Influence of membrane wing active deformation on the aerodynamic performance of an aircraft model

Feng, Siyuan; Guo, Qinfeng; Wang, Jinjun; Xu, Yang

doi:10.1007/s11431-022-2128-9

Cited by 7 publications

(3 citation statements)

References 26 publications

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“…In recent years, with the rapid development of the aviation industry, the study of wing aerodynamic characteristics has become one of the hotspots in the aviation field 2,3 .…”

Section: Introductionmentioning

confidence: 99%

Analysis of aerodynamic characteristics of a certain aircraft wing structure at different angles of attack

HU,

YIN,

LIU

2024

Ninth International Symposium on Sensors, Mechatronics, and Automation System (ISSMAS 2023)

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The aerodynamic performance of a certain aircraft wing structure at different angles of attack was analyzed using FLUENT finite element software. According to simulation, the lower surface of the wing is a high-pressure zone, while the upper surface is a low-pressure zone. As the angle of attack increases, the high-pressure zone will move towards the leading edge of the wing, while the trailing edge of the wing slowly forms a low-pressure zone; At the same time, the airflow accelerates on the surface of the wing, causing a decrease in pressure and an increase in lift. This provides a theoretical basis for further optimizing the wing structure.

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“…In recent years, with the rapid development of the aviation industry, the study of wing aerodynamic characteristics has become one of the hotspots in the aviation field 2,3 .…”

Section: Introductionmentioning

confidence: 99%

Analysis of aerodynamic characteristics of a certain aircraft wing structure at different angles of attack

HU,

YIN,

LIU

2024

Ninth International Symposium on Sensors, Mechatronics, and Automation System (ISSMAS 2023)

View full text Add to dashboard Cite

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“…Feng et al. (2022) applied MFC actuators on a simplified aircraft model with membrane wings. Therefore, based on the flexible membrane airfoil and MFC technique, this study will apply active control onto the airfoil leeward surface covered with a flexible membrane skin.…”

Section: Introductionmentioning

confidence: 99%

“…He et al (2022) proposed novel ideas for active control of a membrane airfoil by controlling the membrane vibration frequency at specific chordwise locations for intensive actuation. Feng et al (2022) applied MFC actuators on a simplified aircraft model with membrane wings. Therefore, based on the flexible membrane airfoil and MFC technique, this study will apply active control onto the airfoil leeward surface covered with a flexible membrane skin.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamics and fluid–structure interaction of an airfoil with actively controlled flexible leeward surface

Guo

et al. 2023

J. Fluid Mech.

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Piezoelectric macro-fibre composite (MFC) actuators are employed onto the flexible leeward surface of an airfoil for active control. Time-resolved aerodynamic forces, membrane deformations and flow fields are synchronously measured at low Reynolds number (Re = 6 × 104). Mean aerodynamics show that the actively controlled airfoil can achieve lift-enhancement and drag-reduction simultaneously in the angle of attack range of 10° ≤ α ≤ 14°, where the rigid airfoil encounters stall. The maximum increments of lift and lift-to-drag ratio are 27.1 % and 126 % at the reduced actuation frequency of ${f^ + } = 3.52$ . The unsteady coupling features are further analysed at α = 12°, where the maximum lift-enhancement occurs. It is newly discovered that the membrane vibrations and flow fields are locked into half of the actuation frequency when ${f^ + } > 3$ . The shift of the dominant vibration mode from bending to inclining is the reason for the novel ‘half-frequency lock-in’ phenomenon. To the fluid–structure interaction, there are three characteristic frequencies for the actively controlled airfoil: $S{t_1} = 0.5{f^ + }$ , $S{t_2} = {f^ + }$ , and $S{t_3} = 1.5{f^ + }$ . Here, St1 and its harmonics (St2, St3) are coupled with the natural frequencies of the leading-edge shear layer, resulting in the generation of multi-scale flow structures and suppression of flow separation. The lift presents comparable dominant frequencies between St1 and St3, which means the instantaneous lift is determined by the flow structures of St1 and St3. The local membrane bulge and dent affect the instantaneous swirl strength of flow structures near the maximum vibration amplitude location, which is the main reason for the variation of instantaneous lift.

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Experimental investigations on structural improvement of morphing mechanism for nose cone of aerospace vehicle adopting a bionic redundant constraint strategy

Zhang

et al. 2023

Sci. China Technol. Sci.

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Influence of membrane wing active deformation on the aerodynamic performance of an aircraft model

Cited by 7 publications

References 26 publications

Analysis of aerodynamic characteristics of a certain aircraft wing structure at different angles of attack

Analysis of aerodynamic characteristics of a certain aircraft wing structure at different angles of attack

Aerodynamics and fluid–structure interaction of an airfoil with actively controlled flexible leeward surface

Experimental investigations on structural improvement of morphing mechanism for nose cone of aerospace vehicle adopting a bionic redundant constraint strategy

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