Hypersonic Aeroelastic Response of Elastic Boundary Panel Based on a Modified Fourier Series Method

Zhou, Xiyue; Wang, Lifeng; Jiang, Jintao; Su, Zhu

doi:10.1155/2019/5164026

Cited by 6 publications

(4 citation statements)

References 28 publications

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“…Introducing these nondimensional variables into the coupled aeroelastic panel system of Equations ( 1) and (2) gives the dimensionless equations…”

Section: Governing Equationsmentioning

confidence: 99%

“…There have been some accidents resulting from panel flutter since flight vehicles reached supersonic speeds in the 1950s [1]. Consequently, panel flutter problems have been widely studied by aeroelastic researchers for decades [2][3][4][5][6]. Because of the geometric nonlinearity of panel vibration, panel flutter usually exhibits limited amplitude vibration, which can lead to fatigue failure, rather than divergent vibration.…”

Section: Introductionmentioning

confidence: 99%

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Passive Suppression of Panel Flutter Using a Nonlinear Energy Sink

Jian

Xia

2020

International Journal of Aerospace Engineering

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A nonlinear energy sink (NES) is used to suppress panel flutter. A nonlinear aeroelastic model for a two-dimensional flat panel with an NES in supersonic flow is established using the Galerkin method. First-order piston aerodynamic theory is adopted to build the aerodynamic load. The effects of NES parameters on flutter boundaries of the panel are investigated using Lyapunov’s indirect method. The mechanism of the NES suppression of panel flutter is studied through energy analysis. Effects of NES parameters on aeroelastic responses of the panel are obtained, and a design technique is adopted to find a suitable combination of parameter values of the NES that suppresses the panel flutter effectively. Results show that the NES can increase or reduce the onset dynamic pressure of the panel flutter and it can reduce the aeroelastic response amplitude effectively within a certain range of dynamic pressure behind the onset dynamic pressure. The installation position of the NES depends on the direction of the airflow. The robust characteristics should be considered to find the suitable combination of parameter values of the NES.

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“…Introducing these nondimensional variables into the coupled aeroelastic panel system of Equations ( 1) and (2) gives the dimensionless equations…”

Section: Governing Equationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Passive Suppression of Panel Flutter Using a Nonlinear Energy Sink

Jian

Xia

2020

International Journal of Aerospace Engineering

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“…However, in the majority of practical applications, these boundary conditions are not accurate. It is essential to study the dynamic characteristics of bi-stable structures under elastic support boundary conditions [18][19][20][21][22][23][24][25][26][27]. Also, both asymmetric and antisymmetric stacking sequences are the most common laminates; they should receive more attention and research.…”

Section: Introductionmentioning

confidence: 99%

Free Vibration Analysis of Trapezoidal Bi-Stable Laminates Supported at the Elastic Midpoint of the Median Line

Xu,

Hao,

Zhang

et al. 2023

Mathematics

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This study investigates the natural vibration of trapezoidal bi-stable laminates (TBL) with elastic supports at the midpoints of the median lines. Configuration of the midplane of the TBL is expressed by a polynomial with 17 parameters. Then, the first order shear deformation theory, curing temperature, and nonlinear strain displacement relations combining energy principles are applied to obtain the bi-stable shapes numerically. Three translational springs and two rotational springs are added at the midpoint of the median line in the trapezoidal bi-stable laminate to acquire elastic point supports. And, by varying the stiffness of the springs, arbitrary elastic point support boundary conditions can be achieved. Chebyshev polynomials are applied to characterize the mode shape function of the TBL. The vibration mode functions of the TBL are mapped to a square area under the new coordinate system by using the coordinate mapping method. Furthermore, the effects of geometry, layup sequence, and spring stiffness on the natural vibrations of the TBL are analyzed, which provides a reference for research in this field. The innovation and highlights lie in the following: (1) the natural frequencies and modes of trapezoidal bi-stable plates are solved; (2) arbitrary elastic support is achieved by a set of artificial springs; (3) the influences of spring stiffness, layer sequence, and trapezoidal base angle on the natural vibration of a trapezoidal bi-stable plate are studied.

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“…Ma et al [6] proposed a parameter estimation method that can calculate nonlinear vibration characteristics of missiles during exercise. Zhou et al [7] proposed an analytical method to directly obtain the aeroelastic time domain response of the elastic boundary panel. Pan et al [8] carried out a number of investigations into the effect of continuous gusts on the initial disturbance of the airborne missile's horizontal backward derailment on large transport aircraft.…”

Section: Introductionmentioning

confidence: 99%

Influence of External Factors on Airborne Missile’s Horizontal Backward Launching

Pan

Jiang

et al. 2021

International Journal of Aerospace Engineering

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This paper studies the influence of different external disturbance factors on the horizontal backward separation of airborne missiles on large transport aircraft. The method of comparison with experiment was adopted to verify the accuracy of the finite element model during the ejection process. By comparing the finite element model, it was confirmed that the all rigid body model and partly rigid body model are inaccurate in calculating the pitch angle and pitch velocity of the missile separation. Finally, the influences of ejection force, random vibration, and missile loading position on the ejection process are analyzed. The analysis found that the ejection force and the sliding distance will increase the vibration of the launching platform, therefore increase the separation pitch angle and the pitch velocity of the missile, but the influence of random vibration on platform is much greater than the other two factors, and it will also introduce randomness into the movement of the missile.

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Hypersonic Aeroelastic Response of Elastic Boundary Panel Based on a Modified Fourier Series Method

Cited by 6 publications

References 28 publications

Passive Suppression of Panel Flutter Using a Nonlinear Energy Sink

Passive Suppression of Panel Flutter Using a Nonlinear Energy Sink

Free Vibration Analysis of Trapezoidal Bi-Stable Laminates Supported at the Elastic Midpoint of the Median Line

Influence of External Factors on Airborne Missile’s Horizontal Backward Launching

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