Effects of oscillating shock waves on the dynamics of fluttering panels

Udrescu, Radu

doi:10.2514/6.2001-1669

Cited by 1 publication

(1 citation statement)

References 4 publications

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“…From the time point of view, this was the earliest case of structural failure due to flutter 1 . The crash of the F‐117A stealth fighter in the 1990s was caused by the destruction of the structure due to the aeroelastic flutter of the aircraft 2 . Flutter instability can jeopardize aircraft structures and their flight performance.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic analysis and flutter control of wings and panels: A review

Chai

Gao

Ankay

et al. 2021

Int Journal of Mech Sys Dyn

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Flutter is a self-excited vibration under the interaction of the inertial force, aerodynamic force, and elastic force of the structure. After the flutter occurs, the aircraft structures will exhibit limit cycle oscillation, which will cause catastrophic accidents or fatigue damage to the structures. Therefore, it is of great theoretical and practical significance to study the aeroelastic characteristics and flutter control for improving the aeroelastic stability of aircraft structures. This paper reviews the recent advances in aeroelastic analysis and flutter control of wings and panel structures. The mechanism of aeroelastic flutter of wings and panels is presented. The research methods of aeroelastic flutter for different structures developed in recent years are briefly summarized. Various control strategies including the linear and nonlinear control algorithms as well as the active flutter control results of wings and panels are presented. Finally, the paper ends with conclusions, which highlight challenges of the development in aeroelastic analysis and flutter control, and provide a brief outlook on the future investigations. This study aims to present a comprehensive understanding of aeroelastic analysis and flutter control. It can also provide guidance on the design of new wings and panel structures for improving their aeroelastic stability.

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Section: Introductionmentioning

confidence: 99%