CN110524913B - Foam sandwich structure of composite material launching tube and integrated forming method thereof - Google Patents
Foam sandwich structure of composite material launching tube and integrated forming method thereof Download PDFInfo
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- CN110524913B CN110524913B CN201910903803.0A CN201910903803A CN110524913B CN 110524913 B CN110524913 B CN 110524913B CN 201910903803 A CN201910903803 A CN 201910903803A CN 110524913 B CN110524913 B CN 110524913B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
Abstract
The invention discloses an integrated molding method of a foam sandwich structure of a composite material launching tube, which comprises the following steps: an inner structural layer; an outer structural layer; the annular ribs are arranged between the inner structural layer and the outer structural layer at intervals along the axial direction of the inner structural layer; wherein, every group ring muscle includes: the first annular rib comprises a first annular rib base body and a first annular rib main body; the second annular rib and the first annular rib are arranged at intervals, and the second annular rib comprises a second annular rib base body and a second annular rib main body; and a plurality of reinforcing regions arrayed along the circumference of the inner structural layer; the two ends of the reinforcing area are respectively connected with the first annular rib and the second annular rib; the axial sections of the first annular rib matrix and the second annular rib matrix are both trapezoidal, and the bottom surfaces of the trapezoids are connected with the inner structure layer; and the foam filling layer is arranged between the inner structural layer and the outer structural layer and is positioned in a space outside the first annular rib, the second annular rib and the reinforcing area.
Description
Technical Field
The invention belongs to the technical field of composite material launching tubes, and particularly relates to a foam sandwich structure of a composite material launching tube and an integrated forming method thereof.
Background
The launching tube is an important component of a missile weapon system, has the functions of orientation, support, erection, temperature regulation, storage and the like, and bears great pressure when the missile is launched. The existing composite material launching tube has low bearing efficiency and large weight.
As a novel structural form, the launching tube foam sandwich structure has the advantages of light weight, high specific strength, easiness in processing and modification, corrosion resistance, heat preservation effect, strong designability and the like, and is widely applied to the fields of buildings, traffic, ships, aerospace and aviation and the like. However, the problem of the continuity of the fibers of the sandwich structure is always a concern, and the problem affects the whole bearing capacity of the launch tube, and causes the phenomena of cracks, service life reduction and the like of the launch tube.
In the prior art, the forming technology of the reinforced area of the foam sandwich structure of the launching tube is to embed the whole reinforced block between the foam blocks, so that the fibers of the reinforced area and the fibers of the ring ribs on two sides are not continuous, and the bearing capacity of the sandwich structure is influenced. In addition, the right angle formed between the ring rib and the inner structure layer after the ring rib is machined can cause the stress concentration phenomenon at the root part of the ring rib.
Disclosure of Invention
The invention aims to provide a foam sandwich structure of a composite material launching tube, wherein an annular rib and an inner structure layer are in transition by adopting an inclined shoulder, so that the phenomenon of stress concentration at the root part of the annular rib can be improved.
The invention also aims to provide an integrated molding technology of the foam sandwich structure of the composite material launching tube, the fibers of the reinforced area can be continuous to the annular ribs on two sides, the fiber continuity is ensured to the maximum extent, the interlayer strength is improved, and the bearing capacity of the reinforced area of the composite material can be better improved.
The technical scheme provided by the invention is as follows:
an integrated molding method of a foam sandwich structure of a composite material launch canister comprises the following steps:
an inner structural layer which is cylindrical;
the outer structural layer is cylindrical and is coaxially sleeved on the outer side of the inner structural layer;
the multiple groups of ring ribs are arranged between the inner structural layer and the outer structural layer at intervals along the axial direction of the inner structural layer;
wherein, every group ring muscle includes:
the first annular rib comprises a first annular rib base body and a first annular rib main body;
the first annular rib substrate is annular and is coaxially jointed on the inner structural layer; the first annular rib main body is annular, and the inner annular surface and the outer annular surface of the first annular rib main body are respectively connected with the first annular rib substrate and the outer structure layer;
the second annular rib and the first annular rib are arranged at intervals, and the second annular rib comprises a second annular rib base body and a second annular rib main body;
the second annular rib base body is annular and is coaxially jointed on the inner structural layer; the second annular rib main body is annular, and the inner annular surface and the outer annular surface of the second annular rib main body are respectively connected with the second annular rib substrate and the outer structure layer; and
a plurality of reinforcement regions in a circumferential array along the inner structural layer; the two ends of the reinforcing area are respectively connected with the first annular rib and the second annular rib;
the axial cross sections of the first annular rib base body and the second annular rib base body are both trapezoidal, and the bottom surfaces of the trapezoids are connected with the inner structure layer;
and the foam filling layer is arranged between the inner structural layer and the outer structural layer and is positioned in the space outside the first annular rib, the second annular rib and the reinforcing area.
Preferably, the axial cross sections of the first annular rib base body and the second annular rib base body are both isosceles trapezoids.
Preferably, the base angle of the isosceles trapezoid is 5 ° to 20 °.
Preferably, the axial cross sections of the second annular rib main body and the second annular rib main body are rectangular;
the width of the joint surface of the first annular rib main body and the first annular rib base body is the same; the width of the joint surface of the second annular rib main body and the second annular rib base body is the same.
An integrated forming method of a foam sandwich structure of a composite material launching tube comprises the following steps:
step one, manufacturing an inner structure layer;
secondly, laying a first annular rib substrate and a second annular rib substrate on the inner structure layer, and after curing, respectively processing inclined planes on two sides of the first annular rib substrate and the second annular rib substrate;
thirdly, installing a foam filling layer between the first annular rib substrate and the second annular rib substrate, and pressurizing and fixing the foam filling layer;
removing part of the foam filling layer, and laying a reinforcing area at the position where the foam filling layer is removed until the height of the reinforcing area is the same as that of the first annular rib substrate and the second annular rib substrate;
step five, synchronously laying the first annular rib main body, the second annular rib main body and the reinforcing area, and curing;
wherein the reinforcing area is kept continuous with the first annular rib main body and the second annular rib main body on two sides of the reinforcing area in the laying process,
and sixthly, manufacturing the outer structure layer, and curing and demolding.
Preferably, in the second step, the curing system is 60-190 ℃ and the curing time is 6-30 h.
Preferably, in the third step, the foam filling layer is fixed by pressing by dry yarn winding;
wherein, the dry yarn is wound by 10-50 groups, and the tension range of each group of yarn is 20-50N.
Preferably, in the fifth step, the first annular rib main body, the second annular rib main body and the reinforcing area respectively comprise 90-degree layers, 0-degree layers and axial inclination +/-theta-degree layers;
when the layers are laid at 0 degree and the layers are axially inclined at +/-theta degrees, the reinforcing area is kept continuous with the first annular rib main body and the second annular rib main body on two sides of the reinforcing area, and the theta degree is more than 0 degree and less than 90 degrees.
Preferably, in the fifth step, the curing system is 60-190 ℃ and the curing time is 6-30 h.
Preferably, the forming thickness of the inner structure layer is 3-30 mm, and the fiber volume content is 50-70%; the forming thickness of the outer structure layer is 3-40 mm, and the fiber volume content is 50-70%.
The invention has the beneficial effects that:
according to the foam sandwich structure of the composite material launching tube, the annular rib and the inner structure layer are in transition through the inclined shoulder, and the stress concentration phenomenon at the root part of the annular rib can be improved.
According to the integrated forming technology of the foam sandwich structure of the composite material launching tube, the fibers in the reinforcing area can be continuous to the annular ribs on two sides, the continuity of the fibers is guaranteed to the greatest extent, the interlayer strength is improved, and the bearing capacity of the reinforcing area of the composite material can be better improved.
Drawings
FIG. 1 is a schematic distribution diagram of a foam sandwich structure of a composite launch canister according to the present invention.
FIG. 2 is a schematic axial cross-sectional view of a composite launch canister foam sandwich structure according to the present invention.
FIG. 3 is a schematic diagram of reinforcement area and hoop reinforcement + θ ° ply prepreg lay-up according to the present invention.
FIG. 4 is a schematic view of the prepreg or carbon cloth laying of the reinforcement area and the ring rib 0 degree ply according to the present invention.
FIG. 5 is a schematic representation of the placement of a 90 ° lay-up of the reinforcement area and hooped rebar of the present invention.
Detailed Description
The present invention is further described in detail below with reference to the attached drawings so that those skilled in the art can implement the invention by referring to the description text.
As shown in fig. 1-2, the present invention provides a composite material launch canister foam sandwich structure comprising: an inner structural layer 110 (inner cylinder), an outer structural layer 120 (outer cylinder), a plurality of groups of annular ribs 130 and a foam filling layer 140. Each group of the ring ribs 130 comprises ring ribs 131, ring ribs 132 and one or more reinforcing areas 133 connected between the ring ribs 131 and the ring ribs 132, which are arranged at intervals; and the reinforcing section 133 is disposed along the axial direction of the launch barrel. A plurality of groups of annular ribs 130 are arranged between the inner structural layer 110 and the outer structural layer 120 at intervals along the axial direction of the inner structural layer; foam filling layers 140 are filled between two adjacent groups of annular ribs 130 and between the annular ribs 131 and the annular ribs 132 of the same group outside the reinforced areas 133; that is, the space between the inner structural layer 110 and the outer structural layer 120 is filled with the annular ribs 131, the annular ribs 132, the reinforcing regions 133 and the foam filling layer 140.
The axial cross sections of the bottom 131a of the annular rib 131 and the bottom 132a of the annular rib 132 (close to the inner structure layer) are both isosceles trapezoids, and the bottom surfaces of the isosceles trapezoids are connected with the inner structure layer 110. The top 131b of the annular rib 131 and the top 132b of the annular rib 132 have rectangular axial sections; and the widths of the joint surfaces of the top 131b of the ring rib 131 and the bottom 131a of the ring rib 131 are the same; the engaging surfaces of the top 132b of the ring rib 132 and the bottom 132a of the ring rib 132 have the same width.
The invention provides an integrated molding method of a foam sandwich structure of a composite material launching tube, which comprises the following steps:
step one, forming a structural layer in the launching tube, wherein the structural layer comprises an ablation-resistant layer and a main bearing layer.
And (3) forming an ablation resistant layer: and coating an ablation-resistant coating on the surface of the die, wherein the coating thickness is 0.2-3 mm, and curing at the ambient temperature of 20-150 ℃ for 2-48 h after coating.
Forming a main bearing layer: the main bearing layer is formed by adopting carbon fiber wet winding, prepreg laying and carbon cloth laying processes, and the carbon fiber is wound in the circumferential direction to form a 90-degree laying layer; the prepreg plies include axial plies (0 degree plies) and plies that are axially inclined ± θ degrees. The winding glue is made of epoxy resin, and the prepreg is a carbon fiber/epoxy resin reinforced material.
(1) And laying carbon cloth. And laying carbon cloth on the outer surface of the ablation-resistant layer, wherein the laying thickness is 0.2-2 mm.
(2) And then the layering is [ 90/+/-theta/0 ] n, wherein theta can be any value between 0-90 degrees, the width of the wound yarn is 20-200 mm, the laying thickness range is 3-30 mm, and the fiber volume content is 50-70%.
And step two, forming the ring rib for the first time. The ring rib is formed by adopting carbon fiber wet winding, prepreg laying and carbon cloth laying processes, and the carbon fiber is wound in the circumferential direction to form a 90-degree laying layer; the prepreg plies include axial plies (0 degree plies) and plies that are axially inclined ± θ degrees. The first forming mainly comprises the step of forming an inclined shoulder at the bottom (close to the inner structural layer) of the annular rib, wherein the laying thickness of the annular rib is 8-30 mm, and the axial length of the annular rib is 50-2000 mm.
And step three, carrying out first curing on the ring ribs after the laying is finished. The curing system is 60-190 ℃, the curing time is 6-30 h, the curing equipment is a curing furnace, and the curing adopts rotary curing.
Step four, the ring rib is formed and lathed for the first time, oblique shoulders are machined, the radial cross sections of the bottoms 131a and 132a of the ring rib are isosceles trapezoids, and the inclination of the oblique shoulders is 5-20 degrees. The bottom of the ring rib is processed into an isosceles trapezoid shape after being paved and molded, so that the bearing capacity of the ring rib can be improved, and the phenomenon of stress concentration at the root part of the ring rib can be improved.
Step five, preparing foam. The foam compression strength adopted for manufacturing the launching tube is more than 1MPa, and the density is 50-130 kg/m3And the requirements of light weight, bearing pressure and heat preservation can be met. The two sides of the foam are processed with inclined planes with the same height as the inclined shoulders on the ring rib, and the angle of the inclined planes is matched with the inclined planes of the ring rib; the foam inner surface is matched with the outer surface of the inner cylinder.
And step six, foam installation. During installation, the inclined planes at two sides of the foam are in butt joint with the inclined planes of the ring ribs, after the foam is installed, dry yarns are wound and pressurized to fix the foam, 10-50 yarns are used for winding, and the tension range of each yarn is 20-50N.
And step seven, curing the foam, wherein the curing temperature is 20-120 ℃, and the curing time is 4-48 h. After solidification, the foam at the position where the reinforced area needs to be laid is scratched out, and the laying space of the reinforced area is processed.
And step eight, secondary molding of the annular rib, wherein the molding of the annular rib tops 131b and 132b (close to the outer structural layer) and the molding of the reinforcing area 133 are included. The forming technology of the top 131b and 132b of the annular rib is the same as that of the first forming technology (the bottom 131a and 132a of the annular rib), the fibers and the annular rib fibers on two sides are continuous when the reinforcing area 133 is laid, and the forming thickness is 8-70 mm.
The forming process of the reinforcing area and the ring ribs on two sides of the reinforcing area comprises the following steps:
(1) the reinforcing area is laid separately: the reinforcing area 133 is independently laid to be as thick as the height of the first molding of the ring rib (the ring rib bottoms 131a and 132 a); the carbon cloth is laid at each 90 ° ply of the reinforced area 133.
(2) The reinforcing area and the annular rib are integrally formed, and the laying angle of each layer of the reinforcing area and each layer of the annular rib is kept the same. When the prepreg is laid in the +/-theta DEG ply, the fibers of the reinforcing area 133 and the two- side ring ribs 131 and 132 are kept continuous, namely, the fibers of the prepregs 133a, 133b and 133c laid in the +/-theta DEG reinforcing area extend to the outer edges of the two- side ring ribs 131 and 132, and meanwhile, the laying angles of other positions of the two- side ring ribs 131 and 132 corresponding to the layers are the same as the laying angle of the reinforcing area 133; as shown in fig. 4, when the ring ribs are laid at 0 ° of the prepreg and laid with the carbon cloth, the reinforced area 133 is kept continuous with the fibers of the ring ribs 131 and 132 on both sides; as shown in fig. 5, when the layers are laid at 90 °, the annular ribs 131 and 132 are formed by winding fibers, and the reinforcing area 133 is formed by laying carbon cloth. Wherein θ can be any value between 0 ° and 90 °.
(3) And manufacturing a pressing plate according to the size of the reinforced area, performing pre-pressing once after each circulation is finished, winding the two ends and the middle of the pressing plate with fibers, and pressurizing for 3-20 min by using the fiber tension.
And step nine, curing the annular ribs for the second time. The curing system is 70-160 ℃, the curing equipment is a curing furnace, and the curing adopts rotary curing.
Step ten, turning the ring rib for the second time, fixing the die on a lathe, processing the outer surfaces of the foam and the ring rib, wherein the processing outer diameter of the foam is the same as that of the ring rib, and processing the foam into a cylinder shape.
And step eleven, forming an outer layer structure (outer cylinder) of the launching cylinder. The outer structure layer is formed by adopting carbon fiber wet winding, prepreg laying and carbon cloth laying processes, and the prepreg is wound in the circumferential direction to form a 90-degree laying layer; the prepreg plies include axial plies (0 degree plies) and plies that are axially inclined ± θ degrees. The forming thickness range is 3-40 mm, and the fiber volume content is 50-70%.
And step twelve, performing integral curing in a rotary curing mode, and then performing machining to obtain the shape of the shooting barrel.
And step thirteen, demolding to obtain the foam sandwich structure of the composite material launching tube.
Examples
Step one, forming a structural layer in the launching tube, wherein the structural layer comprises an ablation-resistant layer and a main bearing layer. The winding glue is made of epoxy resin, the prepreg is a carbon fiber/epoxy resin reinforced material, the thickness of a single layer is selected to be 0.2mm, the forming thickness of an inner structure layer is 6mm, and the volume content of the fiber is 50-70%.
The inner structure layer of the forming launch canister comprises an ablation-resistant layer and a main bearing layer.
Firstly, the surface of the mould is coated with an ablation-resistant coating with the thickness of 0.6mm, and the mould is cured after the coating is finished.
Forming a main bearing layer: and laying carbon cloth. And laying carbon cloth on the outer surface of the ablation-resistant layer, wherein the laying thickness is 0.4 mm. Then the laying is [90/+45/0/-45] n, the laying thickness is 8mm, and the fiber volume content is 50-70%.
And step two, forming the ring rib for the first time. The annular rib laying layer is [90/+ 45/0/90/-45/carbon cloth ] n, the first forming is to form an inclined shoulder at the bottom of the annular rib (close to the inner structural layer), the laying thickness of the annular rib is 10mm, the length of the annular rib 1 is 200mm, and the length of the annular rib 2 is 313 mm.
And step three, carrying out first curing on the ring ribs after the laying is finished. The curing maximum temperature is 135 ℃, the curing time is 10 hours, and the curing equipment is a curing oven.
And step four, the ring rib is formed and lathed for the first time, and an inclined shoulder (isosceles trapezoid) is machined, wherein the inclination of the inclined shoulder is 11.3 degrees.
Step five, preparing foam. The two sides of the foam are processed with inclined planes with the same height as the inclined shoulders on the ring rib, and the inclination is 11.3 degrees, so that the inclined planes are matched with the inclined planes of the ring rib; the foam inner surface is matched with the outer surface of the inner cylinder.
And step six, foam installation. During installation, the inclined planes at two sides of the foam are butted with the inclined planes of the ring ribs, after the foam is installed, the foam is wound and pressurized by dry yarns to fix the foam, 30 bunches of yarns are used, and the average tension of each bunch of yarns is 30N.
And step seven, curing the foam, wherein the foam is cured at room temperature for 24 hours. After solidification, the foam at the position where the reinforced area needs to be laid is scratched out, and the laying space of the reinforced area is processed.
And step eight, secondary molding of the ring ribs, wherein the ring rib layering is [90/+ 45/0/90/-45/carbon cloth ] n, and the molding comprises the molding of the top of the ring ribs (close to the outer structural layer) and the molding of the reinforced area. When the reinforcing area is laid, the fibers are ensured to be continuous with the annular rib fibers on the two sides, and the forming thickness is 20 mm.
The forming process of the reinforcing area and the ring ribs on two sides of the reinforcing area comprises the following steps:
(1) the reinforcing area is laid separately: the reinforcing area is independently laid to be 10mm thick, and the height of the reinforcing area and the first-time molding of the ring rib is equal to the height of the ring rib substrate; and laying carbon cloth on each 90-degree layer of the reinforced area.
(2) The reinforcing area and the ring rib are integrally formed. When the prepreg is paved at +/-45 degrees, the reinforcing area 133 and the ring rib fibers at two sides are kept continuous; when the prepreg is laid at 0 degree and the carbon cloth is laid, the reinforcing area and the ring rib fibers on the two sides are kept continuous; when 90-degree laying is carried out, the annular ribs are formed by winding fibers, and the carbon cloth in the reinforcing area is laid.
(3) And manufacturing a pressing plate according to the size of the reinforced area, performing pre-pressing once after each circulation is finished, winding the two ends and the middle of the pressing plate by using fibers, and pressurizing for 10min by using fiber tension.
And step nine, curing the annular ribs for the second time. The curing maximum temperature is 135 ℃, the curing time is 10 hours, and the curing equipment is a curing oven.
Step ten, turning the annular rib for the second time, and processing the foam and the outer surface of the annular rib.
Step eleven, forming the outer barrel of the launching barrel, wherein the forming thickness range is 7mm, and the fiber volume content is 50-70%.
And step twelve, performing integral curing in a rotary curing mode, and then performing machining to obtain the shape of the shooting barrel.
And step thirteen, demolding to obtain the foam sandwich structure of the composite material launching tube.
First, the fiber continuity of the reinforced region is ensured in the present invention. When the whole embedded block is put in and is subjected to radial force, the stress is related to the thicknesses and the strengths of the inner structure layer and the outer structure layer and the area of the embedded block, and the embedding speed mainly depends on the inner structure layer and the outer structure layer to bear external force; when the fiber continuous laying process of the reinforcing area is applied to the annular ribs, under the radial stress condition, the reinforcing area and the annular ribs bear pressure or tension together, the bearing capacity depends on the inner and outer structural layers, the thickness, the strength and the joint area of the adjacent annular ribs are also related, and the bearing capacity of the whole reinforcing area is greatly increased.
Secondly, the process method of the oblique shoulder transition avoids the stress concentration phenomenon of the ring rib and effectively protects the ring rib. Each layer of the cylinder is formed by winding prepreg and carbon fiber, so that the interlayer strength is relatively low, and after the root part of the inner ring rib is processed into a right angle, the ring rib axially supports the interlayer strength depending on the ring rib, so that the ring rib is easily damaged by axial force, and the ring rib and the inner structure layer are separated seriously; when the annular rib is subjected to axial supporting force, the stress direction is changed into the stress direction perpendicular to the inclined plane by the inclined shoulder transition process method, so that the interlayer stress is avoided, the annular rib is effectively protected, and the axial bearing capacity of the annular rib is improved.
While embodiments of the invention have been described above, it is not limited to the applications set forth in the description and the embodiments, which are fully applicable in various fields of endeavor to which the invention pertains, and further modifications may readily be made by those skilled in the art, it being understood that the invention is not limited to the details shown and described herein without departing from the general concept defined by the appended claims and their equivalents.
Claims (9)
1. The integrated forming method of the foam sandwich structure of the composite material launching tube is characterized in that the foam sandwich structure of the composite material launching tube comprises the following steps:
an inner structural layer which is cylindrical;
the outer structural layer is cylindrical and is coaxially sleeved on the outer side of the inner structural layer;
the multiple groups of ring ribs are arranged between the inner structural layer and the outer structural layer at intervals along the axial direction of the inner structural layer;
wherein, every group ring muscle includes:
the first annular rib comprises a first annular rib base body and a first annular rib main body;
the first annular rib substrate is annular and is coaxially jointed on the inner structural layer; the first annular rib main body is annular, and the inner annular surface and the outer annular surface of the first annular rib main body are respectively connected with the first annular rib substrate and the outer structure layer;
the second annular rib and the first annular rib are arranged at intervals, and the second annular rib comprises a second annular rib base body and a second annular rib main body;
the second annular rib base body is annular and is coaxially jointed on the inner structural layer; the second annular rib main body is annular, and the inner annular surface and the outer annular surface of the second annular rib main body are respectively connected with the second annular rib substrate and the outer structure layer; and
a plurality of reinforcement regions in a circumferential array along the inner structural layer; the two ends of the reinforcing area are respectively connected with the first annular rib and the second annular rib;
the axial cross sections of the first annular rib base body and the second annular rib base body are both trapezoidal, and the bottom surfaces of the trapezoids are connected with the inner structure layer;
a foam filling layer arranged between the inner structural layer and the outer structural layer and positioned in a space outside the first annular rib, the second annular rib and the reinforcing area;
the molding method comprises the following steps:
step one, manufacturing an inner structure layer;
secondly, laying a first annular rib substrate and a second annular rib substrate on the inner structure layer, and after curing, respectively processing inclined planes on two sides of the first annular rib substrate and the second annular rib substrate;
thirdly, installing a foam filling layer between the first annular rib substrate and the second annular rib substrate, and pressurizing and fixing the foam filling layer;
removing part of the foam filling layer, and laying a reinforcing area at the position where the foam filling layer is removed until the height of the reinforcing area is the same as that of the first annular rib substrate and the second annular rib substrate;
step five, synchronously laying the first annular rib main body, the second annular rib main body and the reinforcing area, and curing;
wherein the reinforcing area is kept continuous with the first annular rib main body and the second annular rib main body on two sides of the reinforcing area in the laying process,
and sixthly, manufacturing the outer structure layer, and curing and demolding.
2. The integrated molding method of the composite material launching tube foam sandwich structure according to claim 1, wherein the axial cross section of the first annular rib base body and the axial cross section of the second annular rib base body are both isosceles trapezoids.
3. The integrated molding method of the composite material launching tube foam sandwich structure according to claim 2, wherein the base angle of the isosceles trapezoid is 5 ° to 20 °.
4. The integrated molding method of the foam sandwich structure of the composite material launch canister according to claim 1 or 3, characterized in that the axial cross section of the first annular rib main body and the second annular rib main body is rectangular;
the width of the joint surface of the first annular rib main body and the first annular rib base body is the same; the width of the joint surface of the second annular rib main body and the second annular rib base body is the same.
5. The integrated molding method of the foam sandwich structure of the composite material launching tube as claimed in claim 4, wherein in the second step, the curing system is 60-190 ℃ and the curing time is 6-30 h.
6. The integrated molding method of the foam sandwich structure of the composite material launching tube as claimed in claim 5, wherein in the third step, the foam filling layer is fixed by pressing with dry yarn winding;
wherein, the dry yarn is wound by 10-50 groups, and the tension range of each group of yarn is 20-50N.
7. The integrated molding method of the composite material launch canister foam sandwich structure according to claim 6, wherein in the step five, the first annular rib body, the second annular rib body and the reinforcement area respectively comprise a 90 ° ply, a 0 ° ply and an axially inclined ± θ ° ply;
when the layers are laid at 0 degree and the layers are axially inclined at +/-theta degrees, the reinforcing area is kept continuous with the first annular rib main body and the second annular rib main body on two sides of the reinforcing area, and the theta degree is more than 0 degree and less than 90 degrees.
8. The integrated molding method of the foam sandwich structure of the composite material launching tube as claimed in claim 7, wherein in the fifth step, the curing system is 60-190 ℃ and the curing time is 6-30 h.
9. The integrated forming method of the composite material launching tube foam sandwich structure according to claim 8, wherein the forming thickness of the inner structure layer is 3-30 mm, and the fiber volume content is 50-70%; the forming thickness of the outer structure layer is 3-40 mm, and the fiber volume content is 50-70%.
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| CN111186144A (en) * | 2019-12-26 | 2020-05-22 | 天津爱思达新材料科技有限公司 | Ablation-resistant composite material launching tube body structure and forming method thereof |
| CN112026199B (en) * | 2020-08-17 | 2021-07-06 | 江苏新扬新材料股份有限公司 | Method for forming composite material concentric launching tube |
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| CN103940291A (en) * | 2014-04-09 | 2014-07-23 | 北京航天发射技术研究所 | High-rigidity light launching box |
| CN104275804A (en) * | 2014-05-27 | 2015-01-14 | 航天材料及工艺研究所 | Preparation method of large-size thin-wall foam sandwich structure and application of structure |
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| CN103940291A (en) * | 2014-04-09 | 2014-07-23 | 北京航天发射技术研究所 | High-rigidity light launching box |
| CN104275804A (en) * | 2014-05-27 | 2015-01-14 | 航天材料及工艺研究所 | Preparation method of large-size thin-wall foam sandwich structure and application of structure |
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