CN112644111B - Composite material plane fragile cover with mooring function and preparation method thereof - Google Patents

Composite material plane fragile cover with mooring function and preparation method thereof Download PDF

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Publication number
CN112644111B
CN112644111B CN202011446979.7A CN202011446979A CN112644111B CN 112644111 B CN112644111 B CN 112644111B CN 202011446979 A CN202011446979 A CN 202011446979A CN 112644111 B CN112644111 B CN 112644111B
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layer
cutting
weak area
edge
mooring
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CN112644111A (en
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范棋鑫
徐澧明
蔡登安
贾米芝
王坤
周光明
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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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
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/36—Layered products comprising a layer of synthetic resin comprising polyesters
    • 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
    • B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
    • 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
    • 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
    • B32B38/0004—Cutting, tearing or severing, e.g. bursting; Cutter details
    • 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
    • B32B38/08—Impregnating
    • 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
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/12—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
    • 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
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/077—Doors or covers for launching tubes
    • 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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass fibres
    • 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
    • B32B2571/00—Protective equipment

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

The invention discloses a composite material plane fragile cover with a mooring function and a preparation method thereof, belonging to the technical field of missile launching and protection, wherein the fragile cover comprises: the flange frame, the body sub-valve, the split weak area and the edge weak area; the fiber cloth in the split weak area is cut discontinuously; the edge weak area comprises a bottom layer, a cutting layer and a mooring layer; the fragile cover of the invention is used for manufacturing the defect of the split weak area in a discontinuous cutting mode, so that the fragile cover is split along a preset track when the warhead is burst; the invention discloses a fragile cover with a compact structure, which is characterized in that the defect of a weak area at the edge is made in a prefabricated defect mode, a flexible mooring layer structure is attached, the weak area at the edge after being burst is bent along a preset defect, and a sub-valve of a body of the fragile cover can be moored on a launching box without a throwing body.

Description

Composite material plane fragile cover with mooring function and preparation method thereof
Technical Field
The invention relates to a composite material plane fragile cover with a mooring function and a preparation method thereof, belonging to the technical field of missile launching and protection.
Background
The design of the missile launching box cover is one of important factors influencing the quick response capability of the missile, certain inert gas is filled in the missile launching box to prevent warhead electronic components from being corroded when the missile is stored, and the box cover needs to keep air tightness under certain pressure difference; and when the missile is launched, the requirement of meeting the rapid launching condition is met. Most of traditional missile launching box covers are metal covers, the opening mode adopts mechanical opening or explosive bolt opening covers (see detail U.S. Pat. No. 390006, 1976; U.S. Pat. No. 4333381,1982), and the manufacturing materials are metals. The metal cover is large in general quality, the whole quality is increased, a special transmission mechanism and a servo control mechanism are needed, faults are prone to occurring after long-term storage, and the two cover opening modes have many problems, such as long opening time of a mechanical cover, high maintenance cost of a blasting cover, complex maintenance and the like.
The composite material has the advantages of light weight, high strength, good corrosion resistance, strong designability and the like, and is widely applied to the fields of aerospace, vehicles, medical treatment and the like. The missile launching box cover prepared from the composite material can well solve the problems of large mass, long reaction time, high maintenance cost and the like of the traditional missile launching box cover.
In order to improve the missile launching efficiency and meet the requirement of rapid combat of troops, other scholars have studied domestically. An integral burst type composite material film cover (see CN 1844839A,2006) in China is characterized in that the film cover is impacted by airflow generated by an engine before missile launching, and is integrally destroyed in a preset track. The domestic composite material fragile cover is directionally thrown out (see CN 104864773A,2015 for details), and the fragile cover throwing body realizes the directional throwing under the impact of airflow by arranging a separation area and a connection area. The two kinds of domestic breakable covers all need to cut the lid after the solidification earlier and glue again to glue the department and paste the fibre cloth reinforcement, the flow is complicated, and the quality is difficult to handle the accuse. The frangible cover breaks the projectile and may interfere with the operator and other equipment.
Disclosure of Invention
The invention discloses a composite material plane fragile cover with a mooring function, aiming at the problems in the prior art, the invention combines the preset defect design and the intermittent cutting type preset defect design, and can adapt to different emission conditions by adjusting the number of cutting layers, the layering mode and the like, thereby being a novel fragile cover with compact structure and wide applicability.
The invention is realized by the following steps:
a composite material plane fragile cover with a mooring function comprises a flange frame and a body sub-flap, wherein the body sub-flap is divided into a plurality of flaps by taking the circle center of the body sub-flap as the midpoint, and each flap is a split weak area; the middle connecting area between the flange frame and the body sub-valve is an edge weak area; the split weak area adopts an intermittent cutting type preset defect design, and the method specifically comprises the following steps: the split weak area is cut discontinuously along the dividing line between the sub-lobes of the body by taking the circle center of the split weak area as the center, and fiber connection is reserved and resin glue is used for filling during cutting; the edge weak area is designed for presetting defects, and specifically, the edge weak area sequentially comprises a bottom layer, a cutting layer and a mooring layer from the bottom to the top of the cover body; the bottom layer is designed to be free of defects; the cutting layer is cut along the edge cutting track in the longitudinal direction; the mooring layer is laid on the cutting layer, is not cut and is not dipped in glue to keep flexibility.
The weak area of the edge of the fragile cover adopts a preset defect design. The edge weak area comprises a bottom layer, a cutting layer and a mooring layer, wherein the cutting layer and the mooring layer are glued after cutting, the bottom layer can guarantee air tightness, the cutting layer guarantees proper strength of the edge weak area, the body sub-petals can be bent after being broken, and the mooring layer guarantees that the body sub-petals do not fly out after being broken.
The invention makes the weak area by the fiber cloth step-type cutting mode and keeps flexible connection by the mooring layer, thus the fragile cover has good air tightness, and the body sub-flap can be kept moored on the missile launching box after the fragile cover is burst, and no interference of the throwing object to personnel and equipment exists.
Furthermore, breakable lid has the difference of bottom surface and top surface, and the face that has the mooring layer is the top surface, and when the installation, the bottom surface of breakable lid is towards the launching tube in, the top surface is towards the launching tube outside to smooth bursting when guaranteeing the guided missile transmission, body lobe passes through the mooring layer after bursting and connects on the transmission case. In the process of bursting the fragile cover, one surface with the tying layer faces outwards, when the fragile cover is jacked, the body sub-valve is split along the preset defect track of the split weak area, the edge weak area is broken along the preset defect, and the tying layer can still be connected to connect the flange frame and the body sub-valve; when the outward movement of the top of the fragile cover is continued, the mooring layer of the fragile cover is bent, and the fragile cover is completely damaged.
Furthermore, the upper surfaces of the flange frame and the body sub-petals are also provided with an enhancement layer; the upper surface of the edge weak area is not provided with a reinforced layer. The enhancement layer contains one or more layers of fiber cloth, is the topmost layer structure of body sub-lamella and flange frame, prevents that layer-by-layer is peeled off between captive layer and body sub-lamella when the warhead bursts.
Furthermore, the flange frame, the body sub-lobe and the edge weak area, namely the frangible cover of the invention, are made of high-strength glass fiber bidirectional plain cloth reinforced epoxy resin composite materials, wherein the mooring layer of the edge weak area is not dipped with glue, the composite material is formed by curing and molding the high-strength glass fiber bidirectional plain cloth by taking epoxy resin glue as a matrix, and the layering mode is [ (0/90)/(+/-45)]n. By adopting the layering sequence, the overall structure of the fragile cover can obtain the performance characteristic of quasi isotropy, so that the uniform and stable bearing performance of the weak area can be obtained. After the split weak area is cut discontinuously, filling the split weak area with epoxy resin glue;
the uppermost mooring layer at the edge weak area uses high-strength glass fiber bidirectional plain cloth without gum dipping treatment, can keep flexible connection, can guarantee the body sub-valve to be moored on the launching box after bursting, and does not cause influence on personnel and equipment by thrown objects.
Furthermore, the cutting layer is cut off along the edge cutting track in the longitudinal direction, and the longitudinal position of the cutting layer is enhanced by dipping glue to form adhesive joint.
The invention also discloses a preparation method of the composite material plane fragile cover with the mooring function, which is characterized by comprising the following specific steps of:
1) cutting out high-strength glass fiber bidirectional plain cloth with required size and quantity;
2) cleaning a mould, preparing a rubber pad, and sticking polyester fragile plastic paper on the rubber pad;
3) preparing epoxy resin;
4) preparing two polyester fragile plastic papers, etching the outline of the edge weak area on the polyester fragile plastic papers, and cutting the polyester fragile plastic papers along the outline for standby;
5) laying cutting layer parts on the rubber mat according to a set laying sequence, laying layer by layer and dipping;
6) cutting the cutting layer part according to an edge cutting track, supplementing glue along the cutting track after cutting, covering plastic paper, extruding redundant glue solution by using a compression roller, and removing the plastic paper;
7) laying bottom layer fiber cloth on the part of the cutting layer, and dipping the fiber cloth in glue;
8) turning over the paved cutting layer and the bottom layer together by using a cover plate die to expose the cutting layer on the top;
9) laying a layer of bidirectional plain cloth on the cutting layer, pressing the prepared outline plastic paper of the edge weak area on the cutting layer, aligning the circle center of the outline plastic paper to the circle center of the concentric circle, uniformly dipping glue outside the plastic paper, keeping the plain cloth at the pressed part of the plastic paper not dipped with glue, and manufacturing a glue-dipping mooring layer;
10) taking down the outline plastic paper, taking another piece of bidirectional plain cloth, cutting along the outline plastic paper to obtain round plain cloth with the size of a body, plain cloth with the shape of a weak area at the edge and the remaining plain cloth at the outer side, discarding the plain cloth with the shape of the weak area at the edge, and reserving the other two pieces for later use;
11) laying two pieces of plain cloth obtained by cutting on the mooring layer, aligning the centers of the concentric circles, and infiltrating resin glue to prepare a reinforcing layer;
12) scribing and cutting the laid bottom layer, the cutting layer and the reinforcing layer along the flange frame, and discarding the outer part of the flange frame;
13) cutting residual fiber cloth on the outer side part of the flange frame, and performing discontinuous cutting along the body sub-segment sectioning lines, and performing glue filling and reinforcing along the cutting part;
14) covering the mold, and curing at room temperature;
15) heat treatment, cooling and demoulding;
16) cutting, grinding and polishing, and finishing the manufacture of the fragile cover.
Further, the fragile cover cutting layer is cut off according to an edge cutting track before the fiber cloth is not cured after being dipped; the mooring layer is not dipped in glue during the manufacturing process; and the sectioning weak area is cut discontinuously after gum dipping.
The beneficial effects of the invention and the prior art are as follows:
the fragile cover of the invention is used for manufacturing the defect of the split weak area in a discontinuous cutting mode, so that the fragile cover is split along a preset track when the warhead is burst; the defect of the edge weak area is made in a prefabricated defect mode, a flexible mooring layer structure is attached, so that the edge weak area after being burst is bent along the preset defect, and the sub-valve of the fragile cover body can be moored on the launching box without a throwing body;
the invention designs a composite material plane fragile cover with a mooring function, wherein the fragile cover is split along a split weak area track when a warhead is burst, a body sub-lobe is bent along an edge weak area step cutting track under the action of the warhead, and is connected to a missile launching box through a mooring layer; the structure is compact, the designability is strong, the mechanical property of the weak area is controllable, the process flow is simple, and the quality is stable and controllable;
the invention can adjust the layering mode and the layer number and the sectioning weak area cutting mode according to the launching conditions, so that the fragile cover is suitable for different launching conditions. The preparation method disclosed by the invention is simple in preparation process, stable in quality and compact in structure, and solves the problems of complex flow, difficulty in controlling quality stability and projectile interference in the prior art.
Drawings
FIG. 1 is a top plan view of a composite planar frangible cover with captive functionality according to the present invention;
FIG. 2 is a schematic view of a thin edge area of a frangible cover according to the present invention;
FIG. 3 is a schematic view of the valve weakened area in the frangible cover of the present invention;
FIG. 4 is a schematic view of the bending of the edge weakened area in the frangible cover of the present invention;
FIG. 5 is a schematic cross-sectional view of the frangible cover of the present invention taken along the area of severance weakness;
FIG. 6 shows the installation of a composite planar frangible cover with a captive function in a burst test according to the present invention;
1-flange frame, 2-body sub-lobe, 3-split weak area, 4-edge weak area, 5-mooring layer, 6-bottom layer, 7-cutting layer, 8-edge cutting track, and 9-reinforcing layer.
Detailed Description
In order to make the objects, technical solutions and effects of the present invention more clear, the present invention is further described in detail by the following examples. It should be noted that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The whole broken-type fragile cover of ladder cutting plane in this implementation, its preparation process includes following steps:
1) cutting 9 pieces of 400mm high-strength bidirectional glass fiber cloth;
2) cleaning a mould, preparing a rubber pad, and sticking polyester fragile plastic paper on the rubber pad;
3) scribing a mold with a weak edge area by using polyester fragile plastic paper, and preparing epoxy resin;
4) making a cutting layer, taking 6 pieces of cloth according to [ (0/90)/(+ -45)]3Sequentially laying and gumming layer by layer;
5) sticking polyester fragile plastic paper on the cutting layer, engraving a circular cutting track with the diameter of 290mm on the plastic paper, and cutting off the cutting layer along the cutting track;
6) manufacturing a bottom layer, laying a layer of fiber cloth on the cutting layer, and dipping the fiber cloth in glue;
7) turning over the paved cutting layer and the bottom layer together by using a cover plate die to expose the cutting layer on the top;
8) laying a layer of fiber cloth on the cutting layer, pressing the fiber cloth by using the edge weak area die manufactured in the step 3), dipping the other parts of the fiber cloth with glue, and keeping the edge weak area not dipped with glue;
9) taking another piece of glass fiber cloth, cutting along the edge weak area die, only reserving the body part and the outer part, and abandoning the edge weak area part;
10) laying the cut outer side part and the cut body part of the step 9) on a fragile cover, centering, brushing glue, and preparing a reinforcing layer;
11) cutting the laid bottom layer, the cutting layer and the reinforcing layer along the outer edge of the flange frame by scribing, and discarding the outer part of the flange frame;
12) intermittently cutting the fiber cloth along the track of the split weak area, and reinforcing the glue at the cutting position;
13) covering the mold, and curing at room temperature;
14) heat treatment, cooling and demoulding;
15) cutting, grinding and polishing, and finishing the manufacture of the fragile cover.
A composite material plane fragile cover with a mooring function prepared by the method is shown in figures 1-3; the fragile cover comprises a flange frame 1, a body sub-valve 2, a split weak area 3 between the body sub-valves 2 and an edge weak area 4 between the flange frame 1 and the body sub-valve 2, wherein the layer structure design at the edge weak area 4 comprises the laying of a mooring layer 5 and the preset defect design; the split weak area 3 adopts an intermittent cutting type preset defect design; the fragile cover edge weak area 4 sequentially comprises a bottom layer 6, a cutting layer 7 and a mooring layer 5 from the bottom to the top of the cover body; the cutting layer 7 is cut along the edge cutting track 8, and the bottom layer 6 is designed to be free of defects; the mooring layer 5 is laid on the cutting layer 7; the mooring layer 5 keeps flexibility without gum dipping; the edge cutting track 8 is within the edge weakening zone 4; the split weak area 3 is cut discontinuously along the dividing line between the body sub-splits 2, namely a small amount of fiber connection is reserved during cutting, and then resin glue is used for filling. The frangible cover comprises a reinforcing layer 9 on the body sub-flap 2 and the flange frame 1, distinct from the edge weakened area 4.
A composite planar frangible cover with a captive function prepared by the above method was mounted in a burst test as shown in FIG. 6, with the side having the captive layer facing the outside of the barrel. As shown in fig. 4 to 5, when the warhead pushes against the frangible cover under the action of the actuator cylinder, the frangible cover is damaged, the body sub-flap 2 is split along the preset defect track of the split weak area 3, the edge weak area 4 is broken along the preset defect, and the surface mooring layer 5 can still be connected to connect the body sub-flap 2 and the flange frame 1. When the warhead continues to move outwards, the fragile cover mooring layer 5 is bent, and the missile launching track is given way.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that modifications can be made by those skilled in the art without departing from the principle of the present invention, and these modifications should also be construed as the protection scope of the present invention.

Claims (7)

1. The composite material plane fragile cover with the mooring function is characterized by comprising a flange frame (1) and a body sub-flap (2), wherein the body sub-flap (2) is divided into a plurality of flaps by taking the circle center of the body sub-flap (2) as the midpoint, and each flap is a split weak area (3); the middle connecting area between the flange frame (1) and the body sub-valve (2) is an edge weak area (4);
the split weak area (3) adopts an intermittent cutting type preset defect design, and the method specifically comprises the following steps: the split weak area (3) is cut discontinuously along the dividing line between the body sub-petals (2) by taking the circle center of the split weak area as the center, and part of fiber connection is reserved during cutting and is filled with resin adhesive;
the edge weak area (4) is designed for presetting defects, and specifically, the edge weak area (4) sequentially comprises a bottom layer (6), a cutting layer (7) and a mooring layer (5) from the bottom to the top of a cover body; the bottom layer (6) is designed to be free of defects; the cutting layer (7) is cut off along an edge cutting track (8) in the longitudinal direction; the mooring layer (5) is laid on the cutting layer (7), and the mooring layer (5) keeps flexibility without cutting and gum dipping.
2. A composite planar frangible cover with captive capability according to claim 1 wherein the frangible cover has a bottom surface and a top surface, the surface with the captive layer being the top surface, the surface with the captive layer (5) facing outwards during the bursting process, the body sub-flap (2) being split along the pre-set defect path at the split weakened zone (3) and the marginal weakened zone (4) breaking along the pre-set defect while the captive layer (5) remains attached, connecting the flange frame (1) and the body sub-flap (2); when the outward movement of the top of the fragile cover is continued, the mooring layer (5) of the fragile cover is bent, and the fragile cover is completely broken.
3. The composite material plane fragile cover with mooring function according to claim 1, characterized in that the flange frame (1) and the upper surface of the body sub-flap (2) are further provided with a reinforcement layer (9), and the reinforcement layer comprises one or more layers of fiber cloth; the upper surface of the edge weak area (4) is not provided with a reinforced layer (9).
4. The composite material plane breakable cover with mooring function according to claim 1, wherein the flange frame (1), the body sub-flaps (2) and the edge weak area (4) are made of high-strength glass fiber bidirectional plain cloth reinforced epoxy resin matrix composite, the composite material is made by curing and molding the high-strength glass fiber bidirectional plain cloth by taking epoxy resin glue as a matrix, and the layering mode is [ (0/90)/(± 45)]n(ii) a The split weak area (3) is filled with epoxy resin glue after being cut discontinuously; the uppermost mooring layer (5) at the edge weak area (4) uses high-strength glass fiber bidirectional plain cloth without gum dipping treatment.
5. The composite material plane fragile cover with mooring function according to claim 1, characterized in that the cutting layer (7) is cut along the edge cutting track (8) in the longitudinal direction, and the glue is enhanced in the longitudinal direction to form a glue joint.
6. A preparation method of a composite material plane fragile cover with a mooring function is characterized by comprising the following specific steps:
1) cutting out high-strength glass fiber bidirectional plain cloth with required size and quantity;
2) cleaning a mould, preparing a rubber pad, and sticking polyester fragile plastic paper on the rubber pad;
3) preparing epoxy resin;
4) preparing two polyester fragile plastic papers, etching the outline of the edge weak area on the polyester fragile plastic papers, and cutting the polyester fragile plastic papers along the outline for standby;
5) laying cutting layer parts on the rubber mat according to a set laying sequence, laying layer by layer and dipping;
6) cutting the cutting layer part according to an edge cutting track, supplementing glue along the cutting track after cutting, covering plastic paper, extruding redundant glue solution by using a compression roller, and removing the plastic paper;
7) laying bottom layer fiber cloth on the part of the cutting layer, and dipping the fiber cloth in glue;
8) turning over the paved cutting layer and the bottom layer together by using a cover plate die to expose the cutting layer on the top;
9) laying a layer of bidirectional plain cloth on the cutting layer, pressing the prepared outline plastic paper of the edge weak area on the cutting layer, aligning the circle center of the outline plastic paper to the circle center of the concentric circle, uniformly dipping glue outside the plastic paper, keeping the plain cloth at the pressed part of the plastic paper not dipped with glue, and manufacturing a glue-dipping mooring layer;
10) taking down the outline plastic paper, taking another piece of bidirectional plain cloth, cutting along the outline plastic paper to obtain round plain cloth with the size of a body, plain cloth with the shape of a weak area at the edge and the remaining plain cloth at the outer side, discarding the plain cloth with the shape of the weak area at the edge, and reserving the other two pieces for later use;
11) laying two pieces of plain cloth obtained by cutting on the mooring layer, aligning the centers of the concentric circles, and infiltrating resin glue to prepare a reinforcing layer;
12) scribing and cutting the laid bottom layer, the cutting layer and the reinforcing layer along the flange frame, and discarding the outer part of the flange frame;
13) cutting residual fiber cloth on the outer side part of the flange frame, and performing discontinuous cutting along the body sub-segment sectioning lines, and performing glue filling and reinforcing along the cutting part;
14) covering the mold, and curing at room temperature;
15) heat treatment, cooling and demoulding;
16) cutting, grinding and polishing, and finishing the manufacture of the fragile cover.
7. The method for preparing the composite planar fragile cover with the mooring function according to the claim 6, wherein the fragile cover cutting layer is cut according to the edge cutting track (8) before the fiber cloth is uncured after gum dipping; the mooring layer (5) is not dipped in glue during the manufacturing process; the sectioning weak area (3) is cut discontinuously after gum dipping.
CN202011446979.7A 2020-12-09 2020-12-09 Composite material plane fragile cover with mooring function and preparation method thereof Active CN112644111B (en)

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CN113819802B (en) * 2021-09-06 2022-10-21 南京航空航天大学 Composite material frangible cover with automatic reset function and preparation method thereof
CN114184132B (en) * 2021-12-09 2024-01-16 安徽华烨特种材料有限公司 Method for identifying joint of impregnated reinforced material
CN115014125B (en) * 2022-06-17 2023-07-04 北京新风航天装备有限公司 Broken carbon fiber composite fragile film cover according to preset path
CN117989921B (en) * 2024-04-03 2024-06-25 四川爱思达航天科技有限公司 Fragile cover for differential bearing of internal and external pressure

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