CN219668480U - Acoustic liner structure and aircraft - Google Patents

Abstract

The utility model relates to the technical field of civil aircraft noise treatment, in particular to an acoustic liner structure and an aircraft. The utility model provides an acoustic liner structure, which comprises an acoustic liner panel and a honeycomb core; the acoustic liner panel comprises a first wire mesh and a first perforated plate, wherein the first wire mesh is connected with the first perforated plate; the honeycomb core is connected to the side of the first perforated plate remote from the first wire mesh. Because the acoustic liner panel comprises the first wire mesh and the first perforated plate, the integral strength of the acoustic liner panel can be effectively enhanced, and meanwhile, one side of the first wire mesh is in direct contact with air flow, so that the action of air flow resistance can be effectively reduced, sound waves are dissipated in the process of entering the pores of the first wire mesh and the first perforated plate, and then enter the honeycomb core, and the noise reduction effect is effectively realized under the resistance action of the honeycomb core. The aircraft provided by the utility model has the technical effects due to the fact that the acoustic liner structure is included.

Description

Acoustic liner structure and aircraft

Technical Field

The utility model relates to the technical field of civil aircraft noise treatment, in particular to an acoustic liner structure and an aircraft.

Background

In civil aircraft, acoustic liners are available for installation in the air inlet and exhaust ducts of the nacelle and auxiliary power unit for reducing the noise that the engine propagates outwards. The acoustic liner structure is typically a sandwich structure consisting of an acoustic liner panel and a honeycomb core.

In the related art, the acoustic liner panel is composed of a perforated plate or a wire mesh. Wherein, the sound lining structure of one part of the aircraft adopts the perforated plate to form the sound lining panel, and the sound lining structure of the other part of the aircraft adopts the wire mesh to bond a layer of braided fabric to form the sound lining panel.

However, the acoustic liner panel described above has a problem in that resistance increases or overall rigidity is weak.

Disclosure of Invention

The present utility model provides an acoustic liner structure and an aircraft that effectively address the above-identified and other potential technical problems.

A first aspect of the utility model provides an acoustic liner structure comprising an acoustic liner panel and a honeycomb core; the acoustic liner panel comprises a first wire mesh and a first perforated plate, the first wire mesh being connected to the first perforated plate; the honeycomb core is connected to one side of the first perforated plate away from the first wire mesh.

The acoustic liner structure provided by the embodiment of the utility model comprises an acoustic liner panel and a honeycomb core; the acoustic liner panel comprises a first wire mesh and a first perforated plate, the first wire mesh being connected to the first perforated plate; the honeycomb core is connected to one side of the first perforated plate away from the first wire mesh. Because the acoustic liner panel comprises the first wire mesh and the first perforated plate, the overall strength of the acoustic liner panel can be effectively enhanced, the mechanical property of the overall acoustic liner panel is improved, meanwhile, one side of the first wire mesh is in direct contact with air flow, the action of air flow resistance can be effectively reduced, the acoustic wave energy of the acoustic wave is dissipated in the process of entering the pores of the first wire mesh and the first perforated plate, and then the acoustic wave enters the honeycomb core, and the noise reduction effect is effectively realized under the resistance action of the honeycomb core. Therefore, by adopting the sound liner structure provided by the utility model, the effects of broadband noise reduction and pneumatic drag reduction aiming at the sound source can be realized.

In an alternative embodiment according to the first aspect, the first wire mesh and the first perforated plate constitute the acoustic liner panel by high temperature sintering.

In an alternative embodiment according to the first aspect, the honeycomb core comprises at least two honeycomb core layers, adjacent two of the honeycomb core layers being bonded by an adhesive layer.

In an alternative embodiment according to the first aspect, the adhesive layer includes a first adhesive film, a second metal wire mesh and a second adhesive film that are sequentially stacked, and two adjacent nest core layers are respectively adhered to the first adhesive film and the second adhesive film; or alternatively, the first and second heat exchangers may be,

the bonding layer comprises a first adhesive film, a second perforated plate and a second adhesive film which are sequentially stacked, and two adjacent nest core layers are respectively bonded with the first adhesive film and the second adhesive film.

In an alternative embodiment according to the first aspect, the first wire mesh is any one of a soft brass wire mesh, a tin bronze wire mesh, a stainless steel wire mesh or a carbon structured steel wire mesh.

In an alternative embodiment according to the first aspect, the first perforated plate is an aluminium alloy plate or a stainless steel plate.

In an alternative embodiment according to the first aspect, the thickness of the first perforated plate is less than or equal to 0.5mm; and/or the holes on the first perforated plate are round holes, and the diameter of the round holes is 0.5-1.5 mm.

In an alternative embodiment according to the first aspect, the holes in the first perforated plate are arranged in a rectangular or in a diamond shape; and/or the perforation rate of the holes on the first perforated plate is 5-25%.

In an alternative embodiment according to the first aspect, the acoustic liner structure further comprises a back plate connected to a side of the honeycomb core remote from the acoustic liner panel.

The second aspect of the utility model also provides an aircraft comprising the acoustic liner structure, wherein the acoustic liner structure is arranged on a nacelle of the aircraft, and/or the acoustic liner structure is arranged in an air inlet passage and an air outlet passage of an auxiliary power unit of the aircraft.

The aircraft provided by the utility model comprises the acoustic liner structure, so that the integral strength of the acoustic liner panel can be effectively enhanced, the mechanical property of the integral acoustic liner is improved, and the technical effects of broadband noise reduction and pneumatic drag reduction for a sound source can be realized.

Additional aspects of the utility model will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the utility model.

Drawings

The above and other objects, features and advantages of embodiments of the present utility model will become more readily apparent from the following detailed description with reference to the accompanying drawings. Embodiments of the utility model will now be described, by way of example and not limitation, in the figures of the accompanying drawings, in which:

FIG. 1 is a schematic diagram of the overall structure of an acoustic liner structure according to an embodiment of the present utility model;

FIG. 2 is a schematic cross-sectional view of an acoustic liner structure according to an embodiment of the present utility model;

FIG. 3 is a schematic view of a honeycomb core of an acoustic liner structure according to an embodiment of the present utility model including two honeycomb core layers;

FIG. 4 is a schematic diagram of an APU muffler employing an acoustic liner structure according to an embodiment of the present utility model;

FIG. 5 is a schematic cross-sectional view of the inlet tongue acoustic liner of FIG. 4;

FIG. 6 is a schematic diagram of measured noise reduction for an APU muffler employing an acoustic liner structure provided by an embodiment of the present utility model.

Reference numerals illustrate:

10. an acoustic liner structure; 11. an acoustic liner panel; 111. a first wire mesh; 112. a first perforated plate; 113. a metal sintering point; 12. a top adhesive film; 13. a honeycomb core; 131. a first cellular core layer; 132. a second cellular core layer; 133. an adhesive layer; 1331. a first adhesive film; 1332. a second adhesive film; 1333. a second wire mesh; 15. a back plate; 151. a bottom adhesive film; 20. an APU inlet muffler; 21. an air intake duct wall; 22. an air inlet duct tongue plate acoustic liner; 23. and the side wall of the air inlet channel is acoustic lined.

Detailed Description

Embodiments of the present utility model are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present utility model and should not be construed as limiting the utility model.

In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present utility model and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present utility model.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present utility model, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.

In the present utility model, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; may be a mechanical connection; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.

In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present utility model. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.

In civil aircraft, acoustic liners are available for installation in the air inlet and exhaust ducts of the nacelle and auxiliary power unit for reducing the noise that the engine propagates outwards. The acoustic liner structure is typically a sandwich structure consisting of an acoustic liner panel and a honeycomb core. In the related art, the acoustic liner panel is composed of a first perforated plate or a wire mesh. The acoustic liner structure of one part of the aircraft adopts a first perforated plate to form an acoustic liner panel, and the acoustic liner structure of the other part of the aircraft adopts a wire mesh to bond a layer of braided fabric to form the acoustic liner panel. However, the acoustic liner panel described above has a problem in that resistance increases or overall rigidity is weak.

In view of this, the acoustic liner structure provided by the embodiment of the present utility model includes an acoustic liner panel and a honeycomb core; the acoustic liner panel comprises a first wire mesh and a first perforated plate, the first wire mesh being connected to the first perforated plate; the honeycomb core is connected to one side of the first perforated plate away from the first wire mesh. Because the acoustic liner panel comprises the first wire mesh and the first perforated plate, the overall strength of the acoustic liner panel can be effectively enhanced, the mechanical property of the overall acoustic liner panel is improved, meanwhile, one side of the first wire mesh is in direct contact with air flow, the action of air flow resistance can be effectively reduced, the acoustic wave energy of the acoustic wave is dissipated in the process of entering the pores of the first wire mesh and the first perforated plate, and then the acoustic wave enters the honeycomb core, and the noise reduction effect is effectively realized under the resistance action of the honeycomb core. Therefore, by adopting the sound liner structure provided by the utility model, the effects of broadband noise reduction and pneumatic drag reduction aiming at the sound source can be realized.

Referring to fig. 1 to 6, an acoustic liner structure 10 according to an embodiment of the present utility model includes an acoustic liner panel 11 and a honeycomb core 13; the acoustic liner panel 11 comprises a first wire mesh 111 and a first perforated plate 112, the first wire mesh 111 being connected to the first perforated plate 112; the honeycomb core 13 is connected to the side of the first perforated plate 112 remote from the first wire mesh 111.

The acoustic liner structure 10 provided by the embodiment of the utility model comprises an acoustic liner panel 11 and a honeycomb core 13; the acoustic liner panel 11 comprises a first wire mesh 111 and a first perforated plate 112, the first wire mesh 111 being connected to the first perforated plate 112; the honeycomb core 13 is connected to the side of the first perforated plate 112 remote from the first wire mesh 111. Because the acoustic liner panel 11 comprises the first wire mesh 111 and the first perforated plate 112, the overall strength of the acoustic liner panel 11 can be effectively enhanced, the mechanical property of the overall acoustic liner panel 11 is improved, meanwhile, one side of the first wire mesh 111 is directly contacted with air flow, the action of air flow resistance can be effectively reduced, the acoustic wave energy of the acoustic wave is dissipated in the process of entering the pores of the first wire mesh 111 and the first perforated plate 112, the acoustic wave enters the honeycomb core 13 again, and the noise reduction effect is effectively realized under the resistance action of the honeycomb core 13. Therefore, the sound liner structure 10 provided by the utility model can realize the effects of broadband noise reduction and pneumatic drag reduction aiming at a sound source.

In an alternative exemplary embodiment, the first wire mesh 111 and the first perforated plate 112 constitute the acoustic liner panel 11 by high temperature sintering.

In particular, in this embodiment, the acoustic liner panel 11 is formed by sintering the first wire mesh 111 and the first perforated plate 112 at a high temperature, so that the structural stability of the acoustic liner panel 11 can be effectively enhanced, and the connection mode of the high temperature sintering is simple and easy to operate, so that the manufacturing difficulty of the acoustic liner panel 11 can be effectively reduced.

Illustratively, the first perforated plate 112 is a metallic first perforated plate 112.

Specifically, in this embodiment, during the high-temperature sintering process of the first wire mesh 111 and the first perforated plate 112, a layer of metal powder is first covered between the first wire mesh 111 and the first perforated plate 112, then a current is applied in a sintering electric furnace, a metal sintering point 113 is formed at the contact position, then unsintered metal powder is cleaned, and the pores of the wire mesh and the first perforated plate 112 are dredged.

Illustratively, in this embodiment, the acoustic liner panel 11 is bonded to the honeycomb core 13 using a top adhesive film 12.

Note that, the top adhesive film 12 may be made of a material compatible with the acoustic liner panel 11.

In an alternative exemplary embodiment, the honeycomb core 13 includes at least two honeycomb core layers, and two adjacent honeycomb core layers are bonded by an adhesive layer 133.

In particular, in the present embodiment, the honeycomb core 13 is configured to include at least two honeycomb core layers, and two adjacent honeycomb core layers are bonded by the adhesive layer 133. By the arrangement, the noise reduction effect can be further improved.

Illustratively, in this embodiment, the honeycomb core 13 includes two honeycomb core layers. To clearly describe the noise reduction principle, the two honeycomb cores are a first honeycomb core 131 and a second honeycomb core 132, respectively. During use, noise propagates in the air stream, its sound waves dissipate their sound wave energy as they enter the apertures of the first wire mesh 111 and the first perforated plate 112, and then enter the first cellular core 131, the resistive effect of which first cellular core 131 amplifies the amount of noise reduction at the first characteristic frequency. After the sound wave enters the bonding layer 133 in the middle of the double-layer honeycomb core, the sound wave energy is again reduced, and finally the noise reduction for the second characteristic frequency is amplified in the second honeycomb core 132. In summary, the acoustic liner structure 10 of the present utility model can achieve the effects of broadband noise reduction and pneumatic drag reduction for a sound source.

It should be noted that the honeycomb core 13 may also be formed of more than two honeycomb core layers, for example, a three-layer honeycomb core structure may be formed by bonding the honeycomb core layers on the surfaces of the two-layer honeycomb core layers through the bonding layer 133. The formation of more than three honeycomb cores and so on.

Illustratively, in particular, in the present embodiment, the thickness of the first cellular core 131 may be set to 7.3mm and the thickness of the second cellular core 132 may be set to 5.2mm.

Illustratively, in the present embodiment, the first and second honeycomb core layers 131 and 132 may each be made of an aramid paper honeycomb material.

In an alternative exemplary embodiment, the adhesive layer 133 includes a first adhesive film 1331, a second wire mesh 1333, and a second adhesive film 1332 that are sequentially stacked, and two adjacent nest core layers are respectively adhered to the first adhesive film 1331 and the second adhesive film 1332.

In the embodiment, the adhesive layer 133 includes a first adhesive film 1331, a second metal wire mesh 1333, and a second adhesive film 1332 that are stacked in order, and two adjacent nest-core layers are respectively adhered to the first adhesive film 1331 and the second adhesive film 1332. The first adhesive film 1331 and the second adhesive film 1332 are convenient for realizing connection between the nest core layers on two sides of the second wire mesh 1333, and the second wire mesh 1333 can effectively reduce the sound wave energy passing through the nest core layers again, so that the noise reduction effect of the whole sound liner structure 10 is improved.

In an alternative exemplary embodiment, the adhesive layer 133 includes a first adhesive film 1331, a second perforated plate (not shown) and a second adhesive film 1332 that are stacked in sequence, and two adjacent nest core layers are respectively adhered to the first adhesive film 1331 and the second adhesive film 1332.

In the embodiment, the adhesive layer 133 includes a first adhesive film 1331, a second perforated plate, and a second adhesive film 1332 that are stacked in order, and two adjacent nest core layers are respectively adhered to the first adhesive film 1331 and the second adhesive film 1332. The first adhesive film 1331 and the second adhesive film 1332 are convenient for realizing connection between the nest core layers at two sides of the second perforated plate, and the second perforated plate can effectively reduce the sound wave energy passing through the second perforated plate again, so that the noise reduction effect of the whole sound liner structure 10 is improved.

In alternative exemplary embodiments, the first wire mesh 111 is any one of a soft brass wire mesh, a tin bronze wire mesh, a stainless steel wire mesh, or a carbon structure steel wire mesh.

In particular, in this embodiment, the first wire mesh 111 is any one of a soft brass wire mesh, a tin bronze wire mesh, a stainless steel wire mesh, or a carbon structure steel wire mesh. It should be understood that the specific material of the first wire mesh 111 is not limited herein, and in other embodiments, it may be made of a suitable material according to the specific requirements of the user, so as to reduce noise.

It should be further noted that the second wire mesh 1333 may be made of the same material as the first wire mesh 111, or may be made of other suitable materials. Similarly, the second wire mesh 1333 may have the same size and shape as the first wire mesh 111, so that the first wire mesh 111 and the second wire mesh 1333 have the same structure when the acoustic liner structure 10 is manufactured, which makes the manufacturing process simpler. It is of course also possible to design the first wire mesh 111 and the second wire mesh 1333 separately, respectively, according to the needs of the user.

By way of example, the second wire mesh 1333 may be made of soft brass, tin bronze, stainless steel, and carbon structural steel.

Illustratively, the first wire mesh 111 and the second wire mesh 1333 may employ high mesh numbers of wires, typically 200 mesh or more.

The first wire mesh 111 and the second wire mesh 1333 may be high-mesh wire meshes, and typically, 200 mesh wire meshes or more are used, so that the effect of air flow resistance can be effectively reduced.

It should be further noted that, the high mesh number of the silk screen provided by the embodiment of the utility model can reach 635 mesh at the highest mesh number.

In an alternative exemplary embodiment, the first perforated plate 112 is an aluminum alloy plate or a stainless steel plate.

In particular, in this embodiment, the first perforated plate 112 is made of an aluminum alloy plate or a stainless steel plate, so that the structural strength of the first perforated plate 112 can be effectively improved, and further the structural rigidity of the acoustic liner panel 11 can be effectively improved, and the mechanical properties of the overall acoustic liner structure 10 can be improved.

In an alternative exemplary embodiment, the thickness of the first perforated plate 112 is less than or equal to 0.5mm. Illustratively, the thickness of the first perforated plate 112 may be set to 0.2mm.

It will be appreciated that the thickness of the first perforated plate 112 may also be set to 0.3mm or 0.5mm according to the specific needs of the user.

Illustratively, the first perforated plate 112 has a thickness of 0.2mm or greater.

In an alternative exemplary embodiment, the holes on the first perforated plate 112 are circular holes having a diameter of 0.5mm to 1.5mm. Illustratively, the circular aperture has a diameter of 0.3mm.

Illustratively, in this embodiment, the holes of the first perforated plate 112 are arranged in a rectangular shape or in a diamond shape.

In an alternative exemplary embodiment, the perforation rate of the holes on the first perforated plate 112 is 5% to 25%.

Illustratively, specifically, in the present embodiment, the perforation rate of the holes on the first perforated plate 112 is 17.2%.

It should be noted that, the geometric parameters of the first wire mesh 111 and the first perforated plate 112 may be designed to match the characteristic frequency of the sound source according to the acoustic impedance model.

Similarly, the geometric parameters of the second wire mesh 1333 and the second perforated plate may be designed to match the characteristic frequencies of the sound source according to the acoustic impedance model.

In an alternative exemplary embodiment, the acoustic liner structure 10 further comprises a back plate 15, said back plate 15 being connected to the side of said honeycomb core 13 remote from said acoustic liner panel 11.

Specifically, in the present embodiment, the acoustic liner structure 10 further includes a back plate 15, and the back plate 15 is connected to a side of the honeycomb core 13 away from the acoustic liner panel 11.

Illustratively, in this embodiment, the honeycomb core 13 is bonded to the back sheet 15 using a base adhesive film 151.

It should be noted that, the bottom adhesive film 151 may be made of a material compatible with the back plate 15.

Illustratively, in the present embodiment, the back sheet 15 is a carbon fiber composite sheet.

It should be noted that the carbon fiber composite board has a good bearing capacity, and can facilitate making the back plate 15 a structural bearing member for supporting the entire acoustic liner structure 10.

In order to further illustrate the principles and technical effects of the acoustic liner structure 10 provided by the embodiments of the present utility model, the APU inlet muffler 20 is fabricated by using the fabrication principles of the acoustic liner structure 10 of the present utility model, and the test is completed in the anechoic room environment. In the APU intake silencer 20, with the acoustic liner structure 10 provided by the embodiment of the present utility model, an intake pipe wall 21 is provided on the top layer of the APU intake silencer 20, and may be used as the back plate 15 of the acoustic liner mechanism, an intake tongue acoustic liner 22 is provided in the middle of the APU intake silencer 20, and an intake sidewall acoustic liner 23 is provided in the middle of the APU intake silencer 20. The inlet tongue plate acoustic liner 22 comprises a first acoustic liner panel 11, a first honeycomb core 13, a middle back plate 15, a second honeycomb core 13 and a second acoustic liner panel 11 which are stacked. The geometric parameters of the sintered panels of the first wire mesh 111 and the first perforated plate 112 of the structures of the first acoustic liner panel 11 and the second acoustic liner panel 11 are as follows: the first wire net 111 had a pitch of 0.036mm, the diameter of the mesh of the first wire net 111 was 0.025mm, the thickness of the first perforated plate 112 was 0.2mm, the diameter of the circular perforations of the first perforated plate 112 was 0.3mm, and the perforation rate thereof was 17.2%. The first honeycomb core 13 and the second honeycomb core 13 have the same structure, each comprises two honeycomb core layers, and the thickness of the first honeycomb core layer 131 is 7.3mm; the thickness of the second honeycomb core 132 is 5.2mm. First and second nest core layers 131, 132 the wire mesh openings of second wire mesh 1333 are spaced 0.045mm apart and the wire mesh openings are 0.032mm in diameter. Wherein, the material of the wire mesh and the perforated plate is stainless steel, and the adhesive film between the acoustic liner panel 11 and the honeycomb core 13 and between the honeycomb core 13 and the back plate 15 can be J-299 adhesive film. The back plate 15 is made of a T300 composite material.

After the completion of the production, the APU inlet muffler 20 was tested, and in the muffling chamber, a noise reduction test was performed on the APU inlet muffler 20 based on a known sound source, and the test results are shown in fig. 6. The noise reduction amount of the silencer at the 1/3 octave center frequency is shown in the frequency range of 200 Hz-20000 Hz, wherein the noise reduction effect is close to or exceeds 10dB in the frequency range of 2000 Hz-20000 Hz, and further the fact that the broadband noise reduction effect of the sound liner structure 10 provided by the embodiment of the utility model can be realized is verified.

The utility model also provides an aircraft, comprising the acoustic liner structure 10, wherein the acoustic liner structure 10 is arranged on a nacelle of the aircraft, and/or the acoustic liner structure 10 is arranged in an air inlet passage and an air outlet passage of an auxiliary power unit of the aircraft.

The aircraft provided by the utility model comprises the acoustic liner structure 10, so that the integral strength of the acoustic liner panel 11 can be effectively enhanced, the mechanical property of the integral acoustic liner is improved, and the technical effects of broadband noise reduction and pneumatic drag reduction of a sound source can be realized.

Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present utility model, and are not limiting; although the utility model has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced with equivalents; such modifications and substitutions do not depart from the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present utility model.

It should be noted that the specific features described in the above embodiments may be combined in any suitable manner without contradiction. The various possible combinations of the utility model are not described in detail in order to avoid unnecessary repetition.

Claims (10)

1. An acoustic liner structure comprising an acoustic liner panel and a honeycomb core;

the acoustic liner panel comprises a first wire mesh and a first perforated plate, the first wire mesh being connected to the first perforated plate;

the honeycomb core is connected to one side of the first perforated plate away from the first wire mesh.

2. The acoustic liner structure of claim 1 wherein the first wire mesh and the first perforated plate form the acoustic liner panel by high temperature sintering.

3. The acoustic liner structure of claim 1 wherein the honeycomb core comprises at least two honeycomb core layers, adjacent ones of the honeycomb core layers being bonded by an adhesive layer.

4. The acoustic liner structure of claim 3 wherein the adhesive layer comprises a first adhesive film, a second wire mesh and a second adhesive film laminated in sequence, adjacent two of the nest core layers being bonded to the first adhesive film and the second adhesive film respectively; or alternatively, the first and second heat exchangers may be,

the bonding layer comprises a first adhesive film, a second perforated plate and a second adhesive film which are sequentially stacked, and two adjacent nest core layers are respectively bonded with the first adhesive film and the second adhesive film.

5. The acoustic liner structure of any of claims 1 to 4 wherein the first wire mesh is any one of a soft brass wire mesh, a tin bronze wire mesh, a stainless steel wire mesh, or a carbon structure steel wire mesh.

6. The acoustic liner structure of any one of claims 1 to 4 wherein the first perforated plate is an aluminum alloy plate or a stainless steel plate.

7. The acoustic liner structure of any of claims 1 to 4 wherein the thickness of the first perforated plate is 0.5mm or less; and/or the number of the groups of groups,

the holes on the first perforated plate are round holes, and the diameter of each round hole is 0.5-1.5 mm.

8. The acoustic liner structure of any of claims 1 to 4 wherein the holes in the first perforated plate are arranged in a rectangular or diamond arrangement; and/or the number of the groups of groups,

the perforation rate of the holes on the first perforated plate is 5% -25%.

9. The acoustic liner structure of any of claims 1 to 4 further comprising a back plate attached to a side of the honeycomb core remote from the acoustic liner panel.

10. An aircraft, comprising: the acoustic liner structure of any one of claims 1 to 9, which is provided on a nacelle of the aircraft, and/or,

the acoustic liner structure is arranged in an air inlet passage and an air outlet passage of the auxiliary power device of the aircraft.