Hypersonic flutter and flutter suppression system of a wind tunnel model

Xuan, Chuanwei; Jing, Han; Zhang, Bing; Yun, Haiwei; Chen, Xiaomao

doi:10.1016/j.cja.2019.02.009

Cited by 9 publications

(4 citation statements)

References 21 publications

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“…Both active control method and passive control method can be used to improve thermal flutter behavior [11]. Smart materials [12,13], advanced control techniques [14], and viscoelastic materials [15] are used for flutter control.…”

Section: Introductionmentioning

confidence: 99%

Thermal Aeroelastic Tailoring for Laminated Panel with Lamination Parameters and JAYA Algorithm

Jin

Zheng

Wei

2022

International Journal of Aerospace Engineering

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This work investigates thermal aeroelastic tailoring of a laminated composite panel with a lamination parameter-based method. Equivalent membrane and bending coefficients of thermal expansions for symmetric laminated panel are derived and represented with lamination parameters using Classical Laminated Plate Theory. The relationship between thermal flutter behavior and lamination parameters is examined. The optimization process is split into two stages. In the first stage, lamination parameters and laminate thicknesses are as design variables to minimize the structure mass, subject to thermal flutter behavior and feasible region constraints of lamination parameters. In the second-stage, instead of using conventional genetic algorithm, the enhanced JAYA method is extended to search the laminate configuration to target the optimal lamination parameters. The effectiveness of the presented method is demonstrated through a thermal aeroelastic tailoring problem.

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Section: Introductionmentioning

confidence: 99%

Thermal Aeroelastic Tailoring for Laminated Panel with Lamination Parameters and JAYA Algorithm

Jin

Zheng

Wei

2022

International Journal of Aerospace Engineering

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“…The results showed that, as the wall temperature increases, the starting position of the separation point moves forward, and the length of the separation bubble increases. Xuan et al 18 studied hypersonic flutter and a flutter suppression system of a thin flat rudder model, and the flutter suppression system was developed and validated. Ye et al 19 studied effects of dynamic aeroelasticity on the performance of the two-dimensional inlet were also studied based on the mode method, and the structural dynamics was analyzed based on the modal method, which ignored the influence of geometric nonlinearity.…”

Section: Introductionmentioning

confidence: 99%

“…At the same time, the effects of static aerothermoelastic deformation on the shock wave structure, the separation vortex structure as well as the performance parameters of the threedimensional hypersonic inlet was studied based on the computational fluid dynamics and the computational solid dynamics (CFD/CSD) coupling method. 20 From the perspective of the numerical simulation method, there are two main problems in the current work regarding the aerothermoelasticity of the inlet: (1) In order to reduce the computational amount and the complexity of the problem, simple two-dimensional models were frequently used to conduct structural dynamics analysis based on the modal method; [16][17][18][19] (2) A considerable amount of work focus on the static aeroelastic analysis of the inlet, [14][15][16][17]21 but the dynamic aeroelastic analysis is rarely reported. Moreover, some critical facts and problems exist in the practical engineering as follows: (1) The inlet model is three-dimensional in reality.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of the influence of aerothermoelastic dynamic response on the performance of the three-dimensional hypersonic inlet

Feng

Liu

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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The influence of aerothermoelastic dynamic response on the performance of the three-dimensional hypersonic inlet is investigated in this paper. A dynamic aerothermoelastic analysis framework is developed. The reliability of the framework is verified. The effects of aerodynamic heating on the dynamic response, the effects of the aerothermoelastic dynamic response of the inlet on the flow field structure, and the performance parameters are studied. The results indicate that the static deformation of the leading edge structure is large while the vibration amplitude is small. Meanwhile, the vibration amplitude of the trailing edge structure is larger. The aerothermoelastic dynamic response changes the shock wave structure near the exit, strengthens the shock wave intensity, increases the length of the separated region, and changes the flow field of the exit. Simultaneously, the flow field structure also experiences obvious dynamic changes at different moments. The dynamic response increases the time-averaged flow coefficient, reduces the time-averaged total pressure recovery coefficient, and improves the time-averaged reverse pressure ratio. At the same time, the dynamic response leads to the fluctuation of performance parameters, especially the large fluctuation range of the reverse pressure ratio at the exit.

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“…The most important limitation is that it is impossible to carry out flight testing in the initial design stage without detailed validation and verification using other methods. Therefore, wind-tunnel testing has became a very important method for flutter investigations (3,4) . Wind-tunnel tests can take into account the effects of aerodynamic forces, but the aeroelastic test model must be designed and scaled carefully due to the size of the test section of the wind tunnel.…”

Section: Introductionmentioning

confidence: 99%

A generalised force equivalence-based modelling method for a dry wind-tunnel flutter test system

Zhang¹,

Gao²,

Wang³

et al. 2021

Aeronaut. j.

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Dry wind-tunnel (DWT) flutter test systems model the unsteady distributed aerodynamic force using various electromagnetic exciters. They can be used to test the aeroelastic and aeroservoelastic stability of smart aircraft or high-speed flight vehicles. A new parameterised modelling method at the full system level based on the generalised force equivalence for DWT flutter systems is proposed herein. The full system model includes the structural dynamic model, electromechanical coupling model and fast aerodynamic computation model. An optimisation search method is applied to determine the best locations for measurement and excitation by introducing Fisher’s information matrix. The feasibility and accuracy of the proposed system-level numerical DWT modelling method have been validated for a plate aeroelastic model with four exciters/transducers. The effects of key parameters including the number of exciters, the control time delay, the noise interference and the electrical parameters of the electromagnetic exciter model have also been investigated. The numerical and experimental results indicate that the proposed modelling method achieves good accuracy (with deviations of less than 1.5% from simulations and 4.5% from experimental test results for the flutter speed) and robust performance even in uncertain environments with a 10% noise level.

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Hypersonic flutter and flutter suppression system of a wind tunnel model

Cited by 9 publications

References 21 publications

Thermal Aeroelastic Tailoring for Laminated Panel with Lamination Parameters and JAYA Algorithm

Thermal Aeroelastic Tailoring for Laminated Panel with Lamination Parameters and JAYA Algorithm

Numerical investigation of the influence of aerothermoelastic dynamic response on the performance of the three-dimensional hypersonic inlet

A generalised force equivalence-based modelling method for a dry wind-tunnel flutter test system

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