CN112829342A - Forming method of aircraft special-shaped cabin heat-proof layer and heat-proof layer - Google Patents

Forming method of aircraft special-shaped cabin heat-proof layer and heat-proof layer Download PDF

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Publication number
CN112829342A
CN112829342A CN202011637065.9A CN202011637065A CN112829342A CN 112829342 A CN112829342 A CN 112829342A CN 202011637065 A CN202011637065 A CN 202011637065A CN 112829342 A CN112829342 A CN 112829342A
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temperature
cavity
heat
layer
rtm
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CN112829342B (en
Inventor
张轩
沈亚东
郑张宜
杨戈
艾进
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Hubei Sanjiang Aerospace Group Hongyang Electromechanical Co Ltd
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Hubei Sanjiang Aerospace Group Hongyang Electromechanical Co Ltd
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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
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
    • 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
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/40—Sound or heat insulation, e.g. using insulation blankets
    • 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
    • B29L2031/3076—Aircrafts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)

Abstract

The invention relates to a forming method of a thermal protection layer of a special-shaped cabin section of an aircraft and the thermal protection layer, belongs to the technical field of composite material forming processes, and solves the technical problem that the thermal protection layer processed by the process method for manufacturing the thermal protection layer with a special-shaped structure in the prior art is poor in ablation resistance and mechanical property. The forming method comprises the steps of obtaining an RTM forming die, wherein the RTM forming die is provided with a cavity matched with a heat-proof layer; filling the high-temperature-resistant fabric into the cavity until the cavity is filled with the high-temperature-resistant fabric; packaging and vacuumizing the cavity filled with the high-temperature-resistant fabric; injecting resin into the cavity filled with the high-temperature-resistant fabric by using an RTM (resin transfer molding) glue injection machine; and curing and molding the resin injected into the cavity to obtain the heat-proof layer. By the method, the aircraft special-shaped cabin heat-proof layer with better ablation resistance and mechanical property can be obtained. The heat-shielding layer is manufactured by the forming method.

Description

Forming method of aircraft special-shaped cabin heat-proof layer and heat-proof layer
Technical Field
The invention belongs to the technical field of composite material forming processes, and particularly relates to a forming method of a thermal protection layer of an aircraft special-shaped cabin section and the thermal protection layer.
Background
Part of cabin sections in the high-speed flying aircraft are of special-shaped structures, the overall internal appearance is in oval shape and gradually transits to diamond shape, and the heat-proof layer of the aircraft has good ablation resistance, good heat-proof performance and high mechanical performance while meeting the special-shaped structures. In the prior art, the heat-proof layer of the special-shaped structure is composed of high-temperature-resistant resin and high-temperature-resistant quartz fiber gridding cloth, the high-temperature-resistant gridding cloth is soaked in the high-temperature-resistant resin to form a prepreg, and then the prepreg is wound on a forming tool to be cured and formed, so that the technical defects of poor ablation resistance and poor mechanical property exist.
Disclosure of Invention
The invention provides a forming method of a thermal protection layer of a special-shaped cabin section of an aircraft and the thermal protection layer, which are used for solving the technical problem that the thermal protection layer processed by a process method for manufacturing the thermal protection layer with a special-shaped structure in the prior art is poor in ablation resistance and mechanical property.
The invention is realized by the following technical scheme: a method for forming a heat-proof layer of a special-shaped cabin section of an aircraft comprises the following steps:
obtaining an RTM forming die, wherein the RTM forming die is provided with a cavity matched with the heat-proof layer;
filling a high-temperature-resistant fabric into the cavity until the cavity is filled with the high-temperature-resistant fabric;
packaging and vacuumizing the cavity filled with the high-temperature-resistant fabric;
injecting resin into the cavity filled with the high-temperature-resistant fabric by using an RTM (resin transfer molding) glue injection machine;
and curing and molding the resin injected into the cavity to obtain the heat-proof layer.
Further, in order to better implement the present invention, the method further includes the following steps before the resin is injected into the cavity filled with the high temperature resistant fabric by using the RTM glue injection machine;
and performing simulation process simulation on the resin injection process in the cavity filled with the high-temperature-resistant fabric by using RTM process simulation software.
Further, in order to better implement the invention, the high-temperature resistant fabric is a 2.5D knitted fabric formed by knitting fiber yarns.
Further, in order to better realize the invention, the high-temperature-resistant fabric comprises a high-density layer and a low-density layer which are overlapped and connected together, the RTM forming mold comprises a female mold and a male mold, both the female mold and the male mold are provided with molded surfaces, when the female mold and the male mold are assembled, a cavity is formed between the molded surface of the female mold and the molded surface of the male mold, when the high-temperature-resistant fabric is arranged in the cavity, the high-density layer is positioned at one side close to the molded surface of the female mold, and the low-density layer is positioned at one side close to the molded surface of the male mold.
Further, in order to better realize the invention, the thickness of the high-density layer is the thickness of the fabric
Figure BDA0002876795730000021
To
Figure BDA0002876795730000022
Further, in order to better realize the present invention, the low-density layer is obtained by drawing the high-density layer with a high-density warp, and the low-density layer is the high-density layer with a high-density warp
Figure BDA0002876795730000023
To
Figure BDA0002876795730000024
Furthermore, in order to better realize the invention, the female die is formed by splicing N sub-modules, and the N sub-modules are obtained by dividing the female die according to the appearance of the heat-proof layer.
Further, in order to better implement the present invention, the method for obtaining the cavity size of the RTM molding die includes:
obtaining the size of the heat-proof layer at the curing temperature according to the size of the heat-proof layer at the normal temperature, the linear expansion coefficient of the heat-proof layer material and the temperature difference between the curing temperature and the normal temperature;
obtaining the size of the cavity of the RTM forming die at the curing temperature according to the size of the heat-proof layer at the curing temperature;
and obtaining the size of the cavity of the RTM forming mold at normal temperature according to the size of the cavity of the RTM forming mold at the curing temperature, the thermal expansion coefficient of the manufacturing material of the RTM forming mold and the temperature difference between the curing temperature and normal temperature.
Further, in order to better implement the present invention, the size of the heat-protective layer at the curing temperature is obtained according to the size of the heat-protective layer at normal temperature, the linear expansion coefficient of the heat-protective layer material, and the temperature difference between the curing temperature and normal temperature, and specifically:
Lsolid 1＝LOften 1·Δt·(1+α1) Wherein L isSolid 1The dimension of the heat-protective layer at the curing temperature, LOften 1Δ t is the temperature difference between the curing temperature and the normal temperature, α1Is the coefficient of linear expansion of the heat protective layer material;
Lsolid 2＝LSolid 1Wherein L isSolid 2A dimension of the cavity of the RTM molding die at a curing temperature;
according to the RTM shaping mould the size of die cavity under curing temperature, the thermal expansion coefficient of RTM shaping mould manufacturing materials and the difference in temperature between curing temperature and the normal atmospheric temperature obtain the RTM shaping mould the size of die cavity at normal atmospheric temperature specifically is:
Figure BDA0002876795730000031
wherein L isOften 2Is the size of the cavity of the RTM forming die at normal temperature, alpha2The coefficient of thermal expansion of the material from which the RTM forming die is made.
Further, in order to better implement the present invention, the RTM mold is provided with a glue injection port and a glue outlet port, which are communicated with the cavity, the glue injection port is located at a lower portion of the cavity, and the glue outlet port is located at an upper portion of the cavity.
The invention also provides a heat-proof layer, which is manufactured by the forming method of the aircraft special-shaped cabin section heat-proof layer.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention provides a method for forming a thermal protection layer of a special-shaped cabin section of an aircraft, which comprises the steps of firstly obtaining an RTM forming die with a cavity matched with the thermal protection layer, then filling a high-temperature-resistant fabric into the cavity of the RTM forming die until the cavity is filled with the high-temperature-resistant fabric, then packaging and vacuumizing the cavity filled with the high-temperature-resistant fabric, then injecting resin into the cavity filled with the high-temperature-resistant fabric by using an injection molding machine, enabling the resin to penetrate into gaps of the high-temperature-resistant fabric, and finally curing and forming to obtain the thermal protection layer, wherein the method adopts a glue injection mode, and enables the resin to be immersed into the high-temperature-resistant fabric by using the RTM forming die to be integrally formed to generate the thermal protection layer, so that the internal stress of the thermal protection layer produced by the method is smaller, the areas of the formed thermal protection layer are more uniform, the thermal protection layer can be better attached to the special-shaped cabin section of the aircraft, and the produced thermal protection, thereby being capable of meeting the requirement of high-speed flight of the aircraft.
(2) The invention also provides a heat-proof layer, which is manufactured by the forming method of the aircraft special-shaped cabin heat-proof layer, so that the heat-proof layer is of a double-layer structure, and the density of the outer layer is greater than that of the inner layer, so that the heat-proof layer has better ablation resistance and mechanical property, and higher practicability.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the examples given herein without any inventive step, are within the scope of the present invention.
Example 1:
the embodiment provides a method for forming a heat-proof layer of a special-shaped cabin section of an aircraft, which is used for solving the technical problem that the heat-proof layer is poor in ablation resistance and mechanical property when the heat-proof layer is processed in a winding mode in the prior art. Specifically, in the prior art, a high-temperature-resistant mesh fabric soaked with high-temperature-resistant resin is cut to form a cloth tape, and then the cloth tape is wound on a special-shaped cabin section of an aircraft, the internal stress of a heat-proof layer produced by the processing technology is relatively large, and the perfect fit between the heat-proof layer and the special-shaped cabin section cannot be guaranteed in the winding process, so that the ablation resistance and the mechanical property of each area of the formed heat-proof layer are different, and the ablation resistance and the mechanical property of the whole heat-proof layer are poor.
The forming method of the heat protection layer of the special-shaped cabin section of the aircraft provided by the embodiment comprises the following steps:
step 1: an RTM forming mold is obtained and has a cavity matching the heat protection layer to be processed. Note that the term "RTM" in the present embodiment refers to resin transfer molding.
Step 2: and (3) filling the high-temperature-resistant fabric into the cavity until the cavity is filled with the high-temperature-resistant fingerprints. In the step, the RTM forming die comprises a female die and a male die, wherein molded surfaces are arranged on the female die and the male die, and the cavity is formed between the molded surface on the female die and the molded surface on the male die when the female die and the male die are closed. When the female die and the male die are not matched, the high-temperature-resistant fabric is pre-pressed and cut to form a sleeve-shaped structure, and the sleeve-shaped structure is sleeved on the male die so that the molded surface of the male die is covered by the high-temperature-resistant fabric. The thickness of the high-temperature-resistant fabric is the same as the width of the cavity, so that when the female die and the male die are closed, the cavity can be filled with the high-temperature-resistant fabric, and the technical problem that the high-temperature-resistant fabric is not easy to be filled into the cavity is solved.
And step 3: and packaging the cavity filled with the high-temperature-resistant fabric, and vacuumizing the cavity filled with the high-temperature-resistant fabric by using vacuum equipment, so that air in the cavity is discharged, and the heat-proof layer with low porosity is formed.
And 4, step 4: resin is injected into the cavity filled with the high-temperature-resistant fabric by using an RTM glue injection machine, and it is noted that the resin in this embodiment is a high-temperature-resistant resin.
And 5: and curing and molding the resin injected into the cavity to obtain the required heat-proof layer. In the step, the temperature in the cavity is ensured to be 160-180 ℃, namely the curing temperature of the heat-proof layer is 160-180 ℃, and optimally, the curing temperature of the heat-proof layer is set to be 170 ℃. And, at the initial stage of curing, the pressure in the cavity is guaranteed to be 0.2Mpa, at the final stage of curing, the pressure in the cavity is guaranteed to be 1Mpa, and during the curing, the pressure in the cavity is gradually increased.
The method adopts a glue injection mode, and resin is immersed into the high-temperature-resistant fabric by virtue of an RTM (resin transfer molding) forming die to form the heat-proof layer integrally, so that the internal stress of the heat-proof layer produced by the method is smaller, and all areas of the formed heat-proof layer are more uniform, so that the heat-proof layer can be better attached to the special-shaped cabin section of the aircraft, and the produced heat-proof layer has better ablation resistance and mechanical property, and further can meet the requirement of the aircraft on high-speed flight.
As a best implementation manner of this embodiment, the RTM mold in this embodiment is provided with a glue injection port and a glue outlet port that are communicated with the cavity, the glue injection port is located at a lower portion of the cavity, and the glue outlet port is located at an upper portion of the cavity, so that a process of impregnating the high temperature resistant fabric with the resin can be performed from bottom to top, which is beneficial to discharging air in the high temperature resistant fabric, improving the impregnability of the liquid resin to the high temperature resistant resin, avoiding a situation that a certain position of the high temperature resistant fabric is not impregnated with the resin, ensuring that the impregnation is more uniform, and thus enabling the formed heat protection layer to have a better effect.
As a more preferable embodiment of this embodiment, in this embodiment, before the step of injecting the resin into the cavity filled with the high temperature resistant fabric by using the RTM glue injector, the method further includes the following steps:
step 6: simulation process simulation is carried out on the resin injection process in the cavity filled with the high-temperature-resistant fabric by RTM process simulation software, so that the flowing effect and the coverage rate of the resin in the cavity filled with the high-temperature-resistant fabric can be known, the reasonability of the design of a glue flowing channel of a mold is ensured, and the phenomenon of glue shortage after the heat-proof layer is cured and formed is further ensured.
As a specific implementation manner of this embodiment, the high temperature resistant fabric in this embodiment is a 2.5D woven fabric formed by weaving fiber yarns so as to meet the requirements of pre-pressing and mold filling. A high-temperature resistant fabric as one of the embodiments is a variable-density fabric, specifically, it includes a high-density layer and a low-density layer overlapped and connected together, when the high-temperature resistant fabric is installed in the cavity, the high-density layer is located at one side close to the molded surface of the female mold, and the low-density layer is located at one side close to the molded surface of the male mold. This results in a fabric having an inner and outer layer structure in which the high density layer is located outside the low density layer, i.e., the high density layer is in direct contact with the air. More preferably, the thickness of the high-density layer is the thickness of the fabric
Figure BDA0002876795730000061
To
Figure BDA0002876795730000062
And the thickness of the low-density layer is the thickness of the fabric
Figure BDA0002876795730000063
To
Figure BDA0002876795730000064
The sum of the thicknesses of the low-density layer and the high-density layer is the thickness of the fabric. The low-density layer is obtained by drawing the high-density layer with a high-density layer, and the low-density layer is dense
Figure BDA0002876795730000065
To
Figure BDA0002876795730000066
Thus, the outer surface of the heat-proof layer has higher heat-proof, ablation-resistant and mechanical properties, while the inner layer of the heat-proof layer has better compressibility, so that the heat-proof layer has higher heat-proof, ablation-resistant and mechanical propertiesThe fireproof layer is easier to be connected with the outer wall of the aircraft special-shaped cabin section, the distribution is more uniform after extrusion, and the mold filling is easier.
As a more preferable implementation manner of this embodiment, the female die in this embodiment is formed by splicing N sub-modules, and the N sub-modules are obtained by dividing the female die according to the shape of the heat-proof layer, so that it is ensured that the RTM forming die is more convenient to assemble, and the number and range of the folds of the high-temperature resistant fabric can be dispersed as much as possible, so that the formed heat-proof layer has better performance.
As a specific implementation manner of this embodiment, in this embodiment, an important part in the RTM forming mold is the cavity, and the obtaining method of the cavity includes the following steps:
and 7: and obtaining the size of the heat-proof layer at the curing temperature according to the size of the heat-proof layer at the normal temperature, the linear expansion coefficient of the heat-proof layer material and the temperature difference between the curing temperature and the normal temperature. Specifically, this step can be embodied by the following formula: l isSolid 1＝LOften 1·Δt·(1+α1) Wherein L isSolid 1The dimension of the heat-protective layer at the curing temperature, LOften 1Δ t is the temperature difference between the curing temperature and the normal temperature, α1Is the linear expansion coefficient of the heat-proof layer material.
And 8: and obtaining the size of the cavity of the RTM forming die at the curing temperature according to the size of the heat-proof layer at the curing temperature. Since the size of the heat-proof layer is the same as the size of the cavity at the curing temperature, it can be represented by the following formula: l isSolid 2＝LSolid 1Wherein L isSolid 2The dimensions of the cavity of the RTM forming die at curing temperature.
And step 9: and obtaining the size of the cavity of the RTM forming mold at normal temperature according to the size of the cavity of the RTM forming mold at the curing temperature, the thermal expansion coefficient of a manufacturing material of the RTM forming mold and the temperature difference between the curing temperature and the normal temperature. Specifically, this step can be embodied by the following formula:
Figure BDA0002876795730000067
wherein L isOften 2Is the size of the cavity of the RTM forming die at normal temperature, alpha2The coefficient of thermal expansion of the material from which the RTM forming die is made.
It should be noted that steps 7, 8 and 9 are to obtain the size of the cavity of the RTM mold, and the RTM mold is manufactured in the same manner as the prior art, but the cavity of the RTM mold is obtained according to the above method.
Through the steps 7, 8 and 9, the cavity which is the same as that of the heat-proof layer to be processed can be accurately obtained, so that the heat-proof layer which meets the requirements in size can be formed after glue injection and curing, the problem of the overall size of the heat-proof layer caused by the difference of the linear expansion coefficients of the mold and the heat-proof layer material is solved, and net-size forming of the heat-proof layer is realized.
Example 2:
the thermal protection layer is manufactured by the forming method of the aircraft special-shaped cabin thermal protection layer, so that the thermal protection layer is of a double-layer structure, the density of the outer layer is greater than that of the inner layer, and therefore the aircraft special-shaped cabin thermal protection layer has better ablation resistance and mechanical property and higher practicability.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.

Claims (10)

1. A method for forming a heat-proof layer of a special-shaped cabin section of an aircraft is characterized by comprising the following steps:
obtaining an RTM forming die, wherein the RTM forming die is provided with a cavity matched with the heat-proof layer;
filling a high-temperature-resistant fabric into the cavity until the cavity is filled with the high-temperature-resistant fabric;
packaging and vacuumizing the cavity filled with the high-temperature-resistant fabric;
injecting resin into the cavity filled with the high-temperature-resistant fabric by using an RTM (resin transfer molding) glue injection machine;
and curing and molding the resin injected into the cavity to obtain the heat-proof layer.
2. The method for forming the thermal protection layer of the special-shaped cabin section of the aircraft as claimed in claim 1, wherein the method comprises the following steps: before the resin is injected into the cavity filled with the high-temperature-resistant fabric by using an RTM glue injection machine, the method also comprises the following steps;
and performing simulation process simulation on the resin injection process in the cavity filled with the high-temperature-resistant fabric by using RTM process simulation software.
3. The method for forming the thermal protection layer of the special-shaped cabin section of the aircraft as claimed in claim 1, wherein the method comprises the following steps: and the RTM forming die is provided with a glue injection port and a glue outlet which are communicated with the cavity, the glue injection port is positioned at the lower part of the cavity, and the glue outlet is positioned at the upper part of the cavity.
4. Method for forming a shaped section heat protection layer for an aircraft according to any one of claims 1 to 3, characterized in that: the high-temperature-resistant fabric comprises a high-density layer and a low-density layer which are connected in an overlapping mode, the RTM forming die comprises a female die and a male die, the female die and the male die are both provided with molded surfaces, the female die and the male die form a cavity between the molded surfaces of the female die and the male die when the male die is closed, the high-temperature-resistant fabric is arranged in the cavity, the high-density layer is located on one side close to the molded surface of the female die, and the low-density layer is located on one side close to the molded surface of the male die.
5. The method for forming the thermal protection layer of the special-shaped cabin section of the aircraft as claimed in claim 4, wherein the method comprises the following steps: the thickness of the high-density layer is the thickness of the fabric
Figure FDA0002876795720000011
To
Figure FDA0002876795720000012
6. The method for forming the thermal protection layer of the special-shaped cabin section of the aircraft as claimed in claim 4, wherein the method comprises the following steps: the low-density layer is obtained by drawing the high-density layer warp density, and the low-density layer warp density is the high-density layer warp density
Figure FDA0002876795720000013
To
Figure FDA0002876795720000014
7. The method for forming the thermal protection layer of the special-shaped cabin section of the aircraft as claimed in claim 4, wherein the method comprises the following steps: the female die is formed by splicing N sub-modules, and the N sub-modules are obtained by dividing the female die according to the appearance of the heat-proof layer.
8. The method for forming the thermal protection layer of the special-shaped cabin section of the aircraft as claimed in claim 4, wherein the method comprises the following steps: the method for obtaining the size of the cavity of the RTM forming mold comprises the following steps:
obtaining the size of the heat-proof layer at the curing temperature according to the size of the heat-proof layer at the normal temperature, the linear expansion coefficient of the heat-proof layer material and the temperature difference between the curing temperature and the normal temperature;
obtaining the size of the cavity of the RTM forming die at the curing temperature according to the size of the heat-proof layer at the curing temperature;
and obtaining the size of the cavity of the RTM forming mold at normal temperature according to the size of the cavity of the RTM forming mold at the curing temperature, the thermal expansion coefficient of the manufacturing material of the RTM forming mold and the temperature difference between the curing temperature and normal temperature.
9. The method for forming the thermal protection layer of the special-shaped cabin section of the aircraft as claimed in claim 8, wherein the method comprises the following steps: the size of the heat-proof layer at the curing temperature is obtained according to the size of the heat-proof layer at the normal temperature, the linear expansion coefficient of the heat-proof layer material and the temperature difference between the curing temperature and the normal temperature, and the method specifically comprises the following steps:
Lsolid 1＝LOften 1·Δt·(1+α1) Wherein L isSolid 1The dimension of the heat-protective layer at the curing temperature, LOften 1Δ t is the temperature difference between the curing temperature and the normal temperature, α1Is the coefficient of linear expansion of the heat protective layer material;
Lsolid 2＝LSolid 1Wherein L isSolid 2A dimension of the cavity of the RTM molding die at a curing temperature;
according to the RTM shaping mould the size of die cavity under curing temperature, the thermal expansion coefficient of RTM shaping mould manufacturing materials and the difference in temperature between curing temperature and the normal atmospheric temperature obtain the RTM shaping mould the size of die cavity at normal atmospheric temperature specifically is:
Figure FDA0002876795720000021
wherein L isOften 2Is the size of the cavity of the RTM forming die at normal temperature, alpha2The coefficient of thermal expansion of the material from which the RTM forming die is made.
10. A thermal protective layer, comprising: the heat protection layer is manufactured by the forming method of the aircraft special-shaped cabin section heat protection layer in any one of claims 4 to 9.
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