Flutter Control of a Quasi-three-dimensional Wing in Simplified Unsteady Flow using Forced Jet

Document Type : Dynamics, Vibrations, and Control

Authors

1 Ph.D. Candidate, Department of Aerospace Engineering, Science and Research Branch, Islamic Azad University, Tehran, Iran

2 Corresponding author: Associate Professor, Department of Aerospace Engineering, K. N, Toosi University of Technology, Tehran, Iran

3 Assistant Professor, Department of Aerospace Engineering, Science and Research Branch, Islamic Azad University, Tehran, Iran

Abstract

One of the special topics in the aeroelastic field is the flutter of the airplane wing at an index speed called the flutter speed, which, if this phenomenon is not controlled, there will be a possibility of destroying the structure (airplane wing). Various methods for wing control have been proposed in the last two decades. In the current research, two-way forced jet momentum embedded on the wing is used to control a pseudo three-dimensional wing with a simplified unsteady flow regime. The jet activation signal at the flutter speed is provided by the pulse width-pulse frequency modulator. The advantages of this modulator include its quasi-linear performance, high precision with the presence of fluctuations and flexibility. In this research, the double aeroelastic, non-reversible and rectangular (Hancock) wing model is considered, and the strip theory is used to develop the lift force during spinball. In the speed of the flutter ball, the swing of the wing is driven to damping by the jet activity, and according to the obtained aeroelastic graphs, satisfactory results have followed.

Highlights

  • Assumption of unsteady flow, quasi-three-dimensional wing and rectangular geometric.
  • A modulator is used to generate the signal and excite the thruster.
  • The flutter wing is controlled by bilateral jet.

Keywords

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References

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Aerospace Mechanics
Volume 20, Issue 1 - Serial Number 75
Serial No. 75, Spring
April 2024
Pages 45-58

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History

  • Receive Date: 15 April 2023
  • Revise Date: 30 April 2023
  • Accept Date: 16 August 2023
  • Publish Date: 15 April 2024

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