

Modeling and Experimentation of a Supersonic Flow Around an Airfoil

Naamane¹,

Hasnaoui²

2019

MMC_B

View full text Add to dashboard Cite

The object of this paper is the modeling a supersonic flow of inviscid fluid around a dihedral airfoil. Based on the thin airfoils theory and the non-dimensional stationary Steichen equation of a two-dimensional supersonic flow in isentropic evolution, we obtain a solution for the downstream velocity potential of the oblique shock at the second order of relative thickness. This result has been dealt by the asymptotic analysis and characteristics method. In order to validate our model, the results are discussed in comparison with theoretical and experimental results. Indeed, firstly, the comparison of the results of our model, has shown that they are quantitatively acceptable compared to the existing theoretical results. Finally, an experimental study was conducted using the AF300 supersonic wind tunnel. In this experiment, we have considered the incident upstream Mach number over a symmetrical dihedral airfoil wing. The validation and the accuracy of the results support our model.

show abstract

Chaotic motions of a two-dimensional airfoil with cubic nonlinearity in supersonic flow

Cited by 22 publications

References 24 publications

Finite-time fault-tolerant control for flutter of wing

Finite-time fault-tolerant control for flutter of wing

A finite-time H-infinite adaptive fault-tolerant controller considering time delay for flutter suppression of airfoil flutter

Modeling and Experimentation of a Supersonic Flow Around an Airfoil

Contact Info

Product

Resources

About