CN111674541B - Flexible composite skin, manufacturing method thereof and tool structure - Google Patents
Flexible composite skin, manufacturing method thereof and tool structure Download PDFInfo
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- CN111674541B CN111674541B CN202010448897.XA CN202010448897A CN111674541B CN 111674541 B CN111674541 B CN 111674541B CN 202010448897 A CN202010448897 A CN 202010448897A CN 111674541 B CN111674541 B CN 111674541B
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- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
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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
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
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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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
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- 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
Abstract
The invention provides a flexible composite skin, a manufacturing method thereof and a tool structure, and belongs to the technical field of aviation. The problem of current flexible skin stability and bearing capacity poor is solved. The composite skin comprises a flexible rubber base body, an embedded supporting structure and a fiber reinforcement body, wherein the embedded supporting structure and the fiber reinforcement body are shaped in the flexible rubber base body in parallel, the embedded supporting structure and the fiber reinforcement body are arranged in an overlapped mode in a mutually perpendicular mode, and uniform independent grid units are formed inside the flexible rubber base body. The manufacturing tool structure comprises a metal base plate, a fiber bundle die plate, a supporting rod die plate, a pressing cover plate and a slider die, wherein the metal base plate is fixedly connected with a pair of fiber bundle die plates, the supporting rod die plate is fixedly installed on the upper surface of the metal base plate, the supporting rod die plate is connected with the pair of fiber bundle die plates to form a rectangular track, and the slider die slides along the rectangular track. The variable sweep wing quadrilateral shearing module unit is mainly used for the variable sweep wing quadrilateral shearing module unit.
Description
Technical Field
The invention belongs to the technical field of aviation, and particularly relates to a flexible composite skin, a manufacturing method thereof and a tool structure.
Background
The conventional fixed-wing aircraft is generally designed aiming at the condition that the aerodynamic efficiency is optimal in a single flight state, and the optimal aerodynamic efficiency cannot be achieved in each state of a flight envelope. Typical flight tasks generally consist of several different operation links, and the aircraft often needs to complete various combined tasks, and the conventional fixed-wing aircraft has difficulty in meeting the requirements of the aircraft on the multitask execution capability. The aerodynamic flight envelope of the variant aircraft can be expanded by changing the aerodynamic shape and the structural shape, the application range and the flight efficiency of the aircraft are remarkably improved, and the multi-task execution capacity of the aircraft is realized. The variant aircraft technology is an important development direction of the aircraft in the future as the leading technology in the field of modern aerospace.
The flexible skin is taken as an important component of a variant aircraft, and the following conditions are required: 1. it is desirable to have a low in-plane stiffness to achieve large deformations with minimal driving force. 2. High out-of-plane stiffness is required to withstand aerodynamic loads. 3. It is necessary to have strong structural stability to reduce buckling wrinkles generated during deformation. 4. Excellent airtightness and smoothness are required to improve aerodynamic performance in flight. The existing flexible skin can only meet the above 1-2 point conditions, and the comprehensive performance of the existing flexible skin is greatly limited. In addition, the existing flexible skin structure needs to resist the deformation buckling phenomenon through a certain degree of pretension, which increases the deformation driving force and the installation difficulty to a certain degree.
Disclosure of Invention
The invention provides a flexible composite skin, a manufacturing method thereof and a tool structure, aiming at solving the problems in the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme: the utility model provides a flexible composite skin, it includes flexible rubber base member, embedded bearing structure and fibre reinforcement are stereotyped in the flexible rubber base member in parallel, mutually perpendicular overlap is arranged between embedded bearing structure and the fibre reinforcement, forms even independent grid unit in flexible rubber base member inside.
Furthermore, the flexible rubber matrix comprises a matrix solution and a curing agent, and the matrix solution and the curing agent are mixed and solidified to form the flexible rubber matrix.
Furthermore, the embedded support structure comprises a plurality of support rods, and the support rods are arranged in parallel at equal intervals.
Furthermore, the support rod is made of alloy materials.
Furthermore, the fiber reinforcement bodies are arranged in parallel with each other and have equal distances between adjacent fiber bundles.
Furthermore, the flexible composite skin penetrates through the reserved hole of the framework to the position below the adjacent hole through the U-shaped needle, and then the heat-resistant wire is recovered through the crochet hook, so that single-side bottom-crossing sewing and fixing are realized.
The utility model provides a manufacturing frock structure of flexible composite skin, it includes metal baseplate, fibre bundle mould board, support stick mould board, gland plate and slider mould, fixedly connected with a pair of fibre bundle mould board on the metal baseplate, support stick mould board fixed mounting is at the upper surface of metal baseplate, support stick mould board links to each other with a pair of fibre bundle mould board and forms the rectangle track, the slider mould slides along the rectangle track, be equipped with the broach structure that has equidistant range on the fibre bundle mould board, all have the logical groove of equidistant range on support stick mould board and the slider mould, the gland plate is located the area that surrounds of fibre bundle mould board, support stick mould board and slider mould.
Furthermore, a groove is formed in the metal bottom plate, and the pair of fiber bundle mold plates are fixed in the groove.
A method of manufacturing a flexible composite skin, comprising the steps of:
the method comprises the following steps: uniformly mixing 107 rubber silicon matrix solution and a curing agent according to the mass ratio of 100;
step two: placing the silicon rubber solution in a vacuum machine, and discharging redundant bubbles in the solution;
step three: coating a layer of release agent on the surface of a metal base plate of a manufacturing tool;
step four: taking out the silicon rubber solution, pouring the silicon rubber solution onto the surface of a horizontally placed metal bottom plate, uniformly coating the surface by using a brush, and putting the metal bottom plate into a thermostat to solidify the silicon rubber solution to form a flexible rubber matrix;
step five: placing a first group of support rods on the surface of the flexible rubber matrix in parallel at fixed intervals through the through groove structure of the support rod mould plate;
step six: enabling the fiber bundles to penetrate through the comb tooth structures of the fiber bundle mould plate and continuously lay the fiber bundles on the surfaces of the support rods and the flexible rubber matrix in a rotary winding manner, so that the adjacent fiber bundles are equal in distance and parallel to each other;
step seven: enabling a second group of support rods to pass through the through groove structure of the support rod mould plate, enabling the second group of support rods and the first group of support rods to be arranged in parallel in a staggered mode to form an embedded support structure, repeating the step six, ensuring that the fiber bundles and the support rods are arranged in an up-and-down overlapped mode to form a fiber reinforcement body, and enabling the embedded support structure and the fiber reinforcement body to form a multi-unit grid in the flexible rubber matrix;
step eight: coating a layer of release agent on the surface of the gland plate;
step nine: pouring a layer of silicone rubber solution on the material formed in the step seven, covering a gland plate on the surface of the material to ensure the surface to be flat, and putting the manufacturing tool into a thermostat;
step ten: and after the silicon rubber solution is solidified, cutting the silicon rubber solution by using a die cutting machine to form the composite skin.
Furthermore, in the fourth step, the temperature in the constant temperature box is 70 ℃.
Compared with the prior art, the invention has the beneficial effects that: the invention solves the problem that the existing flexible skin has poor stability and bearing performance.
The interior of the flexible composite skin structure is uniformly divided into independent checkerboard grid units, so that the deformation practical area and the unit width-thickness ratio are reduced, the structural stability is improved, and wrinkles are not easy to generate. The embedded support structure and the fiber reinforcement are arranged in an overlapping manner to enhance the interaction between the embedded support structure and the fiber reinforcement, thereby enhancing the bearing performance.
A frock structure accessible fibre bundle mould broach unit structure and support stick mould lead to groove restriction fibre bundle winding interval and support stick interval of arranging for making flexible composite skin, through slider mould adjustment skin overall dimension, has strengthened designability and the regulation nature of flexible composite skin preparation. The tool is simple in structure, simple and convenient to install, free of repeated disassembly and assembly, high in reliability and capable of reducing the process manufacturing difficulty.
The flexible composite skin disclosed by the invention is suitable for plane and twisted surface structures, simple and reliable in fixing mode of alternately sewing the temperature-resistant wires, capable of realizing modularized disassembly and assembly and attractive in appearance.
Drawings
FIG. 1 is a schematic structural view of a flexible composite skin according to the present invention;
FIG. 2 is a schematic structural view of a tooling for manufacturing a flexible composite skin according to the present invention;
FIG. 3 is a schematic diagram of the construction of a fiber bundle die plate and a support rod die plate according to the present invention;
FIG. 4 is a schematic view of a method of manufacturing a flexible composite skin in accordance with the present invention;
FIG. 5 is a schematic view of a flexible composite skin stitching method according to the present invention;
FIG. 6 is a schematic view of the skin shear module assembly of the present invention.
The method comprises the following steps of 1-a flexible rubber substrate, 2-an embedded supporting structure, 3-a fiber reinforcement, 4-a metal bottom plate, 5-a fiber bundle mold plate, 6-a supporting rod mold plate, 7-a pressing cover plate, 8-a sliding block mold, 9-a crochet hook and 10-a U-shaped needle.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely explained below with reference to the drawings in the embodiments of the present invention.
Referring to fig. 1-6 to illustrate the embodiment, the flexible composite skin comprises a flexible rubber matrix 1, an embedded support structure 2 and fiber reinforcements 3, wherein the embedded support structure 2 and the fiber reinforcements 3 are shaped in the flexible rubber matrix 1 in parallel, the embedded support structure 2 and the fiber reinforcements 3 are arranged in an overlapped mode in a mutually perpendicular mode, and uniform independent grid units are formed inside the flexible rubber matrix 1. The total deformation area in the skin structure can be reduced, the width-thickness ratio of the unit is reduced, the stability of the skin structure can be improved, and wrinkles are not easy to generate during shearing deformation.
The flexible rubber substrate 1 of the embodiment comprises a substrate solution and a curing agent, and the substrate solution and the curing agent are mixed and solidified to form the flexible rubber substrate 1. The embedded support structure 2 comprises a plurality of support rods which are arranged in parallel at equal intervals, and the support rods are made of alloy materials, preferably 304 alloy. The fibre reinforcement 3 is arranged parallel to each other with equal spacing between adjacent fibre bundles. The flexible composite skin penetrates through the framework preformed hole to the lower part of the adjacent hole through the U-shaped needle 10, and then the heat-resistant wire is recovered through the crochet hook 9, so that single-side bottom-crossing sewing and fixing are realized. The external convex area is favorably reduced, the influence on the aerodynamic performance is avoided, the skin can be assembled and disassembled in a modularized manner, the attractive appearance is ensured, and the wire diameter of the preferable temperature-resistant wire is 0.25mm. The flexible composite skin can be applied to a sweep-back wing quadrilateral shearing module unit. The variable-sweep wing shear deformation principle is met, and the requirements on the change of the aspect ratio and the sweep angle can be met simultaneously.
The embodiment is described with reference to fig. 2 to 4, and the tooling structure for manufacturing the flexible composite skin comprises a metal base plate 4, fiber bundle mold plates 5, a support rod mold plate 6, a pressure cover plate 7 and a slider mold 8, wherein the metal base plate 4 is fixedly connected with the pair of fiber bundle mold plates 5, the support rod mold plate 6 is fixedly installed on the upper surface of the metal base plate 4, the support rod mold plate 6 is connected with the pair of fiber bundle mold plates 5 to form a rectangular track, the slider mold 8 slides along the rectangular track, the fiber bundle mold plate 5 is provided with comb tooth structures arranged at equal intervals, the support rod mold plate 6 and the slider mold 8 are respectively provided with through grooves arranged at equal intervals, the pressure cover plate 7 is located in a surrounding area of the fiber bundle mold plates 5, the support rod mold plate 6 and the slider mold 8, the metal base plate 4 is provided with a groove, and the pair of fiber bundle mold plates 5 is fixed in the groove.
The slider mould 8 can slide freely in the rectangular track to control the size of the skin, and the fiber bundles are wound in a rotating manner in the comb tooth unit structure of the fiber bundle mould plate 5 in the X direction with a certain pretightening force, so that the fiber bundles are ensured to be equal in distance and parallel to each other, and the stability of the composite flexible skin is enhanced; the supporting rods are placed in the through grooves of the supporting rod die 6 and the sliding block die 8 in the Y direction to ensure that adjacent intervals are equal and parallel to each other, and the external rigidity of the surface is effectively improved; and the flatness of the surface of the skin is ensured through the attachment of the gland plate 7 in the Z direction, and the fiber bundle and the support rod are cured in the flexible matrix in the skin tool to form the flexible composite skin. The skin manufacturing standardization can be realized, and the manufacturing complexity is greatly reduced.
The fiber bundle mould plates 5 are provided with comb tooth unit structures which are distributed at equal intervals, and the fiber bundles can be arranged in a parallel and staggered zigzag winding mode according to the performance requirements of skins so as to change the laying intervals and the laying angles. The support rod mould plate 6 is provided with through grooves at equal intervals, and the support rods can be arranged in parallel according to certain groove intervals according to the performance requirements of the skin, so that the out-of-plane bearing capacity of the skin is improved to a certain extent. The skin parameters can be adjusted according to actual performance requirements, and the designability of actual application is enhanced.
Referring to fig. 4 and 6, the embodiment is described, and a manufacturing method of a flexible composite skin comprises the following steps:
the method comprises the following steps: uniformly mixing 107 rubber silicon matrix solution and a curing agent according to the mass ratio of 100;
step two: placing the silicon rubber solution in a vacuum machine, and discharging redundant bubbles in the solution;
step three: coating a layer of release agent on the surface of a metal base plate 4 of a manufacturing tool;
step four: taking out the silicon rubber solution, pouring the silicon rubber solution into the surface of a horizontally placed metal bottom plate 4, uniformly coating the surface by using a brush, and putting the metal bottom plate into a thermostat to solidify the silicon rubber solution to form a flexible rubber matrix 1;
step five: a first group of support rods are parallelly placed on the surface of the flexible rubber matrix 1 at fixed intervals through the through groove structure of the support rod mould plate 6;
step six: enabling the fiber bundles to penetrate through the comb tooth structures of the fiber bundle mold plate 5 and continuously paved on the surfaces of the support rods and the flexible rubber matrix 1 in a rotary winding mode, so that the adjacent fiber bundles are equal in distance and parallel to each other;
step seven: enabling a second group of support rods to pass through the through groove structure of the support rod die plate 6, enabling the second group of support rods and the first group of support rods to be arranged in parallel in a staggered mode to form the embedded support structure 2, repeating the step six, ensuring that the fiber bundles and the support rods are arranged in an up-and-down overlapped mode to form the fiber reinforcement 3, and enabling the embedded support structure 2 and the fiber reinforcement 3 to form a multi-unit grid in the flexible rubber matrix 1;
step eight: coating a layer of release agent on the surface of the gland plate 7;
step nine: pouring a layer of silicone rubber solution on the material formed in the step seven, covering a gland plate 7 on the surface of the material to ensure the surface to be smooth, and putting the manufacturing tool into a thermostat;
step ten: and after the silicon rubber solution is solidified, cutting the silicon rubber solution by using a die cutting machine to form the composite skin.
In the first step of this embodiment, the viscosity of the silicone rubber solution can be improved by adding silicone oil, the base solution and the curing agent are poured into the beaker respectively, the beaker is placed in the mass scale to ensure that the mass ratio of the base solution to the curing agent is 100, and then the beaker solutions are mixed together and sufficiently stirred for a certain time to ensure that the liquids are uniformly mixed with each other. In the fourth step, the temperature in the constant temperature box is 70 ℃, and the solidification time is accelerated.
The flexible composite skin, the manufacturing method thereof and the tooling structure provided by the invention are described in detail, specific examples are applied in the text to explain the principle and the implementation mode of the invention, and the description of the examples is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (9)
1. The utility model provides a manufacturing frock structure of flexible composite skin which characterized in that: the flexible composite skin comprises a flexible rubber base body (1), an embedded supporting structure (2) and fiber reinforcement bodies (3), wherein the embedded supporting structure (2) and the fiber reinforcement bodies (3) are shaped in the flexible rubber base body (1) in parallel, the embedded supporting structure (2) and the fiber reinforcement bodies (3) are arranged in an overlapped mode in a mutually perpendicular mode, an even independent grid unit is formed inside the flexible rubber base body (1), the manufacturing tool structure comprises a metal bottom plate (4), a fiber bundle mold plate (5), a supporting rod mold plate (6), a press cover plate (7) and a slider mold (8), the metal bottom plate (4) is fixedly connected with a pair of fiber bundle mold plates (5), the supporting rod mold plate (6) is fixedly installed on the upper surface of the metal bottom plate (4), the supporting rod mold plate (6) is connected with the pair of fiber bundle mold plates (5) to form a rectangular track, the slider mold (8) slides along the rectangular track, comb tooth structures which are arranged at equal intervals are arranged on the fiber bundle mold plate (5), the supporting rod mold plate (6) and the slider mold plate (8) and the press cover plate (7) and the fiber bundle mold plate (8) are arranged in an equal interval area.
2. The tooling structure for manufacturing the flexible composite skin according to claim 1, wherein: the metal bottom plate (4) is provided with a groove, and the pair of fiber bundle mold plates (5) are fixed in the groove.
3. The tooling structure for manufacturing the flexible composite skin according to claim 1, characterized in that: the flexible rubber substrate (1) comprises a substrate solution and a curing agent, and the substrate solution and the curing agent are mixed and solidified to form the flexible rubber substrate (1).
4. The tooling structure for manufacturing the flexible composite skin according to claim 1, wherein: the embedded supporting structure (2) comprises a plurality of supporting rods which are arranged in parallel at equal intervals.
5. The tooling structure for manufacturing the flexible composite skin according to claim 4, wherein: the support rod is made of alloy materials.
6. The tooling structure for manufacturing the flexible composite skin according to claim 1, wherein: the adjacent fiber lines of the fiber reinforcement body (3) have equal space and are arranged in parallel.
7. The tooling structure for manufacturing the flexible composite skin according to claim 1, wherein: the flexible composite skin penetrates through the framework preformed hole to the lower part of the adjacent hole through the U-shaped needle (10), and then the heat-resistant wire is recovered through the crochet hook (9), so that single-side bottom-crossing sewing and fixing are realized.
8. A method of manufacturing the flexible composite skin of claim 1, wherein: the manufacturing method comprises the following steps:
the method comprises the following steps: uniformly mixing 107 rubber silicon matrix solution and a curing agent according to the mass ratio of 100;
step two: placing the silicon rubber solution in a vacuum machine, and discharging redundant bubbles in the solution;
step three: coating a layer of release agent on the surface of a metal bottom plate (4) of a manufacturing tool;
step four: taking out the silicon rubber solution, pouring the silicon rubber solution into the surface of a horizontally placed metal bottom plate (4), uniformly coating the surface by using a hairbrush, and putting the metal bottom plate into a thermostat to solidify the silicon rubber solution to form a flexible rubber matrix (1);
step five: a first group of support rods are parallelly placed on the surface of the flexible rubber matrix (1) at fixed intervals through a through groove structure of a support rod mould plate (6);
step six: fiber wires penetrate through the comb tooth structure of the fiber bundle mold plate (5) and are continuously laid on the surfaces of the support rod and the flexible rubber matrix (1) in a rotary winding mode, so that the adjacent fiber wires are equal in space and parallel to each other;
step seven: enabling a second group of support rods to pass through the through groove structure of the support rod die plate (6), enabling the second group of support rods and the first group of support rods to be arranged in a staggered and parallel mode to form an embedded support structure (2), repeating the sixth step, ensuring that the fiber wires and the support rods are arranged in an up-and-down overlapped mode to form a fiber reinforcement (3), and enabling the embedded support structure (2) and the fiber reinforcement (3) to form a multi-unit grid inside the flexible rubber matrix (1);
step eight: coating a layer of release agent on the surface of the gland plate (7);
step nine: pouring a layer of silicon rubber solution on the material formed in the step seven, covering a gland plate (7) on the surface of the material to ensure that the surface is smooth, and putting the manufacturing tool into a thermostat;
step ten: and after the silicon rubber solution is solidified, cutting the silicon rubber solution by using a die cutting machine to form the composite skin.
9. The method of manufacturing a flexible composite skin according to claim 8, wherein: and in the fourth step, the temperature in the constant temperature box is 70 ℃.
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