Parametric active aeroelastic control of a morphing wing using the receptance method

Liu, Haojie; Gao, Xiumin; Xiao, Wang

doi:10.1016/j.jfluidstructs.2020.103098

Cited by 6 publications

(5 citation statements)

References 40 publications

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“…In a subsonic flow regime, Raja and Upadhya 254 designed a piezoelectric control surface to enhance the flutter velocity of a composite wing model using theoretical and experimental methods. Liu et al 255 used the parametric active aeroelastic control method to suppress aeroelasitc vibrations and expand flutter bounds of a morphing wing, and a comparison between the open‐loop and the closed‐loop flutter bounds of the folding wing over the folding angle range of interest was carried out as shown in Figure 17. It can be found that the closed‐loop flutter bounds were increased by more than 13% in the most of the range of interest.…”

Section: Research Status Of Flutter Controlmentioning

confidence: 99%

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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: Research Status Of Flutter Controlmentioning

confidence: 99%

“…(A) Geometric information and local coordinate system of the folding wing, and (B) open‐loop and closed‐loop flutter boundaries of the folding wing. Reproduced with permission 255 . Copyright 2020, Elsevier…”

Section: Research Status Of Flutter Controlmentioning

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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“…Guo et al [10] analyzed the nonlinear vibration characteristics of a Z-shaped folded plate composed of three carbon-fiber composite plates through theoretical and experimental investigation. Liu et al [11] proposed a parametric active aeroelastic control of a folding wing, which is a promising concept of morphing wings, by integrating the parameterized aeroservoelastic model and the reacceptance-based control strategy.…”

Section: Introductionmentioning

confidence: 99%

Flutter Characteristics of a Modified Z-Shaped Folding Wing Using a New Non-Intrusive Model

Qi,

Wu,

Tian

2024

Aerospace

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Unmanned aerial vehicles (UAVs) with folding wings can serve in multiple mission profiles, usually accompanied by sudden changes in flight speed. These bring great challenges to the aeroelastic design of UAVs, especially in the calculation of flutter characteristics. This paper developed a new non-intrusive aeroelastic model to quickly calculate the flutter characteristics of Z-shaped folding wings at different folding angles. First, the original Z-shaped folding wing was designed to be enhanced. Beams and ribs were arranged inside each wing segment to enhance the structural strength performance. Control surfaces were arranged in the middle-wing and outer-wing to enhance the aerodynamic control performance. Second, a parametric aeroelastic model at any folding angle was reconstructed based on the input file of Nastran software for the flutter calculation of the folding wing in the unfolded state. Finally, the effects of parameters such as folding angle, hinge stiffness between different wing segments, and hinge stiffness of the control surfaces on the flutter characteristics of the folding wing were investigated. The results show that the enhancement scheme could significantly increase the flutter speed and flutter frequency of the folding wing. The hinge stiffness between each wing segment had a significant impact on the flutter characteristics of the folding wing, but flutter at the control surface basically did not occur.

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“…As a new solution, morphing aircraft can change their aerodynamic configuration to ensure optimal performance under various environmental conditions and mission requirements [1][2][3][4][5][6][7][8][9][10]. Since the wing is the main component of the aircraft to provide lift, the primary research object of the current morphing aircraft technology is the morphing wing [11][12][13][14][15][16][17][18][19][20]. Specifically, the variable-camber airfoil technology that can be used on morphing wings has obvious advantages in improving the aerodynamic performance and enhancing the efficiency of the aircraft, which makes it attract extensive attention, and it has gradually become a research hotspot [21][22][23][24][25][26][27][28][29][30][31].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Characteristics of Morphing Supercritical Airfoils for Aircraft with All-Stage High Performance

et al. 2022

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Morphing airfoil is a promising technology for future aircraft to realize all-stage high performance. In the present paper, a conceptual aircraft with morphing airfoil is proposed and the aerodynamic characteristics of three types of morphing airfoils (variable-camber airfoil, variable-chord airfoil, and the combination of both morphing styles) are numerically investigated. The baseline airfoil is RAE 2822 supercritical airfoil; the Reynolds-averaged Navier–Stokes method is adopted for numerical simulation of flow around airfoils, and the accuracy of the numerical simulation method is validated by comparing with experimental data. It is found that the variable-camber and -chord airfoil can not only improve the high lift characteristics at take-off stage, but also increase the lift-to-drag ratio at transonic cruise and low-speed task stages during which the required lift is continuously decreasing due to the consumption of fuel. These findings imply that aircraft with proper morphing airfoil can achieve all-stage high aerodynamic performance.

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Parametric active aeroelastic control of a morphing wing using the receptance method

Cited by 6 publications

References 40 publications

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

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

Flutter Characteristics of a Modified Z-Shaped Folding Wing Using a New Non-Intrusive Model

Aerodynamic Characteristics of Morphing Supercritical Airfoils for Aircraft with All-Stage High Performance

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