CN117048140A - Quick heat dissipation aviation combined material and radome fairing - Google Patents

Quick heat dissipation aviation combined material and radome fairing Download PDF

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Publication number
CN117048140A
CN117048140A CN202311314606.8A CN202311314606A CN117048140A CN 117048140 A CN117048140 A CN 117048140A CN 202311314606 A CN202311314606 A CN 202311314606A CN 117048140 A CN117048140 A CN 117048140A
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China
Prior art keywords
heat
layer
core
heat conduction
rapid thermal
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Pending
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CN202311314606.8A
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Chinese (zh)
Inventor
邱涛
白立安
李丹
张贺川
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Xi'an Yuanfei Aerotechnics Development Co ltd
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Xi'an Yuanfei Aerotechnics Development Co ltd
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Priority to CN202311314606.8A priority Critical patent/CN117048140A/en
Publication of CN117048140A publication Critical patent/CN117048140A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/005—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile
    • B32B9/007—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile comprising carbon, e.g. graphite, composite carbon
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B9/047—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material made of fibres or filaments
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2250/00—Layers arrangement
    • B32B2250/40—Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2250/00—Layers arrangement
    • B32B2250/42—Alternating layers, e.g. ABAB(C), AABBAABB(C)
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2255/00—Coating on the layer surface
    • B32B2255/02—Coating on the layer surface on fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/302—Conductive
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2457/00—Electrical equipment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft

Abstract

The invention discloses a fast heat dissipation aviation composite material, which comprises a core layer and a matrix layer, wherein the core layer comprises a heat conduction structure, and the heat conduction structure is made of nanoscale graphene materials; the matrix layer is made of heat-conducting carbon fibers, the highest heat conductivity coefficient of the heat-conducting carbon fibers can reach 700W/mk, the heat conductivity coefficient can exceed that of copper, and meanwhile, the heat-conducting carbon fibers have good mechanical properties and excellent heat-conducting and radiation heat-radiating capabilities, so that the heat-conducting and heat-radiating properties of the fast heat-radiating aviation composite material are improved; every two adjacent base body layers between all be provided with the core layer, the core layer includes heat conduction structure, and heat conduction structure is made by nano-scale graphene material, and graphite alkene has very good heat conduction performance, and nano-scale graphite alkene's coefficient of heat conduction is up to 5300W/mk, sets up the heat conduction structure of graphite alkene material between the base body layer, reinforcing quick heat dissipation aviation combined material's heat conduction heat dispersion. The invention also provides a fairing, which is made of the rapid heat dissipation aviation composite material.

Description

Quick heat dissipation aviation combined material and radome fairing
Technical Field
The invention relates to the technical field of fast heat dissipation aviation composite materials, in particular to a fast heat dissipation aviation composite material and a fairing.
Background
With the progress of science and technology, the electronic industry has been rapidly advancing. In particular, the modern chip technology is developed at a high speed, various instruments and equipment are more advanced, and the functions are more and more extensive. There is also increasing use in aircraft, so to speak, that any weapon is a furnishing without these advanced instruments.
The avionic device is characterized by that it utilizes advanced digital electronic technology, further develops toward high-integration and intelligent mode, and uses microcomputer and multiplexing data bus as tie, and organically links the sensor, display and controller with flight control system, engine control system and fire control system so as to implement high-integration among all the systems of the aircraft. And a perfect self-checking and fault monitoring and fault alarming means are adopted, so that the accuracy and reliability of information measurement are improved.
Advances in science and technology invent and manufacture a wide variety of advanced aircraft, particularly unmanned aerial vehicle families. The unmanned plane is an advanced weapon with low cost and high killing efficiency, all aircrafts and optical equipment, electronic equipment and chips of the unmanned plane, an instrument cabin of the unmanned plane is required to be provided with a shielding cover or a fairing for preventing the airy, rain and sun from being exposed to the sun from aerodynamic consideration and the equipment, all photoelectric equipment and instruments are sealed in a narrow space by the structural materials, heat energy can be generated when any electronic equipment works, and if the electronic equipment cannot conduct heat and dissipate the heat timely, the performance and the use precision of the optical instrument can be influenced under the high-temperature environment. In extreme cases, even if they are not functional, any product of the aircraft is characterized by a high strength and light weight, so that these shields or fairings are mostly manufactured from advanced composite materials, which consist of both reinforcing materials and structural adhesives. The general adhesive body is resin such as epoxy resin, the resin is an insulator which does not conduct heat and dissipate heat, and the reinforcing materials such as carbon fiber, glass fiber, aramid fiber and ceramic fiber are not ideal materials for conducting heat and dissipating heat. Although advanced composite materials, such as carbon-epoxy composite materials, are widely used in the field of light weight and high strength aerospace, a problem of heat dissipation and conduction is not well solved, and the wide use of the materials on shielding covers and fairings is affected.
Disclosure of Invention
The invention aims to provide a rapid heat dissipation aviation composite material and a fairing, so as to solve the problems in the prior art, enhance the heat conduction and heat dissipation performance of the rapid heat dissipation aviation composite material and improve the heat dissipation capacity of aviation components.
In order to achieve the above object, the present invention provides the following solutions: the invention provides a fast heat dissipation aviation composite material, which comprises the following components:
the solar cell comprises a core layer, wherein the core layer comprises a heat conduction structure, and the heat conduction structure is made of nanoscale graphene materials;
the base layer is made of heat-conducting carbon fibers, and the number of the base layer is at least two; the core layer is arranged between every two adjacent matrix layers, and the core layer is connected with the matrix layers.
Preferably, the core layer further comprises a core frame, and the heat conducting structure is filled in the core frame.
Preferably, the core frame includes a columnar channel, two ends of the columnar channel are respectively arranged towards the substrate layers at two sides of the core layer, the heat conducting structure is a columnar structure matched with the columnar channel, and the heat conducting structure is arranged in the columnar channel.
Preferably, the core frame is in a honeycomb structure, the honeycomb opening of the core frame is arranged towards the substrate layer, and the heat conduction structure is filled in the honeycomb of the core frame.
Preferably, a skin layer is respectively arranged on the top of the substrate layer of the top layer and the bottom of the substrate layer of the bottom layer.
Preferably, the skin layer and the core frame are both made of metal materials.
Preferably, spray coating layers are respectively arranged on the top of the top substrate layer and the bottom of the bottom substrate layer.
Preferably, the projected area ratio of the thermally conductive structure to the core layer is 5% in a plane parallel to the base layer.
Preferably, the core layer and the matrix layer are bonded by using a heat-conducting adhesive and then thermally pressed and solidified into an integral structure.
The invention also provides a fairing, which is made of the rapid heat dissipation aviation composite material.
Compared with the prior art, the invention has the following technical effects:
the rapid heat dissipation aviation composite material comprises a core layer and a matrix layer, wherein the matrix layer is made of heat conduction carbon fibers, the highest heat conduction coefficient of the heat conduction carbon fibers can reach 700W/mk, the heat conduction coefficient can exceed copper, and meanwhile, the rapid heat dissipation aviation composite material has good mechanical property and excellent heat conduction and radiation heat dissipation capacity, and the heat conduction and heat dissipation performance of the rapid heat dissipation aviation composite material is improved; every two adjacent base body layers between all be provided with the core layer, the core layer includes heat conduction structure, and heat conduction structure is made by nano-scale graphene material, and graphite alkene has very good heat conduction performance, and nano-scale graphite alkene's coefficient of heat conduction is up to 5300W/mk, sets up the heat conduction structure of graphite alkene material between the base body layer, can further strengthen the heat conduction heat dispersion of quick heat dissipation aviation combined material.
The invention also provides a fairing, which is made of the rapid heat dissipation aviation composite material, so that the heat dissipation capacity of the fairing is improved, the normal operation of aviation equipment is ensured, and the service life of aviation electronic equipment is prolonged.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic structural diagram of a composite material of the prior art;
FIG. 2 is a schematic structural diagram of a fast heat dissipating aerospace composite disclosed in an embodiment of the present invention;
FIG. 3 is an isometric view of a disclosed fast heat dissipating aerospace composite according to an embodiment of the present invention;
fig. 4 is a schematic cross-sectional view of a fast heat dissipating aerospace composite disclosed in an embodiment of the invention.
Wherein 1 is a core layer, 2 is a matrix layer, 3 is a heat conduction structure, 4 is a core frame, and 5 is a skin layer.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a rapid heat dissipation aviation composite material and a fairing, so as to solve the problems in the prior art, enhance the heat conduction and heat dissipation performance of the rapid heat dissipation aviation composite material and improve the heat dissipation capacity of aviation components.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
The invention provides a rapid heat dissipation aviation composite material, which comprises a core layer 1 and a matrix layer 2, wherein the core layer 1 comprises a heat conduction structure 3, and the heat conduction structure 3 is made of nanoscale graphene materials; the matrix layers 2 are made of heat-conducting carbon fibers, and the number of the matrix layers 2 is at least two; a core layer 1 is arranged between every two adjacent matrix layers 2, and the core layer 1 is connected with the matrix layers 2.
The rapid heat dissipation aviation composite material comprises a core layer 1 and a matrix layer 2, wherein the matrix layer 2 is made of heat conduction carbon fibers, the highest heat conduction coefficient of the heat conduction carbon fibers can reach 700W/mk, the heat conduction coefficient can exceed copper, the high-strength light-weight characteristic of the conventional carbon fibers is reserved, and meanwhile, the rapid heat dissipation aviation composite material has good mechanical property and excellent heat conduction and radiation heat dissipation capacity, and the heat conduction and heat dissipation performance of the rapid heat dissipation aviation composite material is improved; every two adjacent base body layers 2 between all be provided with core body layer 1, core body layer 1 includes heat conduction structure 3, and heat conduction structure 3 is made by nano-scale graphite alkene material, and graphite alkene has very good heat conduction performance, and nano-scale graphite alkene's coefficient of heat conduction is up to 5300W/mk, sets up heat conduction structure 3 of graphite alkene material between base body layer 2, can further strengthen quick heat dissipation aviation combined material's heat conduction heat dispersion.
In practical application, when the rapid heat dissipation aviation composite material is prepared, an autoclave molding process is adopted, a male die wet molding mode is adopted, a layer of heat conduction carbon fiber with the heat conduction coefficient of 700W/mk can be paved after a layer of heat conduction glue is coated on a die, the heat conduction carbon fiber is taken as a substrate layer 2, a small amount of nano-scale graphene with the heat conduction performance of 5300W/mk is scattered on the surface of the heat conduction carbon fiber to be taken as a heat conduction structure 3, then a layer of heat conduction carbon fiber is coated and paved again to be taken as another substrate layer 2, a small amount of nano-scale graphene is scattered on the surface to be taken as a heat conduction structure 3 of another core layer 1, and the steps are sequentially circulated until the heat conduction carbon fiber is paved to the specified thickness of the rapid heat dissipation aviation composite material; the mold is a working part of a fast heat dissipation aviation composite production mold, and is a common means for those skilled in the art, and is not described herein; meanwhile, the matrix layer 2 is paved until the matrix layer is paved to the specified thickness of the rapid heat dissipation aviation composite material, so that the structural integrity of the rapid heat dissipation aviation composite material is ensured. The difference between the epoxy carbon prepreg and the solid carbon fiber in the prior art is that the epoxy carbon prepreg is not used, but the epoxy heat-conducting glue with excellent heat conduction performance and the heat-conducting carbon fiber with excellent heat conduction performance are used, so that the heat conduction and heat dissipation performance of the rapid heat dissipation aviation composite material is effectively improved.
In other specific embodiments of the present invention, the core layer 1 further includes a core frame 4, the heat conducting structure 3 is filled in the core frame 4, and the setting of the core frame 4 can provide a powerful support for the heat conducting structure 3, and meanwhile, the fixing between the core layer 1 and the base layer 2 is convenient, so that the molding quality of the fast heat dissipation aviation composite material of the present invention is ensured.
When setting up core frame 4, core frame 4 includes the column passageway, and the both ends of column passageway set up towards the basal body layer 2 of core layer 1 both sides respectively, and heat conduction structure 3 is the column structure with column passageway looks adaptation, and heat conduction structure 3 sets up in the column passageway, when core frame 4 provides support, positioning action for heat conduction structure 3, sets up the column passageway and can effectively avoid core frame 4 to cause between heat conduction structure 3 and basal body layer 2 and shelter from, ensures that heat conduction structure 3 can exert heat conduction and heat dissipation action.
In practical application, the core frame 4 can be a honeycomb structure, the honeycomb opening of the core frame 4 is arranged towards the substrate layer 2, the heat conducting structure 3 is filled in the honeycomb of the core frame 4, the core frame 4 is made of honeycomb plates, the production and manufacturing difficulty of the rapid heat dissipation aviation composite material is reduced, and meanwhile, the heat conducting structure 3 is conveniently filled.
In addition, in order to further enhance the structural integrity of the rapid heat dissipation aviation composite, the top of the top substrate layer 2 and the bottom of the bottom substrate layer 2 are respectively provided with a skin layer 5, and meanwhile, the structural strength of the rapid heat dissipation aviation composite is improved.
In other embodiments of the present invention, the skin layer 5 and the core frame 4 may be made of metal, for example, the core frame 4 is made of aluminum honeycomb, the skin layer 5 is made of aluminum, the skin layer 5 and the core frame 4 are made of aluminum, for example, the skin layer 5 is made of a 0.2mm thick mirror aluminum plate with a brand of 3003-O, so that the heat conductivity and heat dissipation performance of the rapid thermal composite material can be further enhanced, and the heat conductivity coefficient of the rapid thermal composite material of the present invention can reach more than 500W/mk, and exceeds the heat conductivity coefficient of metallic silver and metallic copper.
When the skin layer 5 is not arranged, the top of the top layer matrix layer 2 and the bottom of the bottom layer matrix layer 2 can be respectively provided with a spray coating, and the top of the top layer matrix layer 2 and the bottom of the bottom layer matrix layer 2 are coated with a heat conducting material to form a spray coating, so that the heat conducting and radiating performance of the fast radiating aviation composite material can be improved.
It should be emphasized that in this embodiment, in the plane parallel to the substrate layer 2, the projected area ratio of the heat conducting structure 3 to the core layer 1 is 5%, and in practical application, the projected area ratio of the heat conducting structure 3 to the core layer 1 may be adjusted according to the requirement of the heat conductivity coefficient of the fast heat dissipation aviation composite material. It should be noted that, when the heat conducting structure 3 is filled, the space filling can be performed according to a certain rule, or the filling can be performed by adopting a random filling mode, or the distribution of the heat conducting structures 3 in different areas of the rapid heat dissipation aviation composite material can be adjusted according to the later working environment of the rapid heat dissipation aviation composite material and the heat conduction and dissipation requirements of different areas, so that the adaptability of the rapid heat dissipation aviation composite material is improved.
In actual production, after the core layer 1 and the matrix layer 2 are bonded by using the heat-conducting glue, the core layer and the matrix layer are sent into an autoclave for heating, pressurizing, vacuumizing and curing according to an autoclave curing process, and are cured into an integral structure.
Meanwhile, the invention also provides a fairing, which is made of the rapid heat dissipation aviation composite material, so that the heat dissipation capacity of the fairing is improved, the normal operation of aviation equipment is ensured, and the service life of aviation electronic equipment is prolonged.
The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided to facilitate understanding of the method and core ideas of the present invention; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.

Claims (10)

1. A fast heat dissipating aerospace composite comprising:
the solar cell comprises a core layer, wherein the core layer comprises a heat conduction structure, and the heat conduction structure is made of nanoscale graphene materials;
the base layer is made of heat-conducting carbon fibers, and the number of the base layer is at least two; the core layer is arranged between every two adjacent matrix layers, and the core layer is connected with the matrix layers.
2. The rapid thermal dissipation aerospace composite of claim 1, wherein: the core layer further comprises a core frame, and the heat conducting structure is filled in the core frame.
3. The rapid thermal dissipation aerospace composite of claim 2, wherein: the core frame comprises a columnar channel, two ends of the columnar channel are respectively arranged towards the substrate layers on two sides of the core layer, the heat conducting structure is a columnar structure matched with the columnar channel, and the heat conducting structure is arranged in the columnar channel.
4. A rapid thermal dissipating aerospace composite according to claim 3, wherein: the core frame is of a honeycomb structure, the honeycomb opening of the core frame faces to the substrate layer, and the heat conduction structure is filled in the honeycomb of the core frame.
5. The rapid thermal dissipation aerospace composite according to any one of claims 2-4, wherein: and the top of the substrate layer at the top layer and the bottom of the substrate layer at the bottom layer are respectively provided with a skin layer.
6. The rapid thermal dissipation aerospace composite of claim 5, wherein: the skin layer and the core body frame are made of metal materials.
7. The rapid thermal dissipation aerospace composite according to any one of claims 2-4, wherein: and spraying layers are respectively arranged at the top of the top substrate layer and the bottom of the bottom substrate layer.
8. The rapid thermal dissipation aerospace composite according to any one of claims 2-4, wherein: in a plane parallel to the substrate layer, the projected area ratio of the heat conducting structure to the core layer is 5%.
9. The rapid thermal dissipation aerospace composite of claim 1, wherein: and the core body layer and the matrix layer are bonded by using heat-conducting glue and then thermally pressed and solidified into an integral structure.
10. A fairing, characterized by: the fairing is made using the rapid thermal dissipation aerospace composite of any one of claims 1-9.
CN202311314606.8A 2023-10-12 2023-10-12 Quick heat dissipation aviation combined material and radome fairing Pending CN117048140A (en)

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Citations (4)

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