CN113927925A - Variable cross-section non-rotating body thermal protection structure and forming process - Google Patents

Variable cross-section non-rotating body thermal protection structure and forming process Download PDF

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Publication number
CN113927925A
CN113927925A CN202111181957.7A CN202111181957A CN113927925A CN 113927925 A CN113927925 A CN 113927925A CN 202111181957 A CN202111181957 A CN 202111181957A CN 113927925 A CN113927925 A CN 113927925A
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China
Prior art keywords
thermal protection
variable cross
rubber
layer
section non
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CN202111181957.7A
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Chinese (zh)
Inventor
许亚洪
倪楠楠
王召娣
顾麒麟
高家琪
蒋燕骏
卞凯
戴锋
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Jiangsu Sanqiang Composite Material Co ltd
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Jiangsu Sanqiang Composite Material Co ltd
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Priority to CN202111181957.7A priority Critical patent/CN113927925A/en
Publication of CN113927925A publication Critical patent/CN113927925A/en
Withdrawn legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/78—Moulding material on one side only of the preformed part
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/681—Component parts, details or accessories; Auxiliary operations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3005—Body finishings

Abstract

The invention belongs to the field of composite material molding, and particularly relates to a variable cross-section non-rotating body thermal protection structure and a molding process; variable cross section non-rotating body heat protection structure, it includes the metal cabin body of a variable cross section and non-gyration, its characterized in that: the invention designs a thermal protection structure and a forming process of a metal cabin body suitable for a variable-section non-revolving body, and ensures the connection reliability between the thermal protection layer and the metal cabin body.

Description

Variable cross-section non-rotating body thermal protection structure and forming process
Technical Field
The invention belongs to the field of composite material forming, and particularly relates to a variable cross-section non-rotating body thermal protection structure and a forming process.
Background
With the rapid development of the aerospace industry, the development of thermal protection systems for aircraft has become a hot issue. At present, resin-based ablation heat-proof materials are widely applied to high-end science and technology fields such as various aircrafts by virtue of a plurality of advantages of the resin-based ablation heat-proof materials.
The shell of a common aircraft is a metal revolving body, a thermal protection material is generally directly laid on the surface of the metal shell, when parts of the revolving body are provided, a laid thermal protection layer can form a complete revolving body, the overall structural strength of the thermal protection layer is good, certain impact can be borne, and the connection reliability between the thermal protection layer and the shell can be ensured, but special conditions exist, along with some design requirements, the shell of some aircraft is a non-revolving body with a variable cross section and is processed by adopting a metal material, when the thermal protection layer is processed on the surface of the non-revolving shell, the thermal protection layer is generally obtained by directly laying prepreg on the surface of the shell, because the shell is a non-revolving body, the thermal protection layer obtained by laying can not be connected into a revolving body end to end, and only the cured prepreg between the thermal protection layer and the metal shell is connected with the metal surface, the connection strength of the shell and the metal shell is poor, so that the problem that the heat protection layer is easily peeled off from the metal shell is easily caused, and the shell and the heat protection layer are made of different materials and have different material characteristics in a heated state, so that the problem that the shell and the metal shell are easily peeled off is also caused.
Disclosure of Invention
Aiming at the problems in the prior art, the invention designs a thermal protection structure for a variable-section non-revolving body and a thermal protection forming process.
The technical scheme of the invention is as follows:
variable cross section non-rotating body heat protection structure, it includes the metal cabin body of a variable cross section and non-gyration, its characterized in that: an adhesive structure is processed on the surface of the metal cabin body, a rubber surface is coated and molded on the adhesive structure, and a thermal protection layer is laid and cured on the rubber surface.
Furthermore, the attachment structure is a rough surface obtained by performing rough treatment on the surface of the metal cabin.
Furthermore, the attachment structure is a plurality of through holes arranged on the surface of the metal cabin body, and the rubber surface enters the through holes and is connected with the rubber surface coated on the back surface of the metal cabin body into a whole.
Furthermore, the attachment structure is a blind hole formed in the surface of the metal cabin, and the size of the bottom of the blind hole is larger than that of the opening.
Furthermore, the rubber surface is a multilayer composite rubber surface and comprises a structural adhesive layer connected with the attachment structure, an RTV-2 rubber layer bonded with the structural adhesive layer and a structural adhesive layer coated between the surface of the RTV-2 rubber layer and the thermal protection layer.
The variable cross-section non-rotating body thermal protection forming process is characterized in that: the forming method comprises a variable-section non-rotating metal cabin body, and comprises the following steps:
s1: randomly cutting the prepreg according to the corresponding height according to the thermal protection anatomical structure, and performing 3-in-1 on the cut prepreg;
s2: treating the surface of the metal cabin body to obtain an attachment structure on the surface of the metal cabin body;
s3: coating a layer of rubber on the surface of the metal cabin body to form a rubber surface;
s4: laying up the prepreg obtained in the step S1, laying up the prepreg in an overlapping winding mode, and paving the starting layer and the finishing layer in a mode of gradually changing material widths;
s5: and curing by adopting an autoclave molding process, and processing according to the shape requirement.
Furthermore, the prepreg of step S1 is formed by combining a silica fiber cloth uniformly coated with a phenolic resin and a phenolic prepreg.
Further, when the prepreg of step S1 is subjected to 3-in-1, each prepreg layer is misaligned by 2 mm.
Further, the rubber surface in the step 2 is a multilayer composite rubber surface, which comprises a structural adhesive layer connected with the attachment structure, an RTV-2 rubber layer bonded with the structural adhesive layer, and a structural adhesive layer coated between the surface of the RTV-2 rubber layer and the thermal protection layer.
Further, the included angle between the prepreg and the metal cabin body in the laying in the step S4 is between 17.5 ° and 18.5 °.
In conclusion, the invention has the following beneficial effects:
the invention designs a thermal protection structure for a variable cross-section non-revolving body, which is characterized in that the thermal protection structure cannot form a complete revolving structure due to the special structure of the variable cross-section non-revolving body, and the thermal protection structure and the variable cross-section non-revolving body are connected in a one-surface connection mode, so that the phenomenon of peeling between the thermal protection structure and the variable cross-section non-revolving body can occur in practical use, and the connection reliability between the thermal protection structure and the variable cross-section non-revolving body cannot be guaranteed.
Drawings
FIG. 1 is a schematic view of a thermal protective structure of a variable cross-section non-rotating body employing a first adhesion structure;
FIG. 2 is a schematic view of a thermal protective structure of a variable cross-section non-rotating body employing a second adhesion structure;
FIG. 3 is a schematic view of a thermal protective structure of a variable cross-section non-rotating body employing a third adhesion structure;
in the figure, 1 is a metal cabin, 10 is an attachment structure, 11 is a rubber surface, and 3 is a protective layer.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the drawings of the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the described embodiments of the invention without any inventive step, are within the scope of protection of the invention.
Referring to fig. 1, the variable cross-section non-revolving body thermal protection structure includes a variable cross-section non-revolving metal cabin 1, and is characterized in that: an attachment structure 10 is processed on the surface of the metal cabin body 1, a rubber surface 11 is coated and molded on the attachment structure 10, and a thermal protection layer 3 is laid and cured on the rubber surface 11.
In order to solve the problem that a heat protection layer is easy to peel off when being cured on the surface of a variable-section non-revolving body metal cabin in the prior art, the invention improves the connection reliability between the metal cabin and the heat protection layer by adding an attachment structure on the surface of the metal cabin and additionally arranging a rubber surface on the attachment structure, thereby reducing or avoiding the peeling problem between the metal cabin and the heat protection layer.
In the actual production process, if the thermal protection layer is directly cured on the surface of the metal cabin with the attachment structure, or the surface of the metal cabin is directly coated with the rubber surface without the attachment structure and the thermal protection layer is cured, the connection strength of the two modes still cannot meet the requirements of actual products.
The invention designs various attachment structures to improve the connection reliability between the metal cabin and the rubber layer, thereby ensuring the connection reliability of the thermal protection layer.
First attachment structure
The attachment structure 10 is a rough surface obtained by performing rough treatment on the surface of the metal cabin; the first adhesion structure is that a rough surface for increasing the adhesion force is formed on the surface of the metal cabin body; the surface roughness is often used: and (3) roughening the surface of the metal cabin body, or processing the surface of the metal cabin body by using a sand blasting method.
Second attachment structure
Attachment structure 10 be a plurality of through-hole 101 that sets up at the metal cabin body surface, the rubber face gets into in the through-hole and is connected integratively with the rubber face of metal cabin body back coating, this kind of attachment structure provides the through-hole that supplies the rubber entering of rubber face, in the forming process of rubber face, can form the spliced pole of being connected in the through-hole that a plurality of and rubber face are connected, the connection reliability of rubber face and the metal cabin body has been promoted, for further promotion reliability, can form another rubber face at the back coating of the metal cabin body, make the spliced pole in the through-hole be connected with the rubber face at the back and constitute a whole, form an integrative tensile structure, better reinforcing connection reliability, it is preferred, still be equipped with a plurality of through-hole when the surface machining of the metal cabin body has rough surface, both combine, can obtain better adhesive force.
Third attachment structure
Attachment structure 10 be the blind hole 102 that the metal cabin body surface set up, the bottom size of blind hole is greater than the oral area size, do not do the restriction to the shape of blind hole here, the hole of various shapes all can be used according to the needs of actual product, this kind of attachment structure is mainly when coating the rubber face, the rubber of rubber face can flow in the blind hole, and solidify in the blind hole, and because the bottom size of blind hole is greater than the oral area size, rubber need overcome the deformation power of rubber and just can be extracted from the blind hole after the solidification in the blind hole, the joint strength of rubber face and the metal cabin body has been promoted, it is preferred, the surface machining of the metal cabin body has rough surface and still is equipped with a plurality of blind hole simultaneously, both combine, can obtain better adhesive force.
Further, the rubber surface 11 is a multi-layer composite rubber surface, which comprises a structural adhesive layer connected with the attachment structure, an RTV-2 rubber layer bonded with the structural adhesive layer, and a structural adhesive layer coated between the surface of the RTV-2 rubber layer and the thermal protection layer, wherein the two structural adhesive layers are the same components and are both epoxy adhesive cured at normal temperature.
The variable cross-section non-rotating body thermal protection forming process is characterized in that: the forming method comprises a variable-section non-rotating metal cabin body, and comprises the following steps:
s1: randomly cutting the prepreg according to the corresponding height according to the thermal protection anatomical structure, and performing 3-in-1 on the cut prepreg;
s2: treating the surface of the metal cabin body to obtain an attachment structure on the surface of the metal cabin body;
s3: coating a layer of rubber on the surface of the metal cabin body to form a rubber surface;
s4: laying up the prepreg obtained in the step S1, laying up the prepreg in an overlapping winding mode, and paving the starting layer and the finishing layer in a mode of gradually changing material widths; obtaining a thermal protection layer; in the process of laying, each ply needs to be pressed by an elastic band for prepressing,
s5: and curing by adopting an autoclave molding process, and processing according to the shape requirement.
Compared with the traditional process, the forming process provided by the invention is additionally provided with the step S2 and the step S3; the connection strength of the thermal protection layer is improved through the attachment structure and the rubber surface, the attachment structure improves the connection reliability of the rubber surface and the metal cabin body, the thermal protection layer obtained through the rubber surface and the prepreg paving layer is connected, and the problem of poor connection strength of the thermal protection layer and the metal cabin body caused by variable cross section, non-rotation and the metal cabin body is solved by utilizing the characteristic that the rubber surface is similar to a prepreg material;
furthermore, the prepreg of step S1 is formed by combining quartz fiber cloth evenly coated with phenolic resin and phenolic prepreg, the quartz fiber cloth has the characteristics of high temperature resistance and good chemical stability, the phenolic prepreg is phenolic resin prepreg of carbon fiber, the phenolic resin coated on the quartz fiber cloth can be better combined with the phenolic prepreg, and simultaneously has the characteristics of high temperature resistance and good structural strength, thereby meeting the requirements of high temperature resistance and structural strength of the thermal protection layer, overcoming the problem of insufficient structural strength caused by the independent utilization of the quartz fiber cloth as the thermal protection layer in the prior art, in the process of coating phenolic resin, the quartz fiber cloth needs to be spread, the phenolic resin is evenly coated on the quartz fiber cloth, 144g of phenolic resin is coated per square meter, the flatness of the quartz fiber cloth needs to be maintained all the time in the coating process, and no wrinkle distortion occurs, after air drying, the phenolic prepreg is subjected to co-curing.
Further, when the prepreg of step S1 is subjected to 3-in-1, each prepreg layer is misaligned by 2 mm.
The rubber in the step 2 is RTV-2 rubber, and further comprises a structural adhesive layer connected with the attachment structure, an RTV-2 rubber layer bonded with the structural adhesive layer, and a structural adhesive layer coated between the surface of the RTV-2 rubber layer and the thermal protection layer, wherein the two structural adhesive layers are the same in component and are both epoxy adhesive cured at normal temperature.
Further, the included angle between the prepreg and the metal cabin body in the laying in the step S4 is between 17.5 ° and 18.5 °.
In conclusion, the invention has the following beneficial effects:
the invention designs a thermal protection structure for a variable cross-section non-revolving body, which is characterized in that the thermal protection structure cannot form a complete revolving structure due to the special structure of the variable cross-section non-revolving body, and the thermal protection structure and the variable cross-section non-revolving body are connected in a one-surface connection mode, so that the phenomenon of peeling between the thermal protection structure and the variable cross-section non-revolving body can occur in practical use, and the connection reliability between the thermal protection structure and the variable cross-section non-revolving body cannot be guaranteed.

Claims (10)

1. Variable cross section non-rotating body heat protection structure, it includes the metal cabin body of a variable cross section and non-gyration, its characterized in that: an adhesive structure is processed on the surface of the metal cabin body, a rubber surface is coated and molded on the adhesive structure, and a thermal protection layer is laid and cured on the rubber surface.
2. The variable cross-section non-rotating body thermal protection structure of claim 1, wherein: the attachment structure is a rough surface obtained by performing rough treatment on the surface of the metal cabin.
3. The variable cross-section non-rotating body thermal protection structure of claim 1, wherein: the attachment structure is a plurality of through holes arranged on the surface of the metal cabin body, and the rubber surface enters the through holes and is connected with the rubber surface coated on the back surface of the metal cabin body into a whole.
4. The variable cross-section non-rotating body thermal protection structure according to claim 1, wherein: the attachment structure is a blind hole formed in the surface of the metal cabin body, and the size of the bottom of the blind hole is larger than that of the opening.
5. The variable cross-section non-rotating body thermal protection structure of claim 1, wherein: the rubber surface is a multilayer composite rubber surface and comprises a structural adhesive layer connected with the attachment structure, an RTV-2 rubber layer bonded with the structural adhesive layer and a structural adhesive layer coated between the surface of the RTV-2 rubber layer and the thermal protection layer.
6. The variable cross-section non-rotating body thermal protection forming process is characterized in that: the forming method comprises a variable-section non-rotating metal cabin body, and comprises the following steps:
s1: randomly cutting the prepreg according to the corresponding height according to the thermal protection anatomical structure, and performing 3-in-1 on the cut prepreg;
s2: treating the surface of the metal cabin body to obtain an attachment structure on the surface of the metal cabin body;
s3: coating a layer of rubber on the surface of the metal cabin body to form a rubber surface;
s4: laying up the prepreg obtained in the step S1, laying up the prepreg in an overlapping winding mode, and paving the starting layer and the finishing layer in a mode of gradually changing material widths;
s5: and curing by adopting an autoclave molding process, and processing according to the shape requirement.
7. The variable cross-section non-rotating body thermal protection forming process according to claim 6, wherein: the prepreg of the step S1 is formed by combining quartz fiber cloth evenly coated with phenolic resin and phenolic prepreg.
8. The variable cross-section non-rotating body thermal protection forming process according to claim 6, wherein: when the prepregs in the step S1 are combined for 3 in 1, each layer of the prepregs is staggered by 2 mm.
9. The variable cross-section non-rotating body thermal protection forming process according to claim 6, wherein: the rubber surface in the step 2 is a multilayer composite rubber surface, and comprises a structural adhesive layer connected with the attachment structure, an RTV-2 rubber layer bonded with the structural adhesive layer, and a structural adhesive layer coated between the surface of the RTV-2 rubber layer and the thermal protection layer.
10. The variable cross-section non-rotating body thermal protection forming process according to claim 6, wherein: and when the prepregs are laid in the step S4, an included angle between the prepregs and the metal cabin is 17.5-18.5 degrees.
CN202111181957.7A 2021-10-11 2021-10-11 Variable cross-section non-rotating body thermal protection structure and forming process Withdrawn CN113927925A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202111181957.7A CN113927925A (en) 2021-10-11 2021-10-11 Variable cross-section non-rotating body thermal protection structure and forming process

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202111181957.7A CN113927925A (en) 2021-10-11 2021-10-11 Variable cross-section non-rotating body thermal protection structure and forming process

Publications (1)

Publication Number Publication Date
CN113927925A true CN113927925A (en) 2022-01-14

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN202111181957.7A Withdrawn CN113927925A (en) 2021-10-11 2021-10-11 Variable cross-section non-rotating body thermal protection structure and forming process

Country Status (1)

Country Link
CN (1) CN113927925A (en)

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