CN217022866U - Aviation interior sound insulation heated board - Google Patents
Aviation interior sound insulation heated board Download PDFInfo
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- CN217022866U CN217022866U CN202220573620.4U CN202220573620U CN217022866U CN 217022866 U CN217022866 U CN 217022866U CN 202220573620 U CN202220573620 U CN 202220573620U CN 217022866 U CN217022866 U CN 217022866U
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Abstract
An aviation interior sound-insulation heat-preservation plate comprises an outer wall plate, a sound-insulation heat-preservation interlayer and a sound-insulation inner wall plate which are sequentially stacked; a plurality of sound-absorbing micropores are uniformly distributed on the outer wall plate, and the sound-absorbing micropores are of an inclined hole structure; and a sound insulation damping film is arranged on the outer surface of the sound insulation inner wall plate. The sound-absorbing porous plate structure is formed by arranging the sound-absorbing micropores on the outer wall plate, the sound-insulating and heat-preserving interlayer is used for playing the roles of sound insulation and heat preservation, and the sound insulation effect is improved by forming the damping protective layer by using the sound-insulating and heat-preserving film. The sound micropore structure of inhaling of slope form uses the inclined direction of inhaling the sound micropore downwards, and some particulate matters can slide by oneself, can prevent effectively to inhale the sound micropore and take place to block up. A damping constraint structure layer is formed by utilizing the sound insulation damping film, so that the object is effectively prevented from vibrating, and vibration attenuation is realized.
Description
Technical Field
The utility model relates to the technical field of composite material sound insulation structures, in particular to the field of sound insulation and heat preservation structures, and specifically relates to an aviation interior sound insulation and heat preservation plate.
Background
At present, the airplane becomes the most extensive and rapid vehicle, and the dependence on the airplane is higher and higher. On one hand, for the sound insulation effect of the airplane, passengers and crew generally pay more attention, so that the requirement on the noise in the passenger cabin of the civil airplane is higher and higher; on the other hand, the airplane passenger cabin is required to be well insulated, so that the energy waste is reduced. At present, under the condition of saving cost and reducing energy waste, further improving the comfort and heat preservation of the acoustic environment in the passenger cabin becomes more and more important points of concern of various large-scale aviation passenger plane manufacturers, and is just as an important index of the commercial competitive capacity of the passenger plane. Therefore, how to produce the interior decoration material which is light and suitable for the thermal insulation and sound insulation of the airplane is a topic which needs to be solved and researched urgently.
Patent No. cn200880004068.x discloses a panel for acoustic treatment relating to a panel for acoustic treatment attached to the surface of an aircraft, having from the outside to the inside a porous acoustic insulation layer, at least one cellular structure and a reflecting or impermeable layer, wherein the outer surface of said porous acoustic insulation layer comprises a sheet or lamina in contact with the aerodynamic air flow, the sheet or lamina comprising open areas allowing the passage of sound waves and solid areas not allowing the passage of sound waves, characterized in that the sheet or lamina of said acoustic insulation layer comprises a plurality of groups of micro pores, each group of micro pores forming an open area, the groups of micro pores being separated by at least one set of spacer bands of solid areas, which patent is open-ended only for the acoustic outer panel, without an improved design of the internal acoustic insulation.
Patent CN202010151646.5 discloses an interior trim panel and application thereof, the interior trim panel includes: an outer panel; an inner side plate; the sound absorption capacity of the interior trim panel is improved mainly by arranging the micro-perforations, but the sound insulation effect is still to be improved.
The utility model discloses a honeycomb embedded coupling structure composite material and a preparation method thereof, and provides the honeycomb embedded coupling structure composite material and the preparation method thereof, wherein a honeycomb structure is used as a frame, a fiber material or a fiber and particle mixed material is used as a raw material, the raw material is prepared into the honeycomb embedded coupling structure composite material through raw material proportioning, wet pulping, negative pressure deposition, drying and curing, the fiber material or the fiber and particle mixed material is embedded in a honeycomb cell, an embedded object has a stable shape and is tightly combined with the wall of the honeycomb cell, and the structure of the embedded object can be designed into a layered structure, a gradient structure and a three-dimensional disordered structure according to requirements. In the concrete application process of this embedded integrated configuration combined material again, because of the embedded thing contains the particulate matter, therefore its stable effect can't be ensured, and embedded material may spill over.
SUMMERY OF THE UTILITY MODEL
The utility model mainly aims to provide an aviation interior sound-insulation heat-preservation plate and aims to solve the technical problems.
In order to achieve the purpose, the utility model provides an aviation interior sound-insulation heat-preservation plate, which comprises an outer wall plate, a sound-insulation heat-preservation interlayer and a sound-insulation inner wall plate which are sequentially stacked; a plurality of sound-absorbing micropores are uniformly distributed on the outer wall plate, and the sound-absorbing micropores are of an inclined hole structure; and a sound insulation damping film is arranged on the outer surface of the sound insulation inner wall plate.
Preferably, the included angle between the axis of the sound absorption micro-hole and the surface of the outer wall plate is 60-80 degrees, and the inclination directions of the sound absorption micro-holes are consistent.
Preferably, the sound-absorbing micropores have a diameter of
The distance between the adjacent sound-absorbing micropores is 2-3 mm.
Optionally, on the surface of the outer wall plate, the total area of the sound-absorbing micropores accounts for 20-40% of the surface area of the outer wall plate.
Preferably, the sound-insulation and heat-preservation interlayer is of a honeycomb structure formed by a plurality of honeycomb cells, and each honeycomb cell is filled with an embedded material for heat insulation and preservation.
Preferably, the honeycomb unit cells in the sound-insulation and heat-preservation interlayer are aramid paper honeycombs, the embedded material is formed by superfine glass fibers and thermosetting resin, and the superfine glass fibers are distributed in a three-dimensional disordered manner.
Preferably, the sound insulation damping film is a water-based damping high-performance coating layer.
Preferably, the thickness of the water-based damping high-performance coating layer is 0.8-1.5 mm.
Preferably, the aviation interior sound-insulation and heat-preservation plate is a plate body with a hexagonal structure, and the outer wall plate and the sound-insulation and heat-preservation interlayer as well as the sound-insulation and heat-preservation interlayer and the sound-insulation inner wall plate are all solidified and bonded through the adhesive.
Preferably, the soundproof inner wall panel has a plate-shaped structure formed by bonding a plurality of layers of ultrafine glass fiber reinforced fabric, foam and unsaturated polyester resin.
Due to the adoption of the technical scheme, the utility model has the following beneficial effects:
(1) the sound-absorbing porous plate structure is formed by arranging the sound-absorbing micropores on the outer wall plate, the sound-insulating and heat-preserving interlayer is used for playing the roles of sound insulation and heat preservation, and the sound insulation effect is improved by forming the damping protective layer by using the sound-insulating and heat-preserving film. The sound micropore structure of inhaling of slope form uses the inclined direction of inhaling the sound micropore downwards, and some particulate matters can slide by oneself, can prevent effectively to inhale the sound micropore and take place to block up. A damping constraint structure layer is formed by utilizing the sound insulation damping film, so that the vibration of an object is effectively prevented, and the vibration attenuation is realized.
(2) On one hand, the number and the structure of sound absorption micropores of the outer wall plate can be adjusted by combining with acoustic design; on the other hand combines sound transmission loss mechanism, is three-dimensional mixed and disorderly embedded fine glass material and the sound insulation coating layer who distributes through the increase, can effectively improve the aircraft sound insulation problem, improves cabin sound environmental comfort.
(3) The multi-layer superfine glass fiber reinforced fabric structure of the sound-insulation inner wall plate enables sound waves to be reflected for multiple times in each layer of the composite material, so that sound energy absorption loss is realized, and the integral sound insulation performance of the composite structure is improved.
(4) The embedded superfine glass fiber composite material has high-efficiency heat insulation performance, so that the interior trim panel can further improve the heat insulation performance of the airplane and achieve the effect of reducing the energy consumption of the airplane.
(5) The inclined sound-absorbing micropore structure can solve the problem of micropore blockage under the condition of achieving effective sound-absorbing effect;
(6) through designing interior sound insulation heated board for hexagon structure, can effectively improve interior plaque's aesthetic property and stability, improve its mechanical properties.
Drawings
In order to more clearly illustrate the embodiments or technical solutions of the present invention, the drawings used in the embodiments or technical solutions of the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic structural view of an aviation interior sound-insulation and heat-preservation board provided by the utility model;
FIG. 2 is a schematic structural view of the aviation interior sound-insulation heat-preservation plate provided by the utility model in another direction;
fig. 3 is a schematic view of a sound-insulation and heat-insulation sandwich structure of the sound-insulation and heat-insulation board for aviation interior trim provided by the utility model.
The reference numbers illustrate: 10-an outer wall plate; 20-sound-absorbing micropores; 30-sound insulation and heat preservation interlayer; 40-sound insulation damping film; 50-a sound-insulating inner wall panel; 60-cellular cells; 70-embedded material.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all directional indicators (such as upper, lower, left, right, front and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
Referring to fig. 1, the schematic diagram of the three-dimensional structure of the aviation interior sound-insulation and heat-preservation board of the present invention is shown, and the aviation interior sound-insulation and heat-preservation board includes an outer wall board 10, a sound-insulation and heat-preservation interlayer 30, and a sound-insulation inner wall board 50, which are sequentially stacked; a plurality of sound-absorbing micropores 20 are uniformly distributed on the outer wall plate 10, and the sound-absorbing micropores 20 are in an inclined hole structure; a soundproof damping film 40 is provided on an outer surface of the soundproof inner wall panel 50. The outer wall panel 10 is a thin sheet or plate in contact with the aerodynamic air flow, and sound-absorbing micro-holes 20 are provided with a certain interval therebetween. The inner sound insulation panel 50 is a high-density sound insulation panel structure formed by bonding a plurality of layers of ultrafine glass fiber reinforced fabric, foam and unsaturated polyester resin.
In this embodiment, the included angle between the axis of the sound-absorbing micro-holes 20 and the surface of the outer wall plate 10 is 60 ° to 80 °, and the inclination directions of the sound-absorbing micro-holes 20 are the same, so that some particles can slide down by themselves to prevent the sound-absorbing micro-holes 20 from being blocked. Further, the diameter of the sound-absorbing micro-holes 20 is phi 0.8 mm-phi 1.5mm, the distance between adjacent sound-absorbing micro-holes 20 is 2-3 mm, or the total area of the sound-absorbing micro-holes 20 accounts for 20-40% of the surface area of the outer wall plate 10, and the solid areas between the sound-absorbing micro-holes 20 form a framework supporting structure. The number, inclination and pore size of the sound-absorbing micro-pores 20 can be set according to the requirement of sound-absorbing frequency band.
Referring to fig. 2, the sound-insulating and heat-preserving interlayer 30 has a honeycomb structure formed by a plurality of honeycomb cells 60, and each honeycomb cell 60 is filled with an embedded material 70 for heat insulation and preservation. Further, the honeycomb unit cells 60 in the sound-insulation heat-preservation sandwich layer 30 are aramid paper honeycombs, the embedded material 70 is formed by superfine glass fibers and thermosetting resin, and the superfine glass fibers are distributed in a three-dimensional disordered manner and are tightly attached to the honeycomb unit cells 60.
In this embodiment, the sound-proof damping film 40 is a water-based damping high-performance coating layer, the water-based damping high-performance coating layer is coated on the outer surface of the sound-proof inner wall plate 50, and the sound-proof damping film 40 is a sound-proof coating layer which increases the surface density of the wall plate by forming a damping protective layer, so as to form a damping constraint structure layer, effectively prevent the object from vibrating and realize the vibration attenuation. Further, in order to ensure the sound insulation effect, the thickness of the water-based damping high-performance coating layer is 0.8-1.5 mm.
As shown in the combined drawings 1 and 2, the aviation interior sound-insulation heat-preservation plate is a plate body with a hexagonal structure, and the hexagonal structure can effectively improve the attractiveness and stability of an interior decoration plate and improve the mechanical property of the interior decoration plate. Furthermore, the outer wall plate 10 and the sound-insulation heat-preservation interlayer 30, and the sound-insulation heat-preservation interlayer 30 and the sound-insulation inner wall plate 50 are all cured and bonded through adhesives, wherein the curing temperature is 110-150 ℃, the curing time is 0.5-2 h, and the pressure is 0.3-1.0 MPa.
The aviation interior sound insulation and heat preservation plate in the embodiment has good heat preservation and sound insulation performance, and obviously hinders the propagation of noise and the dissipation of heat.
The above description is only an embodiment of the present invention, but the design concept of the present invention is not limited thereto, and any insubstantial modifications made by using the design concept should fall within the scope of infringing the protection scope of the present invention. However, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention are still within the protection scope of the technical solution of the present invention.
Claims (9)
1. The aviation interior sound-insulation heat-preservation plate is characterized by comprising an outer wall plate (10), a sound-insulation heat-preservation interlayer (30) and a sound-insulation inner wall plate (50) which are sequentially stacked; a plurality of sound-absorbing micropores (20) are uniformly distributed on the outer wall plate (10), and the sound-absorbing micropores (20) are of inclined hole structures; and a sound insulation damping film (40) is arranged on the outer surface of the sound insulation inner wall plate (50).
2. An aviation interior sound-insulation heat-preservation plate as claimed in claim 1, wherein: the included angle between the axis of the sound-absorbing micropores (20) and the surface of the outer wall plate (10) is 60-80 degrees, and the inclination directions of the sound-absorbing micropores (20) are consistent.
3. The aircraft interior sound insulation and heat preservation plate of claim 1, characterized in that: the diameter of each sound-absorbing micropore (20) is phi 0.8 mm-phi 1.5mm, and the distance between every two adjacent sound-absorbing micropores (20) is 2-3 mm.
4. The aircraft interior sound insulation and heat preservation plate of claim 1, characterized in that: on the surface of the outer wall plate (10), the total area of the sound-absorbing micropores (20) accounts for 20-40% of the surface area of the outer wall plate (10).
5. The aircraft interior sound insulation and heat preservation plate of claim 1, characterized in that: the sound-insulation and heat-preservation sandwich layer (30) is internally of a honeycomb structure formed by a plurality of honeycomb unit cells (60), and each honeycomb unit cell (60) is filled with an embedded material (70) for heat insulation and preservation.
6. The aircraft interior sound insulation and heat preservation plate of claim 1, characterized in that: the sound insulation damping film (40) is a water-based damping high-performance coating layer.
7. An aviation interior sound-insulation heat-preservation plate as claimed in claim 6, wherein: the thickness of the water-based damping high-performance coating layer is 0.8-1.5 mm.
8. An aviation interior sound-insulation heat-preservation plate as claimed in claim 1, wherein: the aviation interior sound-insulation and heat-preservation plate is a plate body with a hexagonal structure, and the outer wall plate (10) and the sound-insulation and heat-preservation interlayer (30) as well as the sound-insulation and heat-preservation interlayer (30) and the sound-insulation inner wall plate (50) are solidified and bonded through an adhesive.
9. An aviation interior sound-insulation heat-preservation plate as claimed in claim 1, wherein: the sound insulation inner wall plate (50) is of a plate-shaped structure formed by bonding a plurality of layers of superfine glass fiber reinforced fabrics, foam and unsaturated polyester resin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220573620.4U CN217022866U (en) | 2022-03-16 | 2022-03-16 | Aviation interior sound insulation heated board |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220573620.4U CN217022866U (en) | 2022-03-16 | 2022-03-16 | Aviation interior sound insulation heated board |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217022866U true CN217022866U (en) | 2022-07-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220573620.4U Active CN217022866U (en) | 2022-03-16 | 2022-03-16 | Aviation interior sound insulation heated board |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217022866U (en) |
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- 2022-03-16 CN CN202220573620.4U patent/CN217022866U/en active Active
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