CN214082969U - Carbon fiber composite material fairing and forming die thereof - Google Patents

Abstract

A carbon fiber composite material fairing and a forming die thereof relate to the technical field of carbon fiber composite material forming. The utility model provides a current be used for with supporting radome fairing structural style of rocket, the problem that has the high performance to the spaceflight, lightweight in the unable rocket upgrade engineering of satisfying china. The utility model discloses an end cap passes through a plurality of connecting pieces and installs the prelude at the casing, and the casing forms half cover of I quadrant or half cover of III quadrant that the structure is the same behind the horizontal plane cutting at axle place, and half cover of I quadrant can dismantle through a plurality of connecting pieces and half cover of III quadrant and be connected, and the medial surface of half cover of I quadrant or half cover of III quadrant all is equipped with the strengthening rib, the strengthening rib adds the muscle structure for the net, and a plurality of explosion bolt box installing opening is all seted up to the side of half cover of I quadrant or half cover of III quadrant. The utility model is used for the shaping of carbon-fibre composite radome fairing has satisfied the requirement to the high performance of space flight, lightweight in the china rocket upgrading engineering.

Description

Carbon fiber composite material fairing and forming die thereof

Technical Field

The utility model relates to a carbon-fibre composite shaping technical field, concretely relates to carbon-fibre composite radome fairing and forming die thereof.

Background

The composite material is a material basis of high-performance products and is an important guarantee for realizing advanced design concepts and technologies. High performance composite fairings have been successfully used in a number of national focus areas due to their structural advantages of light weight and high strength, with composite fairings being used in rockets. The requirements of high performance and light weight of spaceflight are important projects for upgrading and updating rockets in China, have multiple innovation difficulties, large technical span and high complexity, and represent the highest level of rocket manufacturing in China. The existing fairing used for matching with the rocket is made of metal materials, has a complicated structure and cannot meet the requirements of high performance and light weight of spaceflight in rocket upgrading and upgrading projects in China. In addition, because the fairing adopts the integrated design, the laying process needs to be considered during the laying design, not only the fiber continuity needs to be ensured, but also the laying angle reference needs to be reasonable and easy to implement. Resulting in a very difficult forming process for composite fairings.

In conclusion, the existing fairing structure form used for matching with the rocket has the problem that the requirements of high performance and light weight of spaceflight in rocket upgrading and upgrading projects in China cannot be met.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving current fairing structural style that is used for with rocket supporting, there is the problem that can't satisfy the high performance of china rocket upgrading and upgrading engineering to the requirement of space flight, lightweight, and then provides a carbon-fibre composite fairing and forming die thereof.

The technical scheme of the utility model is that:

a carbon fiber composite material fairing comprises an end cap A-1, a shell A-2 and a plurality of connecting pieces, wherein the shell A-2 is of a revolving body structure, the end cap A-1 is installed at the head of the shell A-2 through the connecting pieces, the shell A-2 is cut along a horizontal plane where a shaft is located to form a quadrant I half cover A-2-1 and a quadrant III half cover A-2-2 which are identical in structure, the quadrant I half cover A-2-1 is detachably connected with the quadrant III half cover A-2-2 through the connecting pieces, reinforcing ribs A-2-3 are arranged on the inner side faces of the quadrant I half cover A-2-1 and the quadrant III half cover A-2-2, and the reinforcing ribs A-2-3 are of grid reinforcing rib structures, a plurality of explosive bolt box mounting openings A-2-4 are formed in the outer side surfaces of the quadrant I half cover A-2-1 and the quadrant III half cover A-2-2.

The utility model also provides a carbon fiber composite material fairing forming die, which comprises a split die B-1, a central die B-2, a base die B-3, an outer die B-4, an outer pressing frame B-5, a small-end flange cover plate B-6 and a large-end flange cover plate B-7; the split mold B-1 is integrally of a hollow semi-revolving body shell-shaped structure, the outer side surface of the split mold B-1 is matched with the inner side surfaces of a quadrant I half cover A-2-1 and a quadrant III half cover A-2-2, the outer side surface of the split mold B-1 is provided with a net-shaped convex structure B-1-1 matched with a reinforcing rib A-2-3 arranged on the inner side surface of the quadrant I half cover A-2-1 or the quadrant III half cover A-2-2, and the inner side surface of the split mold B-1 is a smoothly-transitional arc concave surface; the whole central die B-2 is of a semi-revolution body structure, the outer side surface of the central die B-2 is matched with the inner side surface of the split die B-1, and the bottom surface of the central die B-2 is a plane; the split mold B-1 is buckled outside the central mold B-2, and the volume of the central mold B-2 is equal to the volume of the arc concave surface of the split mold B-1; the small-end flange cover plate B-6 and the large-end flange cover plate B-7 are both of semicircular plate structures, the bottom surface of the small-end flange cover plate B-6 is matched with the end surface of the small-end inward-turning flange A-X-1, the bottom surface of the large-end flange cover plate B-7 is matched with the end surface of the large-end inward-turning flange A-Z-1, and the small-end flange cover plate B-6 and the large-end flange cover plate B-7 are respectively and vertically arranged at the front end and the rear end of the split mold B-1; the outer mold B-4 is integrally of a hollow semi-revolution body shell-shaped structure, the inner side surface of the outer mold B-4 is a smoothly-transitional arc concave surface, and the inner side surface of the outer mold B-4 is matched with the outer side surface of the quadrant I half cover A-2-1 or the quadrant III half cover A-2-2; the outer mold B-4 is buckled outside the whole body of the small-end flange cover plate B-6, the split mold B-1 and the large-end flange cover plate B-7, and the sum of the volumes of the split mold B-1, the central mold B-2, the small-end flange cover plate B-6, the large-end flange cover plate B-7 and the quadrant I half cover A-2-1 or the quadrant III half cover A-2-2 is equal to the volume of the arc concave surface of the outer mold B-4; the external pressure frame B-5 is integrally of a hollow semi-revolution body shell structure, the inner side surface of the external pressure frame B-5 is a smooth transition arc concave surface, and the inner side surface of the external pressure frame B-5 is matched with the outer side surface of the external mold B-4; an external pressure frame B-5 is buckled outside the external mold B-4, and the sum of the volumes of the external mold B-4, the split mold B-1, the central mold B-2, the small-end flange cover plate B-6, the large-end flange cover plate B-7 and the quadrant I half cover A-2-1 or the quadrant III half cover A-2-2 is equal to the volume of the arc concave surface of the external pressure frame B-5; the base die B-3 is of a plate-shaped structure, the upper end face of the base die B-3 is matched with the lower end face of the external pressure frame B-5, and the bottom of the external pressure frame B-5 is detachably connected with the base die B-3 through a connecting element.

Compared with the prior art, the utility model has the following effect:

1. the utility model discloses carbon-fibre composite radome body is formed by the equipment of I quadrant half cover A-2-1 and III quadrant half cover A-2-2, and radome body medial surface is interior net, closely adds muscle, high reinforcement structure to adopt the integrated design, guarantee I quadrant half cover A-2-1 and III quadrant half cover A-2-2's intensity effectively, can satisfy the high performance to the space flight in the rocket upgrade engineering of china, lightweight requirement.

2. The utility model discloses carbon-fibre composite radome fairing forming die is used for realizing the integrated shaping of carbon-fibre composite radome fairing casing. The split mold B-1 of the forming mold is used for forming the reinforcing ribs A-2-3 and the skin on the inner side face of the carbon fiber composite material fairing shell, the split mold B-1 is divided into a plurality of mold halves according to a certain angle, and inner side demolding can be achieved when demolding is conducted. The central mold B-2 plays a role in positioning the split mold B-1, and the central mold B-2 can also play a role in supporting the split mold B-1 during pressurization. The external pressure frame B-5 and the base mold B-3 of the forming mold are in limit connection through the limit protrusions and the limit grooves which are matched with each other, and meanwhile, the mold is pressurized, so that the product damage caused by excessive pressurization can be effectively avoided. The outer pressing frame B-5 and the base mold B-3 of the forming mold are both made of metal materials, the rigidity is high, and damage to products can be prevented in the pressing process.

Drawings

FIG. 1 is an isometric view of a carbon fiber composite fairing of the present invention;

FIG. 2 is a front view of the carbon fiber composite fairing of the present invention;

FIG. 3 is a top view of the carbon fiber composite fairing of the present invention;

FIG. 4 is a bottom view of the carbon fiber composite fairing of the present invention;

FIG. 5 is a left side view of the carbon fiber composite fairing of the present invention;

FIG. 6 is a right side view of the carbon fiber composite fairing of the present invention;

FIG. 7 is a front view of the shell head end A-X of the carbon fiber composite fairing of the present invention;

FIG. 8 is a front view of the middle section A-Y of the shell of the carbon fiber composite fairing of the present invention;

FIG. 9 is a front view of the shell aft end A-Z of the carbon fiber composite fairing of the present invention;

FIG. 10 is a left side view of quadrant I half cowl A-2-1 of the carbon fiber composite fairing of the present invention;

FIG. 11 is a front view of a quadrant I half cowl A-2-1 of the carbon fiber composite fairing of the present invention;

FIG. 12 is a top view of quadrant I half cowl A-2-1 of the carbon fiber composite fairing of the present invention;

FIG. 13 is a left side view of quadrant III half cowl A-2-2 of the carbon fiber composite fairing of the present invention;

FIG. 14 is a front view of quadrant III half cowl A-2-2 of the carbon fiber composite fairing of the present invention;

FIG. 15 is a top view of quadrant III half cowl A-2-2 of the carbon fiber composite fairing of the present invention;

fig. 16 is a schematic structural view of the carbon fiber composite cowl forming mold of the present invention;

fig. 17 is an exploded view (one) of the carbon fiber composite cowl forming mold of the present invention;

fig. 18 is an exploded view of the carbon fiber composite cowl forming mold of the present invention (ii);

fig. 19 is an exploded view (iii) of the carbon fiber composite cowl forming mold of the present invention;

fig. 20 is an exploded view (iv) of the carbon fiber composite cowl forming die of the present invention.

Detailed Description

The first embodiment is as follows: the carbon fiber composite material fairing of the embodiment is described by combining fig. 1 to fig. 15, and comprises an end cap a-1, a shell a-2 and a plurality of connecting pieces, wherein the shell a-2 is of a revolving body structure, the end cap a-1 is installed at the head part of the shell a-2 through the plurality of connecting pieces, the shell a-2 is cut along a horizontal plane where a shaft is located to form a quadrant i half-cover a-2-1 and a quadrant iii half-cover a-2-2 which are identical in structure, the quadrant i half-cover a-2-1 is detachably connected with the quadrant iii half-cover a-2-2 through the plurality of connecting pieces, reinforcing ribs a-2-3 are arranged on the inner side surfaces of the quadrant i half-cover a-2-1 and the quadrant iii half-cover a-2-2, the reinforcing ribs A-2-3 are of grid reinforcing structures, and a plurality of explosive bolt box mounting openings A-2-4 are formed in the outer side surfaces of the quadrant I half cover A-2-1 and the quadrant III half cover A-2-2.

The second embodiment is as follows: the embodiment is described with reference to fig. 1 to 9, wherein a quadrant I half cover A-2-1 of the embodiment comprises a quadrant I head end A-2-1-1, a quadrant I middle section A-2-1-2 and a quadrant I tail end A-2-1-3, and a quadrant III half cover A-2-2 comprises a quadrant III head end A-2-2-1, a quadrant III middle section A-2-2-2 and a quadrant III tail end A-2-2-3; i, buckling a quadrant head end A-2-1-1 and a quadrant head end A-2-2-1 to form a shell head end A-X, wherein the shell head end A-X is of a round table shell-shaped structure, a first opening is formed in the lower bottom surface of the shell head end A-X, and a small end inward-turning flange A-X-1 is arranged on the upper bottom surface of the shell head end A-X; the quadrant middle section A-2-1-2 and the quadrant middle section III A-2-2 are buckled to form a shell middle section A-Y, the shell middle section A-Y is of a cylindrical shell-shaped structure, and the upper bottom surface and the lower bottom surface of the shell middle section A-Y are provided with second openings; i, buckling a quadrant tail end A-2-1-3 and a quadrant tail end A-2-2-3 to form a shell tail end A-Z, wherein the shell tail end A-Z is of a round table shell-shaped structure, a third opening is formed in the lower bottom surface of the shell tail end A-Z, and a large-end inward-turning flange A-Z-1 is arranged on the upper bottom surface of the shell tail end A-Z; the shell head end A-X, the shell middle section A-Y and the shell tail end A-Z are coaxially arranged from front to back in sequence and are of an integral structure, the outer diameters of the lower bottom surface of the shell head end A-X and the upper bottom surface of the shell middle section A-Y are equal and connected with each other, and the outer diameters of the lower bottom surface of the shell middle section A-Y and the lower bottom surface of the shell tail end A-Z are equal and connected with each other. Other components and connections are the same as in the first embodiment.

The third concrete implementation mode: referring to fig. 1, the embodiment will be described, in which the outer diameters of the upper and lower bottom surfaces of the casing middle sections a to Y are D1, D1 is 1200mm, the outer diameter of the lower bottom surface of the casing head end a to X is equal to the outer diameters of the upper and lower bottom surfaces of the casing middle sections a to Y, the outer diameter of the upper bottom surface of the casing tail end a to Z is D2, D2 is 850mm, the outer diameter of the lower bottom surface of the casing tail end a to Z is equal to the outer diameters of the upper and lower bottom surfaces of the casing middle sections a to Y, the length of the casing a-2 is L1, and L1 is 4125.9 mm. Other compositions and connections are the same as in the first or second embodiments.

The fourth concrete implementation mode: the present embodiment will be described with reference to fig. 1, in which the length of the i-quadrant half cover a-2-1 is L2, L2 is 4121mm, and the length of the iii-quadrant half cover a-2-2 is L3, and L3 is 4126 ± 5 mm. So set up, half cover A-2-1 of I quadrant is different with half cover A-2-2's of III quadrant length, and the purpose is the separation of being convenient for when dismantling. Other compositions and connection relationships are the same as in the first, second or third embodiment.

The fifth concrete implementation mode: the embodiment is described with reference to fig. 1, the reinforcing rib a-2-3 of the embodiment is formed by arranging 21 longitudinal ribs and 35 annular ribs in a criss-cross manner, the rib widths of the longitudinal ribs and the annular ribs are both 6mm, and the rib heights of the longitudinal ribs and the annular ribs are both 8.5 mm. According to the arrangement, the reinforcing ribs A-2-3 are arranged on the inner side surfaces of the I-quadrant half cover A-2-1 and the III-quadrant half cover A-2-2, so that the strength of the I-quadrant half cover A-2-1 and the III-quadrant half cover A-2-2 can be effectively guaranteed. Other compositions and connection relationships are the same as those in the first, second, third or fourth embodiment.

The rib a-2-3 of the present embodiment has a length × width of 80mm × 80mm, or 100mm × 100 mm.

The sixth specific implementation mode: the carbon fiber composite material fairing forming die of the embodiment is described with reference to fig. 1 to 20, and comprises a split die B-1, a central die B-2, a base die B-3, an outer die B-4, an outer pressing frame B-5, a small-end flange cover plate B-6 and a large-end flange cover plate B-7; the split mold B-1 is integrally of a hollow semi-revolving body shell-shaped structure, the outer side surface of the split mold B-1 is matched with the inner side surfaces of a quadrant I half cover A-2-1 and a quadrant III half cover A-2-2, the outer side surface of the split mold B-1 is provided with a net-shaped convex structure B-1-1 matched with a reinforcing rib A-2-3 arranged on the inner side surface of the quadrant I half cover A-2-1 or the quadrant III half cover A-2-2, and the inner side surface of the split mold B-1 is a smoothly-transitional arc concave surface; the whole central die B-2 is of a semi-revolution body structure, the outer side surface of the central die B-2 is matched with the inner side surface of the split die B-1, and the bottom surface of the central die B-2 is a plane; the split mold B-1 is buckled outside the central mold B-2, and the volume of the central mold B-2 is equal to the volume of the arc concave surface of the split mold B-1; the small-end flange cover plate B-6 and the large-end flange cover plate B-7 are both of semicircular plate structures, the bottom surface of the small-end flange cover plate B-6 is matched with the end surface of the small-end inward-turning flange A-X-1, the bottom surface of the large-end flange cover plate B-7 is matched with the end surface of the large-end inward-turning flange A-Z-1, and the small-end flange cover plate B-6 and the large-end flange cover plate B-7 are respectively and vertically arranged at the front end and the rear end of the split mold B-1; the outer mold B-4 is integrally of a hollow semi-revolution body shell-shaped structure, the inner side surface of the outer mold B-4 is a smoothly-transitional arc concave surface, and the inner side surface of the outer mold B-4 is matched with the outer side surface of the quadrant I half cover A-2-1 or the quadrant III half cover A-2-2; the outer mold B-4 is buckled outside the whole body of the small-end flange cover plate B-6, the split mold B-1 and the large-end flange cover plate B-7, and the sum of the volumes of the split mold B-1, the central mold B-2, the small-end flange cover plate B-6, the large-end flange cover plate B-7 and the quadrant I half cover A-2-1 or the quadrant III half cover A-2-2 is equal to the volume of the arc concave surface of the outer mold B-4; the external pressure frame B-5 is integrally of a hollow semi-revolution body shell structure, the inner side surface of the external pressure frame B-5 is a smooth transition arc concave surface, and the inner side surface of the external pressure frame B-5 is matched with the outer side surface of the external mold B-4; an external pressure frame B-5 is buckled outside the external mold B-4, and the sum of the volumes of the external mold B-4, the split mold B-1, the central mold B-2, the small-end flange cover plate B-6, the large-end flange cover plate B-7 and the quadrant I half cover A-2-1 or the quadrant III half cover A-2-2 is equal to the volume of the arc concave surface of the external pressure frame B-5; the base die B-3 is of a plate-shaped structure, the upper end face of the base die B-3 is matched with the lower end face of the external pressure frame B-5, and the bottom of the external pressure frame B-5 is detachably connected with the base die B-3 through a connecting element. Other compositions and connection relationships are the same as in the first, second, third, fourth or fifth embodiment.

The center die B-2 of this embodiment has two functions: on one hand, the positioning function is realized on the split mold B-1; on the other hand, the split mold B-1 can be supported when pressurized.

The lower end surface of the external pressure frame B-5 of the embodiment is provided with a plurality of limiting bulges, and the upper end surface of the base mold B-3 is provided with a plurality of limiting grooves matched with the limiting bulges of the external pressure frame B-5. On one hand, when the base mold B-3 and the external pressure frame B-5 are assembled, the limiting protrusions and the limiting grooves which are matched with each other can play a role in positioning and limiting; on the other hand, when the mold is pressurized, the problem of product damage caused by excessive pressurization can be effectively avoided.

The rear end face of the small-end flange cover plate B-6 of the embodiment is provided with a first arc limiting block, the front end face of the outer mold B-4 is provided with a first arc limiting groove matched with the first arc limiting block of the small-end flange cover plate B-6, the small-end flange cover plate B-6 and the outer mold B-4 are limited through the first arc limiting groove and the first arc limiting block which are matched with each other, and the small-end flange cover plate B-6 and the outer mold B-4 are connected through screws.

The front end face of the large-end flange cover plate B-7 of the embodiment is provided with a second arc limiting block, the rear end face of the outer mold B-4 is provided with a second arc limiting groove matched with the second arc limiting block of the large-end flange cover plate B-7, the large-end flange cover plate B-7 and the outer mold B-4 are limited through the second arc limiting groove and the second arc limiting block which are matched with each other, and the large-end flange cover plate B-7 and the outer mold B-4 are connected through screws.

As shown in FIG. 17, the outer mold B-4 is formed by sequentially connecting an outer mold head end B-4-1, an outer mold middle section B-4,2 and an outer mold tail end B-4-3 from front to back.

As shown in FIG. 17, the external pressure frame B-5 is formed by sequentially connecting the head end B-5-1 of the external pressure frame, the middle section B-5-2 of the external pressure frame and the tail end B-5-3 of the external pressure frame from front to back.

The seventh embodiment: the present embodiment will be described with reference to fig. 16 to 20, and the split mold B-1 of the present embodiment is formed by assembling a plurality of mold halves. With the arrangement, the split mold B-1 is divided into a plurality of mold halves according to a certain angle, so that the inner side demolding is facilitated during demolding. Other compositions and connection relationships are the same as in the first, second, third, fourth, fifth or sixth embodiment.

The specific implementation mode is eight: referring to fig. 16 to 20, the present embodiment is described, in which lightening holes B-5-1 are formed on all the peripheral end surfaces of the outer pressing frame B-5. By the arrangement, the weight reducing holes B-5-1 play a weight reducing role, and the requirement of light weight can be met under the condition that the rigidity is ensured. Other compositions and connection relationships are the same as those of embodiment one, two, three, four, five, six or seven.

The specific implementation method nine: the present embodiment will be described with reference to fig. 16 to 20, and the outer pressing frame B-5 and the base mold B-3 of the present embodiment are made of a metal material. Due to the arrangement, the external pressing frame B-5 and the base mold B-3 are high in rigidity, and damage to products can be prevented in the pressing process. Other compositions and connection relationships are the same as those in the first, second, third, fourth, fifth, sixth, seventh or eighth embodiment.

The above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.

Principle of operation

The forming method for manufacturing the carbon fiber composite material fairing by using the carbon fiber composite material fairing forming die of the invention is described by combining with figures 1 to 20,

the carbon fiber composite material fairing forming method is realized through the following steps:

the I-quadrant half cover A-2-1 and the III-quadrant half cover A-2-2 of the carbon fiber composite material fairing share one carbon fiber composite material fairing forming die to be manufactured independently;

step one, raw material rechecking:

the raw materials comprise a reinforcing material, a prepreg and an adhesive, wherein the reinforcing material is carbon fiber, and the prepreg is epoxy resin;

the carbon fiber is used for rechecking the tensile strength and the tensile modulus of the bundle yarn, the tensile strength of the bundle yarn is more than or equal to 3500MPa, and the tensile modulus is more than or equal to 190 GPa; the epoxy value of the epoxy resin is tested again, and is more than or equal to 0.85;

step two, prepreg manufacturing:

preparing the qualified carbon fiber raw material obtained in the first step into a prepreg with the width of 300mm by using a hot-melting pre-dipping machine;

step three, forming a reinforcing rib A-2-3:

splicing the split mold B-1 on the outer side surface of the central mold B-2, and uniformly laying the prepreg manufactured in the step two on the outer side surface of the split mold B-1, wherein the prepreg is formed into a reinforcing rib A-2-3 of a quadrant I half cover A-2-1 and a quadrant III half cover A-2-2;

step four, arranging the reinforcing ribs A-2-3:

trimming redundant prepreg on the reinforcing rib A-2-3 formed in the step three;

step five, covering and laying:

uniformly paving the prepreg manufactured in the step two on the surface of the repaired reinforcing rib A-2-3 on the outer side surface of the split mold B-1, wherein the prepreg is formed into a skin of a quadrant I half cover A-2-1 and a quadrant III half cover A-2-2;

step six, prepressing the product:

after the covering of the quadrant half cover A-2-1 or the quadrant half cover III A-2-2 is laid, firstly, integrally placing a split mold B-1 and a center mold B-2 on the upper end face of a base mold B-3, then respectively placing a small-end flange cover plate B-6 and a large-end flange cover plate B-7 on the front end and the rear end of the split mold B-1, then buckling an outer mold B-4 on the split mold B-1, finally buckling an outer pressing frame B-5 on the outer mold B-4, connecting the bottom of the outer pressing frame B-5 and the base mold B-3 together through a connecting element, and pre-pressing a product;

step seven, cold die assembly of the product:

after the product is pre-pressed, disassembling the base mold B-3, the outer mold B-4 and the external pressure frame B-5, checking whether a material shortage place exists, if so, adopting prepreg to perform filling, and then splicing the base mold B-3, the outer mold B-4 and the external pressure frame B-5 together;

step eight, hot die assembly of the product:

after the product is subjected to cold die assembly, putting the carbon fiber composite material fairing forming die and the whole product into a curing oven for heating, taking the die out of the curing oven after heating to a certain temperature, and pressurizing the product;

step nine, product curing:

after the product is subjected to hot die assembly, putting the carbon fiber composite material fairing forming die and the whole product into a curing oven for curing;

step ten, demoulding of the product:

after the product is solidified and the carbon fiber composite material fairing forming die is naturally cooled, the die is taken off from the product;

eleventh step, finishing the product

Trimming off burrs of the removed product;

step twelve, processing an explosive bolt box mounting opening A-2-4:

marking and checking the side surfaces of the shell of the trimmed quadrant I half cover A-2-1 and quadrant III half cover A-2-2 according to the processing requirement of an explosive bolt box mounting opening A-2-4, and cutting the product according to the marked line;

step thirteen, end frame turning:

firstly, machining the end faces of a small-end flange cover plate B-6 and a large-end flange cover plate B-7 of a quadrant I half cover A-2-1 and a quadrant III half cover A-2-2 in a turning mode, and machining connecting holes in the end faces of the small-end flange cover plate B-6 and the large-end flange cover plate B-7 in a drilling and die-making mode;

step fourteen, assembling the shell and the end cap A-1:

assembling a head cap A-1 on a small-end flange cover plate B-6 of the shell of the quadrant I half cover A-2-1 and the quadrant III half cover A-2-2 in a mode of glue joint and screw connection;

fifteen, nondestructive flaw detection:

carrying out full-area ultrasonic nondestructive inspection on the product before assembly, and carrying out ultrasonic nondestructive inspection on the adhesive joint surface after adhesive bonding;

thus, the molding manufacture of the quadrant I half cover A-2-1 and the quadrant III half cover A-2-2 is completed. Other compositions and connection relationships are the same as those of embodiment one, two, three, four, five, six, seven, eight or nine.

The specific implementation manner of the raw material retest described in the first step of the present embodiment is as follows: when carbon fibers enter a factory, the carbon fibers are tested in the factory according to GB/T3362-2005, the tensile strength of the bundle yarn is 4914.00Mpa, and the tensile modulus is 233.03 GPa; when the resin is delivered into the factory, the resin is subjected to factory delivery inspection according to Q/12DJ5187-2008, and the epoxy value is 0.90; when the adhesive was introduced into the factory, the introduction was examined according to Q/HSY 063-1995. The reinforcing material is T700 carbon fiber of Dongli corporation of Japan, the performance is reliable, and the purchase is guaranteed; the prepreg adopts a TDE85 epoxy resin system; the adhesive is J-133 adhesive.

The nondestructive inspection described in the fifteenth step of the present embodiment is performed according to "ultrasonic inspection by fiber reinforced plastic nondestructive inspection method" (GJB1038.1A-90) and "general procedure for ultrasonic inspection of composite material product" (HBY 2083 · 01); the internal delamination and inclusion defects of the product are within the allowable range of the composite material product flaw detection standard (Q/HBY 024-2010).

Carbon-fibre composite radome fairing forming method can realize carbon-fibre composite radome fairing integration shaping, can enough guarantee during the technology shaping of putting in succession the carbon fiber, can guarantee again to spread the layer angle benchmark reasonable, easy to carry out. The fairing adopts the grid rib, the reinforcing area and the shell skin integrated forming co-curing technology; the fairing composite material structural part is laid by adopting carbon fiber prepreg, and a metal matched die pressurization molding process is adopted; the fairing is connected with each part in a connection mode of glue joint and screw joint, hole sites of a butt-joint frame of the fairing are guaranteed by matching of a drill jig, drill jig hole sites of a connecting hole of a flange of the fairing are guaranteed, and the size of the drill jig hole sites is consistent with that of a next-stage cabin section; the prepreg laying and metal matched die pressure molding process is adopted, the operability is strong, and the method is suitable for molding complex molded surface products.

Claims (9)

1. A carbon fiber composite material radome fairing which characterized in that: the carbon fiber composite material fairing comprises an end cap (A-1), a shell (A-2) and a plurality of connecting pieces, wherein the shell (A-2) is of a revolving body structure, the end cap (A-1) is installed at the head of the shell (A-2) through the connecting pieces, the shell (A-2) is cut along the horizontal plane where a shaft is located to form a quadrant I half cover (A-2-1) and a quadrant III half cover (A-2-2) which are identical in structure, the quadrant I half cover (A-2-1) is detachably connected with the quadrant III half cover (A-2-2) through the connecting pieces, reinforcing ribs (A-2-3) are arranged on the inner side faces of the quadrant I half cover (A-2-1) and the quadrant III half cover (A-2-2), and the reinforcing ribs (A-2-3) are of a grid reinforcing rib structure, the outer side surfaces of the quadrant I half cover (A-2-1) and the quadrant III half cover (A-2-2) are respectively provided with a plurality of explosive bolt box mounting openings (A-2-4).

2. The carbon fiber composite fairing as recited in claim 1, wherein: the I-quadrant half cover (A-2-1) comprises an I-quadrant head end (A-2-1-1), an I-quadrant middle section (A-2-1-2) and an I-quadrant tail end (A-2-1-3), and the III-quadrant half cover (A-2-2) comprises an III-quadrant head end (A-2-2-1), an III-quadrant middle section (A-2-2-2) and an III-quadrant tail end (A-2-2-3); the first quadrant head end (A-2-1-1) and the third quadrant head end (A-2-2-1) are buckled to form a shell head end (A-X), the shell head end (A-X) is of a truncated cone-shaped shell structure, a first opening is formed in the lower bottom surface of the shell head end (A-X), and a small end inward-turning flange (A-X-1) is arranged on the upper bottom surface of the shell head end (A-X); the quadrant I middle section (A-2-1-2) and the quadrant III middle section (A-2-2-2) are buckled to form a shell middle section (A-Y), the shell middle section (A-Y) is of a cylindrical shell structure, and the upper bottom surface and the lower bottom surface of the shell middle section (A-Y) are provided with second openings; the tail end (A-2-1-3) of the I quadrant and the tail end (A-2-2-3) of the III quadrant are buckled to form a shell tail end (A-Z), the shell tail end (A-Z) is of a round table shell-shaped structure, a third opening is formed in the lower bottom surface of the shell tail end (A-Z), and a large-end inward-turning flange (A-Z-1) is arranged on the upper bottom surface of the shell tail end (A-Z); the shell head end (A-X), the shell middle section (A-Y) and the shell tail end (A-Z) are coaxially arranged from front to back in sequence and are of an integral structure, the outer diameters of the lower bottom surface of the shell head end (A-X) and the upper bottom surface of the shell middle section (A-Y) are equal and mutually connected, and the outer diameters of the lower bottom surface of the shell middle section (A-Y) and the lower bottom surface of the shell tail end (A-Z) are equal and mutually connected.

3. The carbon fiber composite fairing as recited in claim 2, further comprising: the outer diameters of the upper bottom surface and the lower bottom surface of the middle shell section (A-Y) are D1, D1 is 1200mm, the outer diameter of the lower bottom surface of the head end of the shell (A-X) is equal to the outer diameters of the upper bottom surface and the lower bottom surface of the middle shell section (A-Y), the outer diameter of the upper bottom surface of the tail end of the shell (A-Z) is D2, D2 is 850mm, the outer diameter of the lower bottom surface of the tail end of the shell (A-Z) is equal to the outer diameters of the upper bottom surface and the lower bottom surface of the middle shell section (A-Y), the length of the shell (A-2) is L1, and L1 is 4125.9 mm.

4. The carbon fiber composite fairing as recited in claim 3, wherein: the length of the I quadrant half cover (A-2-1) is L2, L2 is 4121mm, the length of the III quadrant half cover (A-2-2) is L3, and L3 is 4126 +/-5 mm.

5. A carbon fiber composite fairing as recited in claim 4, further comprising: the reinforcing ribs (A-2-3) are formed by arranging 21 longitudinal ribs and 35 annular ribs in a criss-cross mode, the rib widths of the longitudinal ribs and the annular ribs are both 6mm, and the rib heights of the longitudinal ribs and the annular ribs are both 8.5 mm.

6. A carbon fiber composite material fairing forming die based on any one of claims 1-5, characterized in that: the carbon fiber composite material fairing forming die comprises a split die (B-1), a central die (B-2), a base die (B-3), an outer die (B-4), an outer pressing frame (B-5), a small-end flange cover plate (B-6) and a large-end flange cover plate (B-7); the split mold (B-1) is integrally of a hollow semi-revolution body shell-shaped structure, the outer side surface of the split mold (B-1) is matched with the inner side surfaces of the quadrant I half cover (A-2-1) and the quadrant III half cover (A-2-2), the outer side surface of the split mold (B-1) is provided with a net-shaped convex structure (B-1-1) matched with a reinforcing rib (A-2-3) arranged on the inner side surface of the quadrant I half cover (A-2-1) or the quadrant III half cover (A-2-2), and the inner side surface of the split mold (B-1) is a smooth-transition arc concave surface; the whole central die (B-2) is of a semi-revolution body structure, the outer side surface of the central die (B-2) is matched with the inner side surface of the split die (B-1), and the bottom surface of the central die (B-2) is a plane; the split mold (B-1) is buckled outside the central mold (B-2), and the volume of the central mold (B-2) is equal to the volume of the arc concave surface of the split mold (B-1); the small-end flange cover plate (B-6) and the large-end flange cover plate (B-7) are both of semicircular plate structures, the bottom surface of the small-end flange cover plate (B-6) is matched with the end surface of the small-end inward-turning flange (A-X-1), the bottom surface of the large-end flange cover plate (B-7) is matched with the end surface of the large-end inward-turning flange (A-Z-1), and the small-end flange cover plate (B-6) and the large-end flange cover plate (B-7) are respectively and vertically arranged at the front end and the rear end of the split mold (B-1); the outer mold (B-4) is integrally of a hollow semi-revolving body shell-shaped structure, the inner side surface of the outer mold (B-4) is a smooth-transition arc concave surface, and the inner side surface of the outer mold (B-4) is matched with the outer side surface of the quadrant I half cover (A-2-1) or the quadrant III half cover (A-2-2); the outer die (B-4) is buckled outside the small-end flange cover plate (B-6), the split die (B-1) and the large-end flange cover plate (B-7) integrally, and the sum of the volumes of the split die (B-1), the center die (B-2), the small-end flange cover plate (B-6), the large-end flange cover plate (B-7) and the quadrant I half cover (A-2-1) or the quadrant III half cover (A-2-2) is equal to the volume of the arc concave surface of the outer die (B-4); the whole external pressure frame (B-5) is of a hollow semi-revolution body shell structure, the inner side surface of the external pressure frame (B-5) is a smooth transition arc concave surface, and the inner side surface of the external pressure frame (B-5) is matched with the outer side surface of the external mold (B-4); the external pressure frame (B-5) is buckled outside the external mold (B-4), and the sum of the volumes of the external mold (B-4), the split mold (B-1), the central mold (B-2), the small-end flange cover plate (B-6), the large-end flange cover plate (B-7) and the quadrant I half cover (A-2-1) or the quadrant III half cover (A-2-2) is equal to the volume of the arc concave surface of the external pressure frame (B-5); the base die (B-3) is of a plate-shaped structure, the upper end face of the base die (B-3) is matched with the lower end face of the external pressure frame (B-5), and the bottom of the external pressure frame (B-5) is detachably connected with the base die (B-3) through a connecting element.

7. The carbon fiber composite material cowl forming die as claimed in claim 6, wherein: the integral structure of the split mold (B-1) is formed by assembling a plurality of mold halves.

8. The carbon fiber composite material cowl forming die as claimed in claim 7, wherein: the peripheral end faces of the external pressure frame (B-5) are provided with lightening holes (B-5-1).

9. The carbon fiber composite material cowl forming die as claimed in claim 8, wherein: the external pressing frame (B-5) and the base mold (B-3) are both made of metal materials.

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