CN110001182B - Preparation method of heat-proof and load-bearing integrated outsole structure of return airship - Google Patents

Preparation method of heat-proof and load-bearing integrated outsole structure of return airship Download PDF

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Publication number
CN110001182B
CN110001182B CN201910272652.3A CN201910272652A CN110001182B CN 110001182 B CN110001182 B CN 110001182B CN 201910272652 A CN201910272652 A CN 201910272652A CN 110001182 B CN110001182 B CN 110001182B
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heat
skin
core material
proof layer
curing
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CN110001182A (en
Inventor
陶积柏
张明
徐鹤
宫顼
孙天峰
刘佳
韩建超
陈维强
张鹏飞
张璇
董薇
黎昱
赖小明
张玉生
郑建虎
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Beijing Satellite Manufacturing Factory Co Ltd
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Beijing Satellite Manufacturing Factory Co Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • B32B37/1018—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure using only vacuum
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • B32B37/1284—Application of adhesive
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
    • B32B37/142—Laminating of sheets, panels or inserts, e.g. stiffeners, by wrapping in at least one outer layer, or inserting into a preformed pocket
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B64G1/58—Thermal protection, e.g. heat shields
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B2038/0052—Other operations not otherwise provided for
    • B32B2038/0076—Curing, vulcanising, cross-linking

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Health & Medical Sciences (AREA)
  • Critical Care (AREA)
  • Emergency Medicine (AREA)
  • General Health & Medical Sciences (AREA)
  • Fluid Mechanics (AREA)
  • Footwear And Its Accessory, Manufacturing Method And Apparatuses (AREA)
  • Laminated Bodies (AREA)

Abstract

The invention discloses a preparation method of a heat-proof and load-bearing integrated outsole structure of a return airship, which comprises the following steps: the method comprises the following steps: preparing a core material, an inner panel and an outer panel; step two: preparing a heat-proof layer of the outsole, and punching the heat-proof layer; step three: adhering an outer panel to the inner surface of the heat-proof layer and curing, 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; 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; step six: arranging a rear buried hole on the inner panel, arranging a rear buried piece and a gasket at the position of the inner connecting sleeve in the rear buried hole, and bonding and curing the rear buried piece and the gasket with the inner panel; step seven: and (4) brushing glue, curing and polishing the outer surface of the heat-proof layer of the outsole. The invention realizes the functions of bearing and heat protection.

Description

Preparation method of heat-proof and load-bearing integrated outsole structure of return airship
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 thermal protection and bearing integrated undersole 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 spacecraft reentry module in China does not have the bearing function, the development of a large-bottom molding process method in an integrated heat-proof structure with low density, high dimensional precision 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 integrated heat-proof and bearing outsole 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 preparation method of a heat-proof and load-bearing integrated outsole structure of a return airship comprises the following steps: the method comprises the following steps: preparing a core material, an inner skin and an outer skin in the bearing structure of the integrated outsole; step two: preparing an integrated outsole heat-proof layer, 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 an outer skin and the inner surface of the heat-proof layer, forming embedded part holes in the outer skin, and machining screw holes in the outer skin and the inner surface of the heat-proof layer; step four: one surface of the core material is glued with the outer skin, and the embedded part is embedded into the core material through the embedded part hole of the outer skin and is solidified; step five: bonding and curing the other surface of the core material and the inner skin, and forming embedded part holes in the inner skin according to the embedded positions of the embedded parts in the core material; step six: processing a rear buried hole in the inner skin, installing a rear buried part in the rear buried hole, and bonding and curing the rear buried part and the inner skin; step seven: and (4) brushing glue, curing and polishing the outer surface of the heat-proof layer of the integrated outsole.
In the preparation method of the integrated heat-proof and load-bearing outsole structure of the return airship, the first step specifically comprises the following steps: selecting a reinforcement and a matrix of an inner skin, a reinforcement and a matrix of an outer skin and a core material of a sandwich structure; arranging the reinforcement and the matrix of the inner skin 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 skin pre-forming blank, and curing and forming the inner skin pre-forming blank in a vacuum bag-autoclave mode to obtain the inner skin of the integrated outsole; arranging the reinforcement and the matrix of the outer skin 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 skin pre-forming blank, and curing and forming the outer skin pre-forming blank in a vacuum bag-autoclave mode to obtain the outer skin of the integrated outsole.
In the preparation method of the heat-proof and load-bearing integrated outsole 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 outsole structure of the return airship, in the third step, the inner surface of the heat-proof layer is brushed with the high-temperature-resistant phenolic resin, and the brushing amount of the glue is 100-500 g/m2(ii) a 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; the gluing and curing of the outer skin and the inner surface of the heat-proof layer specifically comprises the following steps: the method comprises the following steps: preparing a circular flap with the diameter phi of 300-1500 at the center of the top of the outer skin; step two: preparing a plurality of fan-shaped petals on the periphery of the outer skin; step three: attaching the circular flap to the top of the inner surface of the heat-proof layer of the hood, so that the circle center of the circular flap of the outer skin is concentric with the circle center of the top of the heat-proof layer of the hood; step four: cutting 1-5 openings at two sides of the fan-shaped petal along the bus direction along the circumferential direction, wherein the length of the openings is 5-150 mm; step five: all the fan-shaped petals are spliced into a whole, a splicing seam of 0.5-3 mm is reserved when each fan-shaped petal is spliced, and the fan-shaped petals are vacuumized, pressurized and cured through a vacuum bag-oven.
In the fourth step, the outer surface of the embedded part in the height direction 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, the adhesive for gluing one side of the core material and the outer skin is a J47C adhesive film or a J310B adhesive film.
In the fifth step of the preparation method of the integrated heat-proof and load-bearing outsole structure of the return airship, the concrete steps of gluing and curing the inner skin and the core material include the following steps: the method comprises the following steps: preparing a circular flap with the diameter phi of 300-1500 at the center of the top of the inner skin; step two: preparing a plurality of fan-shaped petals on the periphery of the inner skin; step three: attaching the circular valve to the top of the core material of the hood, wherein the circle center of the circular valve of the inner skin is required to be concentric with the circle center of the top of the core material; step four: cutting 1-5 openings at two sides of the fan-shaped petal along the bus direction along the circumferential direction, wherein the length of the openings is 5-150 mm; step five: splicing all the split pieces into a whole, and reserving a splicing seam of 0.5-3 mm when each split piece is spliced; the adhesive for gluing the inner skin and the core material is a J47C adhesive film or a J310B adhesive film, and the inner skin and the core material are vacuumized, pressurized and cured through a vacuum bag-autoclave.
In the sixth step of the preparation method of the heat-proof and load-bearing integrated outsole structure of the return airship, the adhesive for gluing the rear embedded part and the inner skin is EA934NA or Redux420 adhesive or J133 adhesive.
In the seventh step of the preparation method of the heat-proof and load-bearing integrated outsole structure of the return airship, the glue brushing amount of the outer surface of the heat-proof layer is 100-500 g/m2。
In the preparation method of the heat-proof and load-bearing integrated outsole structure of the return airship, the radius r1 of the inner spherical surface of the blunt sphere of the integrated outsole is 500-3000 mm, the radius r2 of the outer spherical surface of the blunt sphere is 500-4000 mm, the total height h is within 2m, and the thickness delta of the heat-proof layer is within 2mfWithin the range of 20-100 mm, the thickness delta of the sandwich structurecWithin the range of 10-80 mm, the thickness delta of the outer skin of the sandwich structuremIn the range of 0.1-4 mm, the thickness delta of the core material of the sandwich structurexIn the range of 2-79.6 mm.
In the preparation method of the heat-proof and bearing integrated outsole 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 outsole structure of a return airship according to an embodiment of the invention;
FIG. 1-1 is a schematic view of a sandwich structure within a thermal protection and load bearing integrated outsole structure of a return airship according to an embodiment of the invention;
FIG. 2 is a flow chart of a method for manufacturing a thermal protection and load bearing integrated outsole structure of a returnable airship according to an embodiment of the invention;
FIG. 3 is a schematic view of a split configuration of an outer skin provided by an embodiment of the present invention;
FIG. 4 is a schematic view of a split structure of an inner skin provided by 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 big end of the returnable airship adopts a detachable heat-proof structure, the heat-proof layer is connected with a metal structure of the returnable cabin through a carbon skin honeycomb structure plate of a bearing structure, the big end of the airship is of a blunt sphere opening structure, and the thickness-variable configuration (the configuration is shown in figure 1) from the sphere bottom to the corner is increased progressively, so that the functions of bearing and heat-proof can be realized simultaneously.
FIG. 2 is a flow chart of a method for manufacturing a thermal protection and load bearing integrated outsole structure of a return airship according to an embodiment of the invention. As shown in fig. 2, the method comprises the steps of:
firstly, preparing a core material, an inner skin and an outer skin of a sandwich structure in the integrated outsole bearing structure.
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 skin and the inner surface of the heat-proof layer, drilling the embedded part hole of the outer skin, and machining the screw hole on the outer skin and the inner surface of the heat-proof layer.
And fourthly, gluing and curing the core material, the embedded part and the outer skin of the sandwich structure.
Fifthly, gluing and curing the core material and the inner skin of the sandwich structure; and (5) drilling embedded part holes of the inner skin.
And sixthly, machining a buried hole in the inner skin 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 and machining the outer contour of the interlayer and the large opening, and brushing glue, curing and polishing the outer surface of the heat-proof layer of the integrated outsole.
The sandwich structure is an X-cor sandwich structure, a honeycomb sandwich structure, a foam sandwich structure and a lattice structure.
The sandwich structure skin 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 inner skin and the outer skin are formed by manually 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 inner surface of the heat-proof material is brushed with high-temperature-resistant phenolic resin, and the brushing amount of the brushing glue is 100-500 g/m2And (3) a range.
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 outer surface of the heat-proof material is brushed with high-temperature-resistant phenolic resin, and the brushing amount of the brushing glue is 100-500 g/m2And (3) a range.
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 outsole support tool is designed according to the net size of a pneumatic outer molded surface (convex surface) redesigned by a process, the overall dimension of the outsole support tool is larger than the redesigned product dimension, and the outsole support 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 reinforcement and resin matrix of the skin are selected according to the target properties and dimensions of the product.
(2) And selecting the core material of the sandwich structure according to the target performance of the integrated outsole.
(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 material skin pre-forming blank by manually laying or automatically laying wires or automatically laying tapes with the prepreg in the step (3).
(5) And (4) curing and molding the skin preform 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 amount of the phenolic resin is 100-500 g/m2And (3) a range.
(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) determining an inner skin split scheme and an outer skin split scheme, then pasting the outer skin split 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) according to the scheme, 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 rear embedded parts of corresponding types and quantity in the rear embedded holes in the 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) Coating high-temperature-resistant phenolic resin on the outer surface of the heat-proof material in the step (16), wherein the coating amount is 100-500 g/m2And (4) obtaining an integrated outsole.
In the step (9), the outer skin comprises a central circular split 1 and a plurality of peripheral fan-shaped splits 2; the plurality of peripheral fan-shaped split parts 2 are arranged along the circumferential direction of the central circular split part 1, and two adjacent peripheral fan-shaped split parts 2 are connected through a splicing seam 31. The sector-shaped partial section 2 is provided with an opening 4 along the circumferential direction.
The outer skin is a circular flap with the diameter phi of 300-phi 1500 on the top, the periphery connected with the circle is divided into 2-36 fan-shaped flaps, 1-5 openings are respectively cut on two sides of each flap along the bus direction along the circumferential direction, and the length of each opening is 5-150 mm. All the split pieces are spliced into a whole, and a splicing seam of 0.5-3 mm is reserved when each split piece is spliced. The split mode is shown in fig. 3.
The inner skin comprises a central circular split 11 and a plurality of peripheral fan-shaped splits 21; the plurality of peripheral fan-shaped petals 21 are arranged along the circumferential direction of the central circular petal 11, and two adjacent peripheral fan-shaped petals 21 are connected through the splicing seams 31. The sectorial petals 21 are provided with openings 41 along the circumferential direction.
The inner skin is a circular flap with the diameter phi of 300-phi 1500 on the top, the periphery connected with the circle is divided into 2-36 fan-shaped flaps, 1-5 openings are respectively cut on two sides of each flap along the bus direction along the circumferential direction, and the length of each opening is 5-150 mm. All the split pieces are spliced into a whole, and a splicing seam of 0.5-3 mm is reserved when each split piece is spliced. The split mode is shown in fig. 4.
The preparation is illustrated in more detail in the following 1 example:
the maximum outer diameter R2035.1mm at the opening of the integrated outsole is R4715mm and R4570mm, the diameters of the inner spherical surface and the outer spherical surface are respectively, and the thickness of the bottom of the ball is 57mm to the gradually increased variable thickness configuration at the corner through the eccentric design of the spherical center of the inner spherical surface and the outer spherical surface and the eccentricity of 88 mm. The preparation method of the integrated outsole with the honeycomb sandwich thickness of 30mm, the skin material of M40J/4211 resin composite material, the skin thickness of 0.64mm and the honeycomb core specification of 0.03 multiplied by 3 comprises the following steps:
(1) high modulus carbon fiber M40J is selected as a reinforcement of the skin, and high temperature epoxy 4211 resin is used as a resin matrix.
(2) A porous aluminum honeycomb core is selected as a core material.
(3) And (2) arranging the reinforcement and the matrix in the step (1) by a solution method to prepare a unidirectional prepreg with a single-layer thickness of 0.08 mm.
(4) And (4) manually laying the prepreg in the step (3) to prepare a carbon fiber composite material skin pre-forming blank, and splitting the skin into 7 pieces.
(5) And (4) curing and molding the skin preform 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) Brushing 192 phenolic resin on the inner surface of the heat-proof material processed in the step (6), wherein the brushing amount (250 +/-10) g/m2。
(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 (3) determining an inner skin and an outer skin split case, then dividing the carbon fiber outer skin prepared in the step (5) into 7 segments according to the scheme, pasting the carbon fiber outer skin on the high-temperature-resistant silicon rubber layer on the inner surface of the heat-proof material in the step (8), wherein the top of the carbon fiber outer skin is a phi 1200 circle, and the periphery of the carbon fiber outer skin is a 6-segment sector, and vacuumizing, pressurizing and curing the carbon fiber outer skin through a vacuum bag-oven.
(10) And (4) polishing and cleaning the surface of the outer skin in the step (9), brushing base glue of J47B and sticking a layer of J47C glue film.
(11) And (3) splicing the honeycomb core into 11 segments, wherein the top is a circle with phi 1200, the periphery is a sector with 10 segments, the segments are connected by J47D, and the honeycomb core is attached to the outer skin in the step (10).
(12) And (3) wrapping foaming glue J47D around the embedded part, embedding the honeycomb core into the embedded part, assembling the embedded part into a position, and vacuumizing and pressurizing the embedded part by using a vacuum bag-autoclave for curing.
(13) Brushing J47B primer on the lower surface of the carbon fiber inner skin prepared in the step (5), pasting a layer of J47C glue film, splitting into pieces, wherein the top is a phi 1300 circle, the periphery is 6 fan-shaped, then pasting the carbon fiber inner skin on the surface of the honeycomb core in the step (12), and the glue 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 rear embedded parts of corresponding types and quantity in the rear embedded holes in the 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) Coating 192 phenolic resin on the outer surface of the heat-proof material in the step (16), wherein the glue amount is (250 +/-10) g/m2And obtaining the integrated outsole.
Fig. 1-1 are schematic views of a sandwich structure in a thermal protection and load bearing integrated outsole structure of a return airship according to an embodiment of the invention. As shown in figure 1-1, compared with the prior art, the integrated outsole structure of the invention is an outer layer heat-proof material and inner layer sandwich structure, has heat-proof performance and bearing performance, and has the detachable and reusable functions, and the preparation method of the invention has high product precision and the dimensional precision is superior to 2 mm. The heat-proof layer has wide size range, the inner spherical radius r1 of the blunt sphere is in the range of SR500 mm-SR 3000mm, the outer spherical radius r2 of the blunt sphere is in the range of SR500 mm-SR 4000mm, the total height h is within 2m, and the thickness delta of the heat-proof layer isfThe thickness delta of the sandwich structure is within the range of 20-100 mmcAt 10 ^ e80mm range, sandwich structure panel thickness deltamWithin the range of 0.1-4 mm, the thickness delta of the sandwich structure core materialxIn 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 (9)

1. A preparation method of a heat-proof and load-bearing integrated outsole structure of a return airship is characterized by comprising the following steps:
the method comprises the following steps: preparing a core material, an inner skin and an outer skin in the bearing structure of the integrated outsole;
step two: preparing an integrated outsole heat-proof layer, 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 an outer skin and the inner surface of the heat-proof layer, forming embedded part holes in the outer skin, and machining screw holes in the outer skin and the inner surface of the heat-proof layer;
step four: one surface of the core material is glued with the outer skin, and the embedded part is embedded into the core material through the embedded part hole of the outer skin and is solidified;
step five: arranging embedded part holes on the inner panel, bonding the inner skin and the other surface of the core material, curing, and arranging the embedded part holes on the inner skin according to the embedded position of the embedded part in the core material;
step six: processing a rear buried hole in the inner skin, installing a rear buried part in the rear buried hole, and bonding and curing the rear buried part and the inner skin;
step seven: brushing glue, curing and polishing the outer surface of the heat-proof layer of the integrated outsole;
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;
the gluing and curing of the outer skin and the inner surface of the heat-proof layer specifically comprises the following steps:
the method comprises the following steps: preparing a circular flap with the diameter phi of 300-1500 at the center of the top of the outer skin;
step two: preparing a plurality of fan-shaped petals on the periphery of the outer skin;
step three: attaching the circular flap to the top of the inner surface of the heat-proof layer of the hood, so that the circle center of the circular flap of the outer skin is concentric with the circle center of the top of the heat-proof layer of the hood;
step four: cutting 1-5 openings at two sides of the fan-shaped petal along the bus direction along the circumferential direction, wherein the length of the openings is 5-150 mm;
step five: all the fan-shaped petals are spliced into a whole, a splicing seam of 0.5-3 mm is reserved when each fan-shaped petal is spliced, and the fan-shaped petals are vacuumized, pressurized and cured through a vacuum bag-oven.
2. The method of making a return airship heat protection and load bearing integrated outsole structure as claimed in claim 1, wherein: the first step specifically comprises the following steps:
selecting a reinforcement and a matrix of an inner skin, a reinforcement and a matrix of an outer skin and a core material of a sandwich structure;
arranging the reinforcement and the matrix of the inner skin 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 skin pre-forming blank, and curing and forming the inner skin pre-forming blank in a vacuum bag-autoclave mode to obtain the inner skin of the integrated outsole;
arranging the reinforcement and the matrix of the outer skin 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 skin pre-forming blank, and curing and forming the outer skin pre-forming blank in a vacuum bag-autoclave mode to obtain the outer skin of the integrated outsole.
3. The method of making a return airship heat protection and load bearing integrated outsole structure as claimed 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 special supporting tool or combined clamp clamping.
4. The method of making a return airship heat protection and load bearing integrated outsole structure as claimed 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 content of the first and second substances,
one surface of the core material and the outer skin are glued by using an adhesive J47C adhesive film or J310B adhesive film.
5. The method of making a return airship heat protection and load bearing integrated outsole structure as claimed in claim 1, wherein: in the fifth step, the bonding and curing of the inner skin and the core material specifically comprises the following steps:
the method comprises the following steps: preparing a circular flap with the diameter phi of 300-1500 at the center of the top of the inner skin;
step two: preparing a plurality of fan-shaped petals on the periphery of the inner skin;
step three: attaching the circular valve to the top of the core material of the hood, wherein the circle center of the circular valve of the inner skin is required to be concentric with the circle center of the top of the core material;
step four: cutting 1-5 openings at two sides of the fan-shaped petal along the bus direction along the circumferential direction, wherein the length of the openings is 5-150 mm;
step five: splicing all the split pieces into a whole, and reserving a splicing seam of 0.5-3 mm when each split piece is spliced;
the adhesive for gluing the inner skin and the core material is a J47C adhesive film or a J310B adhesive film, and the inner skin and the core material are vacuumized, pressurized and cured through a vacuum bag-autoclave.
6. The method of making a return airship heat protection and load bearing integrated outsole structure as claimed in claim 1, wherein: in the sixth step, the adhesive for gluing the rear embedded part and the inner skin is EA934NA or Redux420 adhesive or J133 adhesive.
7. The method of making a return airship heat protection and load bearing integrated outsole structure as claimed 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.
8. The method of making a return airship heat protection and load bearing integrated outsole structure as claimed in claim 1, wherein: the radius r1 of the inner spherical surface of the blunt sphere with the integrated outsole is 500-3000 mm, the radius r2 of the outer spherical surface of the blunt sphere is 500-4000 mm, the total height h is within 2m, and the thickness delta of the heat-proof layer isfWithin the range of 20-100 mm, the thickness delta of the sandwich structurecWithin the range of 10-80 mm, the thickness delta of the outer skin of the sandwich structuremIn the range of 0.1-4 mm, the thickness delta of the core material of the sandwich structurexIn the range of 2-79.6 mm.
9. The method of making a return airship heat protection and load bearing integrated outsole structure as claimed 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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