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CN119329176A - A process for forming atomic oxygen resistant composite materials - Google Patents

A process for forming atomic oxygen resistant composite materials Download PDF

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Publication number
CN119329176A
CN119329176A CN202411713421.9A CN202411713421A CN119329176A CN 119329176 A CN119329176 A CN 119329176A CN 202411713421 A CN202411713421 A CN 202411713421A CN 119329176 A CN119329176 A CN 119329176A
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CN
China
Prior art keywords
composite material
resin
carbon fiber
atomic oxygen
based carbon
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202411713421.9A
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Chinese (zh)
Inventor
王梓桥
周秀燕
匡乃航
陈浩然
刘甲秋
许崇煜
朱楠
李金儒
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Harbin FRP Institute Co Ltd
China National Building Material Group Co Ltd CNBM
Original Assignee
Harbin FRP Institute Co Ltd
China National Building Material Group Co Ltd CNBM
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Filing date
Publication date
Application filed by Harbin FRP Institute Co Ltd, China National Building Material Group Co Ltd CNBM filed Critical Harbin FRP Institute Co Ltd
Priority to CN202411713421.9A priority Critical patent/CN119329176A/en
Publication of CN119329176A publication Critical patent/CN119329176A/en
Pending legal-status Critical Current

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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
    • 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
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • 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
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/18—Layered products comprising a layer of synthetic resin characterised by the use of special additives
    • B32B27/20—Layered products comprising a layer of synthetic resin characterised by the use of special additives using fillers, pigments, thixotroping agents
    • 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 shape; Layered products comprising a layer 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 shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/18—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by an internal layer formed of separate pieces of material which are juxtaposed side-by-side
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/0012—Mechanical treatment, e.g. roughening, deforming, stretching
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/04—Punching, slitting or perforating
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B2038/0052—Other operations not otherwise provided for
    • B32B2038/0076—Curing, vulcanising, cross-linking
    • 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
    • B32B2307/70—Other properties
    • B32B2307/714—Inert, i.e. inert to chemical degradation, corrosion

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Laminated Bodies (AREA)

Abstract

A process for forming an atomic oxygen resistant composite material. The invention belongs to the technical field of aerospace materials. The invention solves the problems that the composite material is not resistant to atomic oxygen in the aerospace environment, and the adhesion process is easy to cause debonding and bubbles, etc. According to the invention, the alloy material and the resin-based carbon fiber composite material are coated with glue solution, and then the alloy material and the resin-based carbon fiber composite material are bonded, so that the atomic oxygen resistant composite material is obtained. According to the invention, the thickness uniformity of the adhesive layer can be effectively ensured by the compression roller, the adhesive layer uniformity can better bond the metal protective layer on the surface of the resin-based carbon fiber composite material, the forming process of the invention ensures that the atomic oxygen resistant composite material does not have the debonding phenomenon in the aerospace environment, and the service life of the aerospace instrument is effectively prolonged.

Description

Forming process of atomic oxygen resistant composite material
Technical Field
The invention belongs to the technical field of aerospace materials, and particularly relates to a forming process of an atomic oxygen resistant composite material.
Background
Atomic oxygen is formed by the photodissociation of oxygen molecules by solar radiation. On one hand, atomic oxygen has strong oxidizing property, can directly react with materials, can generate serious oxidative degradation on organic materials and partial metal materials on the surface of a spacecraft, and can cause thickness reduction, surface morphology change, thermal/electrical property change and even complete failure of the materials, on the other hand, when the spacecraft operates at a high speed, the atomic oxygen impacts the surface of the spacecraft with great energy, and when the atomic oxygen with strong oxidizing property, large flux and high energy acts on the surface of the spacecraft, the degradation and performance degradation of the surface materials can be caused, so that the normal operation and the service life of the spacecraft are influenced. For the resin composite material and the carbon fiber composite material, the resin composite material and the carbon fiber composite material are easily influenced by atomic oxygen, ultraviolet rays and the like in a space environment, so that the physical and chemical properties of the resin composite material and the carbon fiber composite material are attenuated, the suitability is poor, and the normal operation of a spacecraft is influenced. In order to ensure long-term on-orbit reliable operation of the spacecraft, necessary protection is required for the cabin outer components in the spacecraft aiming at the atomic oxygen resistant requirement of the domestic low-orbit long-life spacecraft.
The proportion of the composite material in the structural weight of an airplane and a spacecraft is obviously increased, the use part is wider, but the composite material does not have the atomic oxygen resistance, in order to improve the defect in the prior art, a layer of atomic oxygen resisting material is covered outside the composite material by adopting a method of spraying paint, coating and pasting, the loss of the spraying paint and the coating is serious, the service life is short, the pasting method has long service life although the loss is less, the pasting method is easy to have the problems of falling off or having bubbles and the like, and the material loss influences the use. Therefore, a new process method is urgently needed, the problems that the composite material is affected by atomic oxygen, debonding and foaming occur in a pasting method can be solved, the service life of the aerospace instrument is prolonged, and the method has important significance for the permanent development of aerospace.
Disclosure of Invention
The invention aims to solve the problems that the composite material is not resistant to atomic oxygen in an aerospace environment, debonding and bubbles are easy to occur in a pasting process, the service life of aerospace instruments is prolonged, and the like.
The technical scheme of the invention is as follows:
One of the purposes of the invention is to provide a forming process of an atomic oxygen resistant composite material, which comprises the following steps:
s1, processing a metal protection layer, namely carrying out acid washing processing on the metal protection layer;
S2, carrying out surface treatment on the resin-based carbon fiber composite material, namely lightly polishing the resin-based carbon fiber composite material by using 800-1000-mesh sand paper;
s3, glue solution preparation, namely uniformly stirring epoxy glue A, B components according to a mass ratio of 5:1, and then placing the mixture in a vacuum tank for degassing;
s4, coating a metal protective layer adhesive layer, namely cutting the metal protective layer into a plurality of long strips with the length of 100-500mm and the width of 50-100mm, punching a vent hole with the diameter of 2mm on the central axis of the broadside every 100mm, uniformly extruding the adhesive solution on the metal protective layer, and uniformly rolling;
S5, coating a resin-based carbon fiber composite material adhesive layer, namely placing the resin-based carbon fiber composite material on a platform, uniformly adding the adhesive solution into an adhesive coating area on the surface of the resin-based carbon fiber composite material for a plurality of times, and uniformly rolling;
And S6, paving a metal protection layer on the surface of the resin-based carbon fiber composite material, namely paving the metal protection layer on the surface of the resin-based carbon fiber composite material, uniformly rolling, paving a next metal protection layer after rolling, paving the metal protection layer and the metal protection layer in a lap joint mode, paving a layer of soft film on the uppermost surface after paving, filling the soft film into a vacuum bag, pressurizing in vacuum, and then adding the soft film into an autoclave for curing to obtain the atomic oxygen resistant composite material.
Further defined, the metal protection layer in S1 is an aluminum foil or aluminum alloy material, and the thickness is 25-50 μm.
Further limited, the pressure of the vacuum tank in the step S3 is-80 to-90 kpa, and the degassing time is 15-20min.
Further defined is a glue thickness in S4 of 10-20 μm and a glue thickness in S5 of 30-40 μm.
Further defined, the autoclave temperature in S6 is 45-85 ℃, the pressure is 200+ -5 Kpa, and the curing time is 1-3h.
Further defined is that the overlap width between the metal protection layer and the metal protection layer in S6 is 2-10mm.
Further limited, the soft film in S6 is silicon rubber with the thickness of 1-2mm, the hardness of 40-80HB, the tensile strength of 5-10 megapascals and the elongation of 200-300%.
Further defined, all of the above steps are accomplished in an environment having a temperature of 15-35 ℃ and a relative humidity of 30% -60%.
The second object of the present invention is to provide an atomic oxygen resistant composite material, which is prepared by the above molding process.
The invention further aims to provide an atomic oxygen resistant composite material applied to aerospace.
The beneficial effects of the invention are as follows:
According to the application, the glue coating and rolling of the special press roller can effectively ensure that the glue layer is uniform in thickness, the glue layer is uniform, the metal protective layer can be better adhered to the surface of the composite material, the function of resisting atomic oxygen is realized, the problem that bubbles can appear when the metal protective layer is combined with the composite material in a vacuum environment is solved, and the metal protective layer and the composite material are free from debonding and bubble generation after tens of thousands of times of high and low temperature cycles, so that the service life of the spacecraft cabin in orbit for 15 years can be satisfied.
Drawings
FIG. 1 is a vacuum autoclave;
FIG. 2 is a photograph of the atomic oxygen resistant composite of example 1 after vacuum autoclave experiments;
FIG. 3 is a photograph of an atomic oxygen resistant composite of comparative example 1 after vacuum autoclave experiments;
FIG. 4 is a graph showing the mass loss of atomic oxygen stripping in example 1 and comparative example 1;
Fig. 5 is a diagram of an experimental bonding process.
Detailed Description
The present invention will be described in further detail with reference to the following examples in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
The terms "comprising," "including," "having," "containing," or any other variation thereof, as used in the following embodiments, are intended to cover a non-exclusive inclusion. For example, a composition, step, method, article, or apparatus that comprises a list of elements is not necessarily limited to only those elements but may include other elements not expressly listed or inherent to such composition, step, method, article, or apparatus.
When an equivalent, concentration, or other value or parameter is expressed as a range, preferred range, or a range bounded by a list of upper preferable values and lower preferable values, this is to be understood as specifically disclosing all ranges formed from any pair of any upper range limit or preferred value and any lower range limit or preferred value, regardless of whether ranges are separately disclosed. For example, when ranges of "1 to 5" are disclosed, the described ranges should be construed to include ranges of "1 to 4", "1 to 3", "1 to 2 and 4 to 5", "1 to 3 and 5", and the like. When a numerical range is described herein, unless otherwise indicated, the range is intended to include its endpoints and all integers and fractions within the range. In the description and claims of the application, the range limitations may be combined and/or interchanged, if not otherwise specified, including all the sub-ranges subsumed therein.
The indefinite articles "a" and "an" preceding an element or component of the invention are not limited to the requirement (i.e. the number of occurrences) of the element or component. Thus, the use of "a" or "an" should be interpreted as including one or at least one, and the singular reference of an element or component includes the plural reference unless the amount clearly dictates otherwise.
Reference to "one embodiment" or "an embodiment" of the present invention means that a particular feature, structure, or characteristic may be included in at least one implementation of the present invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments.
The endpoints of the ranges and any values disclosed in the invention are not limited to the precise range or value, and the range or value should be understood to include values close to the range or value. For numerical ranges, one or more new numerical ranges may be found between the endpoints of each range, between the endpoint of each range and the individual point value, and between the individual point value, in combination with each other, and are to be considered as specifically disclosed herein.
The experimental methods used in the following examples are conventional methods unless otherwise specified. The materials, reagents, methods and apparatus used, without any particular description, are those conventional in the art and are commercially available to those skilled in the art.
Example 1:
S1, treating a metal protective layer, namely selecting an aluminum foil with the thickness of 50 mu m, and carrying out surface phosphoric acid anodizing treatment for 2 hours;
S2, carrying out surface treatment on a resin-based carbon fiber composite material (the volume of the carbon fiber accounts for 60 percent and the volume of the resin accounts for 40 percent), namely lightly polishing the surface of the composite material by using 1000-mesh sand paper;
S3, preparing glue solution, namely uniformly stirring 100g of HB01 glue solution, 100g of component A and 20g of component B, and then placing the glue solution in a vacuum tank for degassing, wherein the pressure of the vacuum tank is-90 kpa, and the degassing time is 20min;
S4, coating a metal protective layer adhesive layer, namely cutting the metal protective layer into a plurality of strips with the length of 500mm and the width of 100mm, punching a vent hole with the diameter of 2mm on the central axis of the wide edge every 100mm, bonding green high-temperature-resistant pressure-sensitive adhesive tapes on two sides of the metal protective layer, placing the metal protective layer on a metal plate, bonding one surface with the pressure-sensitive adhesive tapes with the metal plate, uniformly extruding the adhesive solution on the metal protective layer, uniformly rolling the adhesive solution with the adhesive thickness of 20 mu m;
S5, coating a resin-based carbon fiber composite material adhesive layer, namely placing the resin-based carbon fiber composite material on a platform, averagely dividing HB01 adhesive solution for 2 times, adding the resin-based carbon fiber composite material surface, and uniformly rolling, wherein the adhesive thickness is 40 mu m;
S6, paving a metal protective layer on the surface of the resin-based carbon fiber composite material, namely placing the metal protective layer on the surface of the resin-based carbon fiber composite material, rolling by using a rubber roller with the thickness of 100mm, tearing off a pressure-sensitive adhesive tape after rolling, paving a next metal protective layer, paving a layer of soft film material on the metal protective layer, placing the soft film material in a vacuum bag after the metal protective layer is paved, pressurizing in vacuum, and then adding the vacuum bag into an autoclave for curing, wherein the temperature of the autoclave is 80 ℃, the pressure is 200+/-5 KPa, and the curing time is 2h, so that the atomic oxygen resistant composite material is obtained;
All the steps are completed in a hundred thousand-level clean workshop, and the ambient temperature is 26 ℃ and the relative humidity is 40%.
Comparative example 1:
s1, processing a metal protection layer, namely selecting an aluminum foil with the thickness of 15 mu m, and polishing the surface;
S2, carrying out surface treatment on the resin-based carbon fiber composite material, namely lightly polishing the surface of the composite material by 600-mesh sand paper;
S3, preparing a glue solution, namely uniformly stirring 100g of HB01 glue solution, 20g of component A and component B;
s4, coating a metal protective layer adhesive layer, namely uniformly extruding adhesive solution on the metal protective layer, wherein the adhesive thickness is 100 mu m, and uniformly rolling;
s5, coating a resin-based carbon fiber composite material adhesive layer (the volume of the carbon fiber accounts for 60 percent and the volume of the resin accounts for 40 percent), namely placing the resin-based carbon fiber composite material on a platform, adding HB01 adhesive solution on the surface of the resin-based carbon fiber composite material at one time, and uniformly rolling to obtain the adhesive with the adhesive thickness of 100 mu m;
S6, paving a metal protection layer on the surface of the resin-based carbon fiber composite material, namely placing the metal protection layer on the surface of the resin-based carbon fiber composite material, filling the resin-based carbon fiber composite material into a vacuum bag after the paving, pressurizing the vacuum bag, maintaining the vacuum pressure at-85 kpa, and curing for 24 hours to obtain an atomic oxygen resistant composite material;
All the steps are completed in a hundred thousand-level clean workshop, and the ambient temperature is 26 ℃ and the relative humidity is 40%.
Vacuum autoclave test:
the experimental conditions are +/-100 ℃, the vacuum degree is 10 -4, and the cycle times are 12.
As can be seen from fig. 2 and 3, the surface of example 1 treated by the present experimental process was still flat, no bubbles were generated, no protrusions were generated, and excellent material properties were exhibited, while the surface of comparative example 1 treated by the present experimental process was provided with a plurality of bubbles and wrinkles.
Atomic oxygen stripping mass loss test:
The experimental conditions are that the atomic oxygen irradiation test is carried out on plasma type atomic oxygen ground simulation equipment. Oxygen plasma is generated by magnetic mirror microwave ECR method. The atomic oxygen energy is 5eV, the flux rate is 5.0X11015O/(cm 2. Multidot.s), and when the irradiation fluence reaches 10.0X105O/cm 2, the material is subjected to performance test. The test results are shown in fig. 4, and as can be seen from fig. 4, the atomic oxygen stripping mass loss of example 1 is only 0.1%, and the atomic oxygen stripping mass loss of comparative example 1 is 0.8%, which shows that the atomic oxygen resistant composite material treated by the experimental process can effectively resist the erosion of space atomic oxygen, and meets the use requirement of spacecraft materials.
In the foregoing, the present invention is merely preferred embodiments, which are based on different implementations of the overall concept of the invention, and the protection scope of the invention is not limited thereto, and any changes or substitutions easily come within the technical scope of the present invention as those skilled in the art should not fall within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims (10)

1. The forming process of the atomic oxygen resistant composite material is characterized by comprising the following steps of:
s1, processing a metal protection layer, namely carrying out acid washing processing on the metal protection layer;
S2, carrying out surface treatment on the resin-based carbon fiber composite material, namely lightly polishing the resin-based carbon fiber composite material by using 800-1000-mesh sand paper;
s3, glue solution preparation, namely uniformly stirring epoxy glue A, B components according to a mass ratio of 5:1, and then placing the mixture in a vacuum tank for degassing;
s4, coating a metal protective layer adhesive layer, namely cutting the metal protective layer into a plurality of long strips with the length of 100-500mm and the width of 50-100mm, punching a vent hole with the diameter of 2mm on the central axis of the broadside every 100mm, uniformly extruding the adhesive solution on the metal protective layer, and uniformly rolling;
S5, coating a resin-based carbon fiber composite material adhesive layer, namely placing the resin-based carbon fiber composite material on a platform, uniformly adding the adhesive solution into an adhesive coating area on the surface of the resin-based carbon fiber composite material for a plurality of times, and uniformly rolling;
And S6, paving a metal protection layer on the surface of the resin-based carbon fiber composite material, namely paving the metal protection layer on the surface of the resin-based carbon fiber composite material, uniformly rolling, paving a next metal protection layer after rolling, paving the metal protection layer and the metal protection layer in a lap joint mode, paving a layer of soft film on the uppermost surface after paving, filling the soft film into a vacuum bag, pressurizing in vacuum, and then adding the soft film into an autoclave for curing to obtain the atomic oxygen resistant composite material.
2. The molding process according to claim 1, wherein the metal protection layer in S1 is an aluminum foil or an aluminum alloy material, and has a thickness of 25-50 μm.
3. The molding process according to claim 1, wherein the vacuum tank pressure in S3 is-80 to-90 kpa and the degassing time is 15-20min.
4. The molding process according to claim 1, wherein the glue thickness in S4 is 10-20 μm and the glue thickness in S5 is 30-40 μm.
5. The molding process of claim 1, wherein the autoclave temperature in S6 is 45-85 ℃, the pressure is 200+ -5 Kpa, and the curing time is 1-3h.
6. The molding process according to claim 1, wherein the overlap width between the metal protective layer and the metal protective layer in S6 is 2-10mm.
7. The molding process according to claim 1, wherein the soft film in S6 is a silicone rubber having a thickness of 1 to 2mm, a hardness of 40 to 80HB, a tensile strength of 5 to 10 MPa, and an elongation of 200 to 300%.
8. The molding process of claim 1, wherein all of the above steps are performed in an environment having a temperature of 15-35 ℃ and a relative humidity of 30% -60%.
9. An atomic oxygen resistant composite material prepared by the forming process of any one of claims 1-8.
10. Use of the atomic oxygen resistant composite of claim 9 in aerospace.
CN202411713421.9A 2024-11-27 2024-11-27 A process for forming atomic oxygen resistant composite materials Pending CN119329176A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202411713421.9A CN119329176A (en) 2024-11-27 2024-11-27 A process for forming atomic oxygen resistant composite materials

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202411713421.9A CN119329176A (en) 2024-11-27 2024-11-27 A process for forming atomic oxygen resistant composite materials

Publications (1)

Publication Number Publication Date
CN119329176A true CN119329176A (en) 2025-01-21

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