Low-noise wing structure based on acoustic soft material and aircraft

Abstract

The invention relates to the technical field of aircraft design, and discloses a low-noise wing structure based on an acoustic soft material and an aircraft, a porous acoustic soft material layer is arranged between a main wing and a high lift device (slat and flap), and the arrangement of the porous acoustic soft material combines the outer contours of the main wing and the high lift device. The outer contours of the main wing and the high-lift device are the same as those of the original main wing and the high-lift device, the aerodynamic shapes and aerodynamic performance of the original main wing and the high-lift device are not affected, the aerodynamic performance of the wing is not affected, meanwhile, the strength of an aerodynamic noise source of the wing can be further weakened, noise is absorbed in the sound transmission process, and the sound transmission efficiency is improved. Radiation noise generated when the high lift device is unfolded is remarkably reduced, and the flight comfort degree is improved. In addition, the main wing and the high lift device are simple in structure, easy to manufacture and apply and suitable for various aircrafts with fixed wings.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft design, and discloses a low-noise wing configuration based on acoustic soft material and an aircraft. BACKGROUND

[0002] During the flight of an aircraft, the complex flow of air on the surface of the main wing and its lift-increasing device (flap and aileron) often produces relatively large aerodynamic noise, especially during the take-off and landing stages of the aircraft. Such noise not only affects the flight comfort of the aircraft and causes noise pollution, but also the radiation noise during the take-off and landing stages is a key indicator for the noise airworthiness certification of the aircraft.

[0003] Publication No. CN103879551A discloses a method of using a slit wing cavity filling element, which changes the shape of the slit wing in a low-speed state, thereby weakening or shielding the main sound source area of the leading edge slit wing, so as to reduce the aerodynamic noise radiation level of the slit wing. Publication No. CN107010206A discloses a leading edge high-lift device and a method for reducing noise, which forms a device at the trailing edge area of the slit wing, which, after activation, can further extend the noise generation area downstream of the slit wing cavity and provide wing shielding for low-altitude flight noise. Publication No. CN115292818A discloses a three-section wing trailing edge side edge noise reduction scheme design with a special configuration baffle, which adds a strip-shaped baffle to one end of the flap towards the main wing root, changes the flow field pattern and the structure of the side edge vortex by reasonably designing the baffle configuration, delays the development process of the side edge vortex system, moves the fusion position of the vortex system backward, and makes the area where the vortex system fuses and breaks to produce pulsating pressure away from the flap suction surface, thereby achieving the effect of reducing noise without affecting the aerodynamic performance. Publication No. CN115783236A discloses a low-noise lift-increasing device for a wing and an aircraft, which uses a retractable module at the trailing edge of the slit wing, increases the chord length of the leading edge slit wing, and reduces the slit width between the leading edge slit wing and the fixed wing, thereby achieving the purpose of increasing lift, reducing resistance, and reducing slit wing noise.

[0004] The above-mentioned schemes all reduce the strength of the wing sound source by modifying the structure of the lift-increasing device (slit wing, slit wing), but do not consider inhibiting noise during sound propagation, and modifying the lift-increasing device also increases the complexity of the mechanical structure of the wing. SUMMARY

[0005] The present application aims to provide a low-noise wing configuration based on acoustic soft material and an aircraft, which can further weaken the strength of the wing aerodynamic noise source while ensuring that the aerodynamic performance of the wing is not affected, and can absorb noise during sound propagation, so as to significantly reduce the radiation noise when the lift-increasing device is deployed.

[0006] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows: A low-noise wing configuration based on acoustic soft materials, the wing including a main wing having a leading edge and a trailing edge, a slat disposed at the leading edge of the main wing and a flap disposed at the trailing edge of the main wing; the slat is provided with a first concave side that can fit with the leading edge, and the trailing edge is provided with a second concave side that can fit with the flap, the second concave side being used to provide retraction space for the flap; The first concave side, the second concave side, and the leading edge surface are respectively provided with porous acoustic soft material layers, and the outer contour of the porous acoustic soft material layer is consistent with the shape of the wing position where the porous acoustic soft material layer is located.

[0007] Furthermore, the porous acoustic soft material layer is a porous polymer sound-absorbing material.

[0008] Furthermore, the dynamic density of porous polymer sound-absorbing materials according to Analysis yielded, among which The incoming flow density at the wing. The tortuosity factor of porous polymer sound-absorbing materials. It is the static flow resistance of porous polymer sound-absorbing materials. It refers to the porosity of porous polymer sound-absorbing materials. The angular frequency of the noise. ,in It is a noise frequency. It is the air viscosity coefficient. It is the viscous characteristic length of porous polymer sound-absorbing materials. To determine the airflow velocity across the surface of the porous acoustic soft material layer, For the speed of sound, The imaginary unit is used; the dynamic elastic modulus of porous polymer sound-absorbing materials. according to Analysis yielded, It is the adiabatic constant. It is the pressure of the airflow over the wing surface. It is a Prandtl number.

[0009] Furthermore, the edge of the porous polymer sound-absorbing material at each location is formed by the exposed porous polymer sound-absorbing material, and the edge of the porous polymer sound-absorbing material at each location is consistent with the edge contour of the first concave side, the second concave side, or the corresponding position of the leading edge.

[0010] Furthermore, the porous acoustic soft material layer includes a back plate fixed to the first concave side, the second concave side, or the leading edge surface, and a perforated panel whose outline is consistent with the shape of the wing position where the porous acoustic soft material layer is located, and a cavity is provided between the perforated panel and the corresponding back plate.

[0011] Furthermore, a support assembly is provided inside the cavity to support the perforated panel so that the shape of the perforated panel is consistent with the shape of the wing at the corresponding position.

[0012] Furthermore, the surface of the porous acoustic soft material layer is also covered with metal wire fabric.

[0013] Furthermore, the pressure surface of the flap is provided with a porous acoustic soft material layer.

[0014] To achieve the above-mentioned technical effects, the present invention also provides an aircraft comprising the aforementioned low-noise wing configuration based on acoustic soft materials.

[0015] Compared with the prior art, the beneficial effects of this invention are: 1. This invention provides a porous acoustic soft material layer between the main wing and the lift enhancement device (slats and flaps). The porous acoustic soft material is integrated with the outer contour of the main wing and the lift enhancement device, and is identical to the original outer contour of the main wing and the lift enhancement device. This does not affect the aerodynamic shape and aerodynamic performance of the original main wing and the lift enhancement device. While ensuring that the aerodynamic performance of the wing is not affected, it can further weaken the intensity of the aerodynamic noise source of the wing and absorb noise during sound propagation, thereby significantly reducing the radiated noise when the lift enhancement device is deployed and improving flight comfort.

[0016] 2. The main wing and lift enhancement device of the present invention have a simple structure, are easy to manufacture and apply, and are suitable for various aircraft with fixed wings. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the low-noise wing configuration based on acoustic soft materials in Example 1 or 2; Figure 2 This is a schematic diagram of the slat structure in Example 1; Figure 3 This is a schematic diagram of the main wing structure in Example 1; Figure 4 This is a schematic diagram of the slat structure in Example 2; Figure 5 This is a schematic diagram of the main wing structure in Example 2; Figure 6 This is a schematic diagram of the flap structure in Example 2; Among them, 1. Slat; 2. Main wing; 3. Flap; 4. First concave side; 5. Leading edge; 6. Second concave side; 7. Porous polymer sound-absorbing material; 8. Back plate; 9. Perforated panel; 10. Cavity; 11. Support assembly. Detailed Implementation

[0018] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0019] Example 1 See Figure 1 A low-noise wing configuration based on acoustic soft materials, the wing including a main wing 2 having a leading edge 5 and a trailing edge, a slat 1 disposed at the leading edge 5 of the main wing 2 and a flap 3 disposed at the trailing edge of the main wing 2; the slat 1 is provided with a first concave side 4 that can fit with the leading edge 5, and the trailing edge is provided with a second concave side 6 that can fit with the flap 3, the second concave side 6 being used to provide retraction space for the flap 3; The first concave side 4, the second concave side 6, and the leading edge 5 are respectively provided with porous acoustic soft material layers, and the outer contour of the porous acoustic soft material layer is consistent with the shape of the wing position where the porous acoustic soft material layer is located.

[0020] In this embodiment, a porous acoustic soft material layer is provided between the main wing 2 and the lift enhancement device (slat 1 and flap 3). The porous acoustic soft material is integrated with the outer contour of the main wing 2 and the lift enhancement device, and is the same as the original outer contour of the main wing 2 and the lift enhancement device. This does not affect the original aerodynamic shape and aerodynamic performance of the main wing 2 and the lift enhancement device. While ensuring that the aerodynamic performance of the wing is not affected, it can further weaken the intensity of the aerodynamic noise source of the wing and absorb noise during sound propagation, so as to significantly reduce the radiated noise when the lift enhancement device is deployed and improve flight comfort. In addition, the main wing 2 and the lift enhancement device in this embodiment have a simple structure, are easy to manufacture and apply, and are suitable for various aircraft with fixed wings.

[0021] In this embodiment, the porous acoustic soft material layer is a porous polymer sound-absorbing material 7. The volume and density of the material can be adjusted according to different application environments of the wing to achieve the best noise suppression effect. The adjustment method is as follows: the dynamic density and dynamic elastic modulus of the porous polymer (such as foamed metal) are calculated using an improved JCA sound propagation model. Dynamic density of porous polymer sound-absorbing material 7 according to Analysis yielded, among which The incoming flow density at the wing. The tortuosity factor of porous polymer sound-absorbing material 7. It is the static flow resistance of the porous polymer sound-absorbing material 7. The porosity of porous polymer sound-absorbing material 7 is... The angular frequency of the noise. ,in It is a noise frequency. It is the air viscosity coefficient. It is the viscous characteristic length of the porous polymer sound-absorbing material 7. To determine the airflow velocity across the surface of the porous acoustic soft material layer, For the speed of sound, The imaginary unit is used; the dynamic elastic modulus of porous polymer sound-absorbing material 7. according to Analysis yielded, It is the adiabatic constant. It is the pressure of the airflow over the wing surface. It is a Prandtl number.

[0022] The design of dynamic density and dynamic elastic modulus takes into account the influence of flow on the wing surface on the acoustic properties of porous materials when they are applied to aircraft wings. Its core advantage lies in quantifying the dissipation mechanism of sound energy by surface flow, improving the prediction accuracy of the acoustic properties of porous materials, and thus better guiding material selection and parameter optimization in the design process of low-noise wing configurations.

[0023] See Figure 2 The first concave side 4 of the slat 1 is used to arrange the porous polymer sound-absorbing material 7. The edge of the porous polymer sound-absorbing material 7 forms the original outline of the first concave side 4 of the slat 1 to ensure that the aerodynamic performance of the slat 1 is not damaged. The edge can be made of the porous polymer sound-absorbing material 7 exposed, or the edge of the porous polymer sound-absorbing material 7 can be covered with metal wire fabric or perforated panel 9 to enhance the smoothness of airflow and thus reduce the generation of aerodynamic noise.

[0024] See Figure 3 The space between the trailing edge second concave side 6 and the leading edge 5 of the main wing 2 is used to arrange porous polymer sound-absorbing material 7. The edge of the porous polymer sound-absorbing material 7 at the leading edge 5 forms the original outline of the leading edge 5 of the main wing 2, and the edge of the trailing edge second concave side 6 forms the original outline of the trailing edge. Each edge can be formed by the exposed porous polymer sound-absorbing material 7.

[0025] Example 2 See Figure 1 , Figures 4 to 6This embodiment demonstrates a low-noise wing configuration using a parallel resonant cavity consisting of a perforated panel 9, a cavity 10, and a backplate 8 as the acoustic soft material. It includes a main wing 2 with a leading edge 5 and a trailing edge, a slat 1 located at the leading edge of the main wing 2 and containing a first concave side 4, and a flap 3 located at the rear end of the main wing 2. A second concave side 6 structure is provided at the trailing edge of the main wing 2 to provide space for the flap 3 to retract. A porous acoustic soft material layer formed by a parallel resonant cavity sound-absorbing structure is arranged on the first concave side 4 of the slat 1, the leading edge 5, the trailing edge, and the underside of the flap 3. The sound-absorbing structure consists of the perforated panel 9, the cavity 10, and the backplate 8. This structure best ensures that the aerodynamic performance of the wing is not compromised.

[0026] See Figure 4 The perforated panel 9, the cavity 10 and the back plate 8 together constitute the parallel resonant cavity sound absorption structure of the slat 1. Here, the shape of the perforated panel 9 is consistent with the outline of the first concave side 4 of the original slat 1.

[0027] See Figure 5 Parallel resonant cavity sound-absorbing structures are arranged at the leading edge 5 and the trailing edge. The parallel resonant cavity sound-absorbing structures at these locations consist of perforated panels 9, cavities 10, and back plates 8. The outline of the perforated panel 9 at the first concave side 4 is consistent with the outline of the leading edge 5 of the original main wing 2, and the outline of the perforated panel 9 at the second concave side 6 is consistent with the outline of the trailing edge of the corresponding position of the original main wing 2.

[0028] See Figure 6 The perforated panel 9, the cavity 10, and the back plate 8 together form the parallel resonant cavity sound absorption structure of the flap 3. The shape of the perforated panel 9 is consistent with the lower side outline of the original flap 3.

[0029] In this embodiment, a support component 11 is provided inside the cavity 10. The arrangement of the cavity 10 and the support component 11, as well as the geometric parameters of the perforated panels 9 at each position, can be optimized and adjusted according to the available space and noise characteristics of the wing.

[0030] Similarly, metal wire fabric can be pasted onto the surface of the perforated panel 9 at various locations as needed to improve sound absorption performance.

[0031] It should be noted that in Example 1, metal wire fabric or perforated panel 9 can also be covered on the edge of porous polymer sound-absorbing material 7, and the metal wire fabric can be metal woven mesh, which can be used alone as a porous acoustic soft material layer.

[0032] Based on the same inventive concept, this embodiment also provides an aircraft including the aforementioned low-noise wing based on acoustic soft materials.

[0033] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A low-noise wing configuration based on acoustic soft materials, characterized in that, The wing includes a main wing (2) having a leading edge (5) and a trailing edge, a slat (1) disposed at the front end of the leading edge (5) of the main wing (2) and a flap (3) disposed at the trailing edge of the main wing (2); the slat (1) is provided with a first concave side (4) that can fit with the leading edge (5), and the trailing edge is provided with a second concave side (6) that can fit with the flap (3), the second concave side (6) being used to provide retraction space for the flap (3); The first concave side (4), the second concave side (6) and the leading edge (5) are respectively provided with porous acoustic soft material layers, and the outline of the porous acoustic soft material layer is consistent with the shape of the wing position where the porous acoustic soft material layer is located.

2. The low-noise wing configuration based on acoustic soft materials according to claim 1, characterized in that, The porous acoustic soft material layer is a porous polymer sound-absorbing material (7).

3. The low-noise wing configuration based on acoustic soft materials according to claim 2, characterized in that, Dynamic density of porous polymer sound-absorbing material (7) according to Analysis yielded, among which The incoming flow density at the wing. The tortuosity factor of the porous polymer sound-absorbing material (7) is... It is the static flow resistance of the porous polymer sound-absorbing material (7). It is the porosity of the porous polymer sound-absorbing material (7). The angular frequency of the noise. ,in It is a noise frequency. It is the air viscosity coefficient. It is the viscous characteristic length of the porous polymer sound-absorbing material (7). To determine the airflow velocity across the surface of the porous acoustic soft material layer, For the speed of sound, The imaginary unit; the dynamic elastic modulus of the porous polymer sound-absorbing material (7). according to Analysis yielded, It is the adiabatic constant. It is the pressure of the airflow over the wing surface. It is a Prandtl number.

4. The low-noise wing configuration based on acoustic soft materials according to claim 2, characterized in that, The edge of the porous polymer sound-absorbing material (7) at each location is formed by the exposed porous polymer sound-absorbing material (7), and the edge of the porous polymer sound-absorbing material (7) at each location is consistent with the edge contour of the corresponding position of the first concave side (4), the second concave side (6) or the leading edge (5).

5. The low-noise wing configuration based on acoustic soft materials according to claim 1, characterized in that, The porous acoustic soft material layer includes a back plate (8) fixed to the surface of the first concave side (4), the second concave side (6) or the leading edge (5), and a perforated panel (9) whose outline is consistent with the shape of the wing position where the porous acoustic soft material layer is located. A cavity (10) is provided between the perforated panel (9) and the corresponding back plate (8).

6. The low-noise wing configuration based on acoustic soft materials according to claim 5, characterized in that, A support assembly (11) is provided inside the cavity (10) to support the perforated panel (9) so that the shape of the perforated panel (9) is consistent with the shape of the wing at the corresponding position.

7. The low-noise wing configuration based on acoustic soft materials according to claim 1, characterized in that, The surface of the porous acoustic soft material layer is also covered with metal wire fabric.

8. The low-noise wing configuration based on acoustic soft materials according to claim 1, characterized in that, The pressure surface of the flap (3) is provided with a porous acoustic soft material layer.

9. An aircraft, characterized in that, The low-noise wing configuration based on acoustic soft materials as described in any one of claims 1-8.

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