CN109955502A - The preparation method of recoverable airship solar heat protection and carrying integrated side wall construction - Google Patents
The preparation method of recoverable airship solar heat protection and carrying integrated side wall construction Download PDFInfo
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- CN109955502A CN109955502A CN201910271778.9A CN201910271778A CN109955502A CN 109955502 A CN109955502 A CN 109955502A CN 201910271778 A CN201910271778 A CN 201910271778A CN 109955502 A CN109955502 A CN 109955502A
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- 238000010276 construction Methods 0.000 title abstract 2
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- 238000005498 polishing Methods 0.000 claims abstract description 9
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- 238000004519 manufacturing process Methods 0.000 claims description 10
- 239000011159 matrix material Substances 0.000 claims description 10
- 229920001568 phenolic resin Polymers 0.000 claims description 10
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- 238000003801 milling Methods 0.000 claims description 8
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- 238000002679 ablation Methods 0.000 claims description 3
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- YKTSYUJCYHOUJP-UHFFFAOYSA-N [O--].[Al+3].[Al+3].[O-][Si]([O-])([O-])[O-] Chemical compound [O--].[Al+3].[Al+3].[O-][Si]([O-])([O-])[O-] YKTSYUJCYHOUJP-UHFFFAOYSA-N 0.000 description 1
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Classifications
-
- 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
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
-
- 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
- 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
- B29L2031/3097—Cosmonautical vehicles; Rockets
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
- Building Environments (AREA)
Abstract
The invention discloses the preparation methods of a kind of recoverable airship solar heat protection and carrying integrated side wall construction, and this method comprises the following steps: step 1: preparing the core material, inner panel and outer panels of sandwich；Step 2: the heat shield of side wall is prepared, and is punched in heat shield；Step 3: being glued the inner surface of outer panels and heat shield and solidify, and open up built-in fitting hole on outer panel, adds screw hole in the inside machine of outer panel and heat shield；Step 4: the core material of sandwich and outer panels are glued, and built-in fitting is embedded in core material by the built-in fitting hole of outer panels；Step 5: opening up built-in fitting hole on inner panel, and inner panel is glued and is solidified with core material another side；Step 6: rear embedded part is installed in rear buried via hole, gasket is installed to corresponding position, is glued with inner panel and solidifies by the buried via hole after inner panel processing；Step 7: outer surface brush coating, solidification and polishing to the heat shield of side wall.The present invention realizes carrying and anti-heat function.
Description
Technical Field
The invention belongs to the technical field of a thermal protection system of a returnable airship with a second cosmic speed, and particularly relates to a preparation method of a heatproof and bearing integrated side wall structure of the returnable airship.
Background
The returning spacecraft enters the flying process again at the second space flying speed, most of kinetic energy is converted into the heat energy of air, the heat energy forms an extremely high pneumatic heating environment on the surface of the spacecraft in the forms of boundary layer convection and shock wave radiation, and a reliable and scouring-resistant thermal protection system is required on the outer surface of the spacecraft to protect the life safety of astronauts and equipment inside the spacecraft. The heat-proof material on the surface has higher requirements on structural stability and integrity, and meanwhile, the heat-proof layer is connected with the internal structure and has higher bearing capacity, so the returning airship has higher requirements on light weight, heat protection performance and bearing capacity of a heat protection system. Foreign space shuttles are mostly formed by splicing a large number of low-density heat insulation tiles, and the splicing mode has the problems of poor structural stability, poor safety, complex assembly, long development period and the like. The domestic returnable capsule of the Shenzhou airship adopts a structural form that the heat-proof layer is directly glued on the metal inner shell. In order to solve the defects caused by splicing and molding the heat insulation tiles of foreign space shuttles and the defect that the heat-proof material of the return capsule of the domestic spaceflight does not have the bearing function, the development of a process method for molding the side wall in the integrated heat-proof structure with low density and integral molding of the heat-proof material is urgently needed.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the preparation method of the heat-proof and bearing integrated side wall structure of the returnable airship is provided, the defects caused by splicing and molding of the heat-insulating tiles of foreign spacecrafts and the defect that the heat-proof material of the returnable airship cabin in China does not have the bearing function are overcome, and the bearing and heat-proof functions are realized.
The purpose of the invention is realized by the following technical scheme: a method for preparing a heat protection and load bearing integrated side wall structure of a return airship comprises the following steps: the method comprises the following steps: preparing a core material, an inner panel and an outer panel in a bearing structure of the side wall; step two: preparing a heat-proof layer on the side wall, and punching the heat-proof layer; step three: brushing glue, curing and polishing the inner surface of the heat-proof layer, then gluing and curing the outer panel and the inner surface of the heat-proof layer, forming embedded part holes on the outer panel, and machining screw holes on the outer panel and the inner surface of the heat-proof layer; step four: one surface of the core material is glued with the outer panel, and the embedded part is embedded into the core material through the embedded part hole of the outer panel and is solidified; step five: bonding and curing the other surface of the core material and the inner panel, and forming embedded part holes in the inner panel according to the embedded positions of the embedded parts in the core material; step six: processing a rear buried hole in the inner panel, installing a rear buried piece in the rear buried hole, installing a gasket at the top of the rear buried piece, and bonding and curing the gasket and the inner panel; step seven: and brushing glue, curing and polishing the outer surface of the heat-proof layer of the side wall.
In the preparation method of the heat-proof and load-bearing integrated side wall structure of the return airship, the first step specifically comprises the following steps: selecting a reinforcement and a base body of the inner panel, a reinforcement and a base body of the outer panel and a core material of the sandwich structure; arranging the reinforcement and the matrix of the inner panel by a solution method or a hot melting method to prepare a unidirectional prepreg, manually laying the unidirectional prepreg or automatically laying wires or automatically laying strips to prepare an inner panel preformed blank, and curing and molding the inner panel preformed blank in a vacuum bag-autoclave mode to obtain an inner panel with a side wall; arranging the reinforcement and the matrix of the outer panel by a solution method or a hot melting method to prepare a unidirectional prepreg, manually laying the unidirectional prepreg or automatically laying wires or automatically laying strips to prepare an outer panel preformed blank, and curing and molding the outer panel preformed blank in a vacuum bag-autoclave mode to obtain the inner panel with the side wall.
In the preparation method of the heat-proof and load-bearing integrated side wall structure of the return airship, in the second step, the heat-proof layer is made of a light ablation heat-proof material with the density of 0.2-0.9 g/cm3(ii) a The machining method of the inner surface and the outer surface of the heat-proof layer is numerical control milling, and the clamping mode is special supporting tool or combined clamp clamping.
In the preparation method of the heat-proof and load-bearing integrated side wall structure of the return airship, in the third step, high-temperature-resistant phenolic resin is brushed on the inner surface of the heat-proof layer, and the brushing amount of glue is 100-500 g/square meter; then coating high-temperature-resistant silicon rubber on the outer layer of the high-temperature-resistant phenolic resin, wherein the thickness of a rubber layer is 0.05-2 mm; and (3) attaching the outer panel to the high-temperature-resistant silicon rubber layer, and vacuumizing, pressurizing and curing through a vacuum bag-oven.
In the fourth step, the outer surface of the embedded part is wrapped with the foam rubber and embedded with the core material to be assembled in place, and the vacuum bag-autoclave is used for vacuumizing, pressurizing and curing; wherein, one side of the core material and the outer panel are glued by using an adhesive J47C adhesive film or J310B adhesive film.
In the fifth step, the adhesive for gluing the other surface of the core material and the inner panel is a J47C adhesive film or a J310B adhesive film, and the adhesive is vacuumized, pressurized and cured by a vacuum bag-autoclave.
In the sixth step of the preparation method of the heat-proof and load-bearing integrated side wall structure of the return airship, the adhesive for gluing the rear embedded part and the inner panel is EA934NA or Redux420 adhesive or J133 adhesive; the gasket is metal or non-metallic material, glues for gluing with interior panel and is Redux420 or J133 glue.
In the seventh step, the glue brushing on the outer surface of the heat-proof layer is high-temperature-resistant phenolic resin, and the glue brushing amount is 100-500 g/square meter.
In the preparation method of the heat-proof and load-bearing integrated side wall structure of the return airship, the radius r1 of the circular truncated cone where the side wall is located is 100-2000 mm, the radius r2 of the circular truncated cone is 100-2000 mm, the taper angle α is 5-20 degrees, the height h is 100-6000 mm, and the thickness delta of the heat-proof layer is 100-6000 mmfThe thickness delta of the sandwich structure is within the range of 20-100 mmcThe thickness delta of the sandwich structure panel is within the range of 10-80 mmmWithin the range of 0.1-4 mm, the thickness delta of the sandwich structure core materialxIn the range of 2-79.6 mm.
In the preparation method of the heat-proof and bearing integrated side wall structure of the return airship, the sandwich structure is an X-cor sandwich structure, a honeycomb sandwich structure, a foam sandwich structure or a lattice structure.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention solves the defects caused by splicing and molding the heat insulation tiles of foreign space shuttles and the defect that the heat-proof material of the return capsule of the domestic spaceship does not have the bearing function, and realizes the bearing and heat-proof functions;
(2) the preparation method of the invention has good manufacturability and strong adaptability, is easy to be converted into batch production of a production line, and reduces the cost.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a schematic view of a thermal protection and load bearing integrated sidewall configuration of a return airship according to an embodiment of the invention;
FIG. 1-1 is a schematic representation of a size-incorporated thermal protection and load bearing integrated sidewall structure of a return airship according to an embodiment of the invention;
FIGS. 1-2 are schematic illustrations of the dimensions of the sandwich structure in the integrated thermal protection and load bearing sidewall structure of a return airship according to embodiments of the invention;
FIG. 2 is a flow chart of a method for making a thermal protection and load bearing integrated sidewall structure of a returnable airship according to an embodiment of the invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The re-entry airship adopts a detachable heat-proof structure, the heat-proof layer is connected with a metal structure of the re-entry cabin through a bearing structure, the lateral wall of the airship is of a heat-proof structure integrating an interlayer and a heat-proof material, the structure is shown in figure 1, and the functions of bearing and heat-proof can be realized simultaneously.
FIG. 2 is a flow chart of a method for making a thermal protection and load bearing integrated sidewall structure of a returnable airship according to an embodiment of the invention. As shown in fig. 2, the method comprises the steps of:
the first is the preparation of the inner and outer panels of the sandwich structure in the load bearing structure of the side walls.
And secondly, machining and partially perforating the inner surface and the outer surface of the heat-proof layer.
Thirdly, brushing glue, curing and polishing the inner surface of the heat-proof layer, then gluing and curing the outer panel and the inner surface of the heat-proof layer, drilling the embedded part holes of the outer panel, and machining screw holes in the outer panel and the inner surface of the heat-proof layer.
And fourthly, gluing and curing the core material and the embedded part of the sandwich structure with the outer panel.
Fifthly, gluing and curing the core material of the sandwich structure and the inner panel; and (5) drilling embedded part holes of the inner panel.
And sixthly, processing the rear buried hole of the inner panel of the sandwich structure.
And seventhly, gluing the rear embedded part and the gasket at the position of the inner connecting sleeve.
And eighthly, machining the outer surface and the outer contour of the heat-proof layer, machining the outer contour of the interlayer and the large opening hole, brushing glue on the outer surface of the heat-proof layer on the side wall, curing and polishing.
The sandwich structure is an X-cor sandwich structure, a honeycomb sandwich structure, a foam sandwich structure and a lattice structure.
The sandwich structure panel is made of fiber reinforced resin matrix composite materials. The fiber type can be carbon fiber, glass fiber, organic fiber, ceramic fiber, metal fiber, etc. The carbon fiber is T300 or higher high-strength carbon fiber or M40 or higher high-modulus carbon fiber. The glass fiber is E glass fiber, S glass fiber, basalt fiber, etc. The organic fiber is aramid fiber, ultra-high molecular weight polyethylene fiber, polyimide fiber, PBO fiber, PBI fiber, etc. Ceramic fiber, aluminum silicate fiber and modified fiber. The metal fiber is copper fiber, aluminum fiber, etc.
The resin matrix is thermoplastic resin, including polypropylene, polycarbonate, polyamide, polysulfone, etc. The thermosetting resin includes epoxy resin, cyanate resin and the like. The composite forming method of the inner panel and the outer panel comprises the steps of manually laying or automatically laying wires or automatically laying strips, and then curing and forming through a vacuum bag-autoclave. The preparation method of the unidirectional prepreg used for manual laying is a hot melting method or a solution method, and the thickness of a single layer ranges from 0.02mm to 0.5 mm.
The heat-proof material is a light ablation heat-proof material with the density of 0.2-0.9 g/cm3And (3) a range.
The machining method of the inner surface and the outer surface of the heat-proof material is numerical control milling, and the clamping mode is special supporting tool or combined clamp clamping.
The glue brushing amount of the inner surface of the heat-proof material is 100-500 g/square meter.
The adhesive for gluing the outer skin and the heat-proof layer is high-temperature-resistant silicon rubber, and the thickness of the adhesive layer is 0.05-2 mm. The curing mode is vacuum bag-oven vacuum pumping and pressurizing curing.
The sandwich structure core material is porous aluminum honeycomb, foam, C-cor and the like.
The adhesive for the adhesive bonding of the core material, the embedded part and the outer skin is J47C adhesive film or J310B adhesive film and similar products, and the foaming adhesive is J47D or J245D2 and similar products. The curing mode is vacuum bag-autoclave vacuumizing pressurization curing.
The post-buried machining and combined machining method is numerical control milling, and the clamping mode is special supporting tool or combined clamp clamping.
The adhesive for gluing the core material and the inner skin is J47C adhesive film or J310B adhesive film and similar products.
The glue for post-buried gluing is EA934NA or Redux420 glue or J133 glue.
The connecting gasket is made of metal or non-metal materials, and the adhesive is Redux420 adhesive or J133 adhesive.
The glue brushing amount of the outer surface of the heat-proof material is 100-500 g/square meter.
The preparation method is convenient for molding operation and adopts a mode of increasing the size and increasing the configuration to carry out size increasing design on a product blank in order to ensure a process area of size precision.
The side wall supporting tool is designed according to the net size of a pneumatic outer molded surface (convex surface) redesigned by a process, the overall size of the side wall supporting tool is larger than the size of a redesigned product, and the side wall supporting tool is required to be resistant to high temperature of more than 200 ℃; the air tightness of the molded surface area of the product requires that the pressure change value is less than 0.01MPa within 10 minutes of vacuum pressure maintaining.
Specifically, the method comprises the following steps:
(1) the panel reinforcement fibers and resin matrix are selected according to the targeted properties and dimensions of the sidewall.
(2) The core material of the sandwich structure is selected according to the target properties of the side walls.
(3) Arranging the reinforcement and the matrix in the step (1) by a solution method or a hot melting method to prepare a unidirectional prepreg for manual laying, or for automatic filament laying or automatic tape laying by infiltration.
(4) And (4) preparing a carbon fiber composite panel preforming blank by manually laying or automatically laying wires or automatically laying tapes by using the prepreg in the step (3).
(5) And (4) curing and forming the panel preform blank in the step (4) in a vacuum bag-autoclave mode.
(6) The inner surface and the outer surface of the heat-proof material are processed by numerical control milling, and the clamping mode is special supporting tool or combined clamp clamping.
(7) Brushing high-temperature-resistant phenolic resin on the inner surface of the heat-proof material processed in the step (6), wherein the brushing glue amount is 100-500 g/square meter.
(8) And (4) coating high-temperature-resistant silicon rubber on the inner surface of the heat-proof material in the step (7), wherein the thickness of a rubber layer ranges from 0.05 mm to 2 mm.
(9) And (4) attaching the outer skin prepared in the step (5) to the high-temperature-resistant silicon rubber layer on the inner surface of the heat-proof material in the step (8), and vacuumizing, pressurizing and curing through a vacuum bag-oven.
(10) And (4) polishing and cleaning the surface of the outer skin in the step (9), and brushing the primer and the adhesive film.
(11) Splicing the core materials into a target size, and attaching the core materials to the outer skin in the step (10).
(12) And wrapping foaming glue or similar products around the embedded part, embedding the core material into the embedded part, assembling in place, and vacuumizing, pressurizing and curing by a vacuum bag-autoclave.
(13) And (5) pasting an adhesive film on the lower surface of the inner skin prepared in the step (5) and then pasting the adhesive film on the surface of the core material prepared in the step (12).
(14) And (5) burying the hole after the numerical control milling, wherein the clamping mode is a special supporting tool or combined clamp clamping mode.
(15) And (5) gluing and connecting the back embedded parts and gaskets at the connecting points in the back embedded holes in a corresponding type and quantity in step (14) and curing.
(16) The height, the hole position and the outline of the part are processed in a numerical control combined mode, and the clamping mode is a special supporting tool or combined clamp clamping mode.
(17) And (3) brushing high-temperature-resistant phenolic resin on the outer surface of the heat-proof material in the step (16), wherein the brushing amount is 100-500 g/square meter, and thus obtaining the side wall.
The preparation is described in more detail below by means of 1 example:
the preparation method of the integrated side wall structure comprises the following steps of forming a small end face radius R169 1693mm, a large end face radius R2011mm and a honeycomb sandwich layer with the thickness of 15mm, forming a panel material of M40J/cyanate resin composite material, forming a panel with the thickness of 0.32mm and forming a honeycomb core with the specification of 0.03 multiplied by 3:
(1) high modulus carbon fiber M40J was selected as the reinforcement of the panel, and high temperature cyanate BS-4 as the resin matrix.
(2) A porous aluminum honeycomb core is selected as a core material.
(3) And (2) arranging the reinforcement body and the matrix in the step (1) through a hot melting method to prepare a unidirectional prepreg with the single-layer thickness of 0.08 mm.
(4) And (4) manually laying the prepreg in the step (3) to prepare a carbon fiber composite panel preform blank with the thickness of 0.32 mm.
(5) And (4) curing and forming the panel preform blank in the step (4) in a vacuum bag-autoclave mode.
(6) The inner surface and the outer surface of the heat-proof material are processed by numerical control milling, and the clamping mode is a special supporting tool.
(7) And (4) brushing 192 phenolic resin on the inner surface of the heat-proof material processed in the step (6), wherein the brushing glue amount is (250 +/-10) g/square meter.
(8) And (4) coating the RTV560 on the inner surface of the heat-proof material in the step (7), wherein the thickness of a glue layer is 0.15 mm.
(9) And (4) pasting the carbon fiber outer skin prepared in the step (5) on the high-temperature-resistant silicon rubber layer on the inner surface of the heat-proof material in the step (8), and vacuumizing, pressurizing and curing through a vacuum bag-oven.
(10) And (4) polishing and cleaning the surface of the outer skin in the step (9), and sticking a J310B adhesive film.
(11) And (3) taking the honeycomb core as a target size, connecting the parts by using a foaming adhesive J245D2, and attaching the parts on the outer skin in the step (10).
(12) And (3) wrapping foaming glue J245D2 around the embedded part, embedding the embedded part into the honeycomb core, assembling in place, and vacuumizing, pressurizing and curing by a vacuum bag-autoclave.
(13) And (3) pasting a layer of J310B adhesive film on the lower surface of the carbon fiber inner skin prepared in the step (5) and then pasting the adhesive film on the surface of the honeycomb core in the step (12), wherein the adhesive film surface is in contact with the honeycomb core.
(14) And (5) burying a hole after numerical control milling, wherein the clamping mode is a special supporting tool.
(15) And (5) gluing and connecting the back embedded parts and gaskets at the connecting points in the back embedded holes in a corresponding type and quantity in step (14) and curing.
(16) The height, the hole position and the outline of the part are processed by the numerical control combination, and the clamping mode is a special supporting tool.
(17) And (3) coating 192 phenolic resin on the outer surface of the heat-proof material in the step (16), wherein the glue amount is 250 +/-10 grams per square meter, and obtaining the side wall.
Fig. 1-1 is a schematic view of the size of the heat-proof and load-bearing integrated side wall structure of the return airship according to the embodiment of the invention, and fig. 1-2 is a schematic view of the size of the interlayer structure in the heat-proof and load-bearing integrated side wall structure of the return airship according to the embodiment of the invention, as shown in fig. 1-1 and fig. 1-2, compared with the prior art, the integrated side wall structure of the invention is an outer heat-proof material and an inner interlayer structure, has both heat-proof performance and load-bearing performance, and has a detachable and reusable function, and the preparation method of the invention has high product precision, size precision superior to 2mm, and can realize a wide size range, the radius r1 of the circular truncated cone where the side wall is located is 100mm to 2000mm, the radius r2 of the circular truncated cone is 100mm to 2000mm, the cone angle α is 5 ° to 20 °, the height h is 100mmfThe thickness delta of the sandwich structure is within the range of 20-100 mmcThe thickness delta of the sandwich structure panel is within the range of 10-80 mmmWithin the range of 0.1 to 4mm,sandwich structure core thickness deltaxIn the range of 2-79.6 mm.
The invention solves the defects caused by splicing and molding the heat insulation tiles of foreign space shuttles and the defect that the heat-proof material of the return capsule of the domestic spaceship does not have the bearing function, and realizes the bearing and heat-proof functions; the preparation method of the invention has good manufacturability and strong adaptability, is easy to be converted into batch production of a production line, and reduces the cost.
The above-described embodiments are merely preferred embodiments of the present invention, and general changes and substitutions by those skilled in the art within the technical scope of the present invention are included in the protection scope of the present invention.
Claims (10)
1. A preparation method of a heat-proof and load-bearing integrated side wall structure of a return airship is characterized by comprising the following steps:
the method comprises the following steps: preparing a core material, an inner panel and an outer panel in a bearing structure of the side wall;
step two: preparing a heat-proof layer on the side wall, and punching the heat-proof layer;
step three: brushing glue, curing and polishing the inner surface of the heat-proof layer, then gluing and curing the outer panel and the inner surface of the heat-proof layer, forming embedded part holes on the outer panel, and machining screw holes on the outer panel and the inner surface of the heat-proof layer;
step four: gluing the core material and the outer panel, embedding the embedded part into the core material through the embedded part hole of the outer panel, and curing;
step five: arranging embedded part holes on the inner panel, and bonding the inner panel and the other surface of the core material by glue and curing;
step six: processing a rear buried hole in the inner panel, installing a rear buried piece in the rear buried hole, installing a gasket at the top of the rear buried piece, and bonding and curing the gasket and the inner panel;
step seven: and brushing glue, curing and polishing the outer surface of the heat-proof layer of the side wall.
2. The method of making a returnable airship heat protection and load bearing integrated sidewall structure as recited in claim 1, wherein: the first step specifically comprises the following steps:
selecting a reinforcement and a base body of the inner panel, a reinforcement and a base body of the outer panel and a core material of the sandwich structure;
arranging the reinforcement and the matrix of the inner panel by a solution method or a hot melting method to prepare a unidirectional prepreg, manually laying the unidirectional prepreg or automatically laying wires or automatically laying strips to prepare an inner panel preformed blank, and curing and molding the inner panel preformed blank in a vacuum bag-autoclave mode to obtain an inner panel with a side wall;
arranging the reinforcement and the matrix of the outer panel by a solution method or a hot melting method to prepare a unidirectional prepreg, manually laying the unidirectional prepreg or automatically laying wires or automatically laying strips to prepare an outer panel preformed blank, and curing and molding the outer panel preformed blank in a vacuum bag-autoclave mode to obtain the outer panel with the side wall.
3. The method of making a returnable airship heat protection and load bearing integrated sidewall structure as recited in claim 1, wherein: in the second step, the heat-proof layer is made of a light ablation heat-proof material with the density of 0.2-0.9 g/cm3(ii) a The machining method of the inner surface and the outer surface of the heat-proof layer is numerical control milling, and the clamping mode is specialAnd clamping by using a supporting tool or a combined clamp.
4. The method of making a returnable airship heat protection and load bearing integrated sidewall structure as recited in claim 1, wherein: in the third step, brushing high-temperature-resistant phenolic resin on the inner surface of the heat-proof layer, wherein the brushing amount of glue is 100-500 g per square meter; then coating high-temperature-resistant silicon rubber on the outer layer of the high-temperature-resistant phenolic resin, wherein the thickness of a rubber layer is 0.05-2 mm; and (3) attaching the outer panel to the high-temperature-resistant silicon rubber layer, and vacuumizing, pressurizing and curing through a vacuum bag-oven.
5. The method of making a returnable airship heat protection and load bearing integrated sidewall structure as recited in claim 1, wherein: in the fourth step, the outer surface of the embedded part in the height direction is wrapped with foaming glue and embedded with a core material to be assembled in place, and the vacuum bag-autoclave is used for vacuumizing, pressurizing and curing; wherein,
the adhesive for gluing the core material and the outer panel is J47C adhesive film or J310B adhesive film.
6. The method of making a returnable airship heat protection and load bearing integrated sidewall structure as recited in claim 1, wherein: in the fifth step, the adhesive for gluing the core material and the inner panel is a J47C adhesive film or a J310B adhesive film, and the adhesive is vacuumized and pressurized and cured through a vacuum bag-autoclave.
7. The method of making a returnable airship heat protection and load bearing integrated sidewall structure as recited in claim 1, wherein: in the sixth step, the adhesive for gluing the rear embedded part and the core material is EA934NA or Redox 420 adhesive or J133 adhesive; the gasket is metal or non-metallic material, glues for gluing with interior panel and is Redux420 or J133 glue.
8. The method of making a returnable airship heat protection and load bearing integrated sidewall structure as recited in claim 1, wherein: and seventhly, brushing glue on the outer surface of the heat-proof layer, wherein the brushing glue is high-temperature-resistant phenolic resin, and the brushing glue amount is 100-500 g per square meter.
9. The method for preparing a heat-proof and load-bearing integrated side wall structure of a returnable airship as claimed in claim 1, wherein the radius r1 of the truncated cone where the side wall is located is 100mm to 2000mm, the radius r2 of the truncated cone is 100mm to 2000mm, the taper angle α is 5 ° to 20 °, the height h is 100mm to 6000mm, and the thickness δ of the heat-proof layer isfThe thickness delta of the sandwich structure is within the range of 20-100 mmcThe thickness delta of the sandwich structure panel is within the range of 10-80 mmmWithin the range of 0.1-4 mm, the thickness delta of the sandwich structure core materialxIn the range of 2-79.6 mm.
10. The method of making a returnable airship heat protection and load bearing integrated sidewall structure as recited in claim 2, wherein: the sandwich structure is an X-cor sandwich structure, a honeycomb sandwich structure, a foam sandwich structure or a lattice structure.
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