CN113819802B - Composite material frangible cover with automatic reset function and preparation method thereof - Google Patents
Composite material frangible cover with automatic reset function and preparation method thereof Download PDFInfo
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- CN113819802B CN113819802B CN202111042851.9A CN202111042851A CN113819802B CN 113819802 B CN113819802 B CN 113819802B CN 202111042851 A CN202111042851 A CN 202111042851A CN 113819802 B CN113819802 B CN 113819802B
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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
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/077—Doors or covers for launching tubes
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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
- B32B25/00—Layered products comprising a layer of natural or synthetic rubber
- B32B25/04—Layered products comprising a layer of natural or synthetic rubber comprising rubber as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B25/08—Layered products comprising a layer of natural or synthetic rubber comprising rubber as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
-
- 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
- B32B25/00—Layered products comprising a layer of natural or synthetic rubber
- B32B25/10—Layered products comprising a layer of natural or synthetic rubber 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
- B32B25/00—Layered products comprising a layer of natural or synthetic rubber
- B32B25/20—Layered products comprising a layer of natural or synthetic rubber comprising silicone rubber
-
- 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
- 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
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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
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a composite material fragile cover with an automatic reset function and a preparation method thereof, belonging to the technical field of missile launching and protection, wherein the fragile cover comprises the following components: the flange frame, the weak area, the sub-cover and the functional area; the weak area is an area which partially cuts off warp yarns or weft yarns according to the bearing requirement; the functional area comprises a bearing layer and a functional layer, wherein the bearing layer bears load, and the functional layer enables the sub-cover to have the functions of folding, large deformation, falling prevention and rebound resetting. According to the novel fragile cover with the functions of falling prevention and automatic reset, the sub cover can be folded and greatly deformed in the function area to give way to the advancing channel of the missile when the missile is launched, and can automatically rebound and reset after the missile body is discharged from the barrel, so that the novel fragile cover is compact in structure, has the functions of falling prevention and automatic reset, and is widely suitable for launching devices with strict requirements on equipment space.
Description
Technical Field
The invention relates to a composite material frangible cover with an automatic reset 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. The traditional missile launching box cover is mostly a metal cover, the cover is opened by adopting a mechanical opening mode or an explosion bolt, and the traditional missile launching box cover is made of metal. 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 made of 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 in China. The integral burst type composite material film cover in China is characterized in that airflow generated by an engine before missile launching is used for impacting the film cover, and the film cover is integrally destroyed in a preset track. According to the domestic composite material fragile cover capable of being directionally thrown, the separation area and the connection area are arranged, so that the fragile cover throwing body can be directionally thrown under the impact of airflow. Above two kinds of internal breakable covers all have the object to throw out, probably cause the damage to operating personnel and other equipment, and this kind of breakable cover has very big limitation to the application scene that the equipment space has strict requirement.
Disclosure of Invention
The invention discloses a composite material fragile cover with an automatic reset function and a preparation method thereof aiming at the problems in the prior art, wherein the fragile cover comprises the following components: the flange frame, the weak area, the sub-cover and the functional area; the weak area is an area for partially cutting off warp yarns or weft yarns according to the bearing requirement; the functional area comprises a bearing layer and a functional layer, wherein the bearing layer bears load, and the functional layer enables the sub-cover to have the functions of folding and large deformation, falling prevention and rebound resetting, so that the defects in the prior art are overcome.
The invention is realized in the following way:
the composite material fragile cover with the automatic reset function comprises a flange frame and a sub-cover in the middle area of the flange frame, and is characterized in that the joint of the flange frame and the sub-cover is quadrilateral, wherein three sides are weak areas, and one side is a functional area; the weak area is prepared by cutting off the fiber bundles in the layer, and the strength of the weak area is controlled by controlling the layer number and the number of the weak area, so that the weak area can not be damaged under a certain range of loads and can be damaged under a specific load.
The functional area comprises a bearing layer and a functional layer, wherein the bearing layer comprises prefabricated defects; defects are prefabricated in the bearing layer in a mode of cutting off fiber bundles in the layers, so that the bearing layer is damaged under a specific load, and the rigidity reduction of the functional area is realized; when the functional layer is designed, the rigidity is small, and the strength is moderate, so that the functions of falling prevention and automatic reset are realized.
The functional layer comprises an isolation layer, a rigid connecting layer, a flexible filling layer and a skin layer from bottom to top in sequence; the isolation layer is a layer of demoulding cloth or a polyester film, the rigid connection layer is one or more layers of impregnated fiber cloth, the flexible filling layer is filled silicon rubber, and the skin layer is one or more layers of fiber cloth layers covered on the flexible filling layer. The demolding cloth enables the functional layer and the bearing layer not to be adhered, and ensures that enough geometric space is available to realize large bending deformation; the two layers of impregnated fiber cloth have smaller rigidity but larger strength, and the sub-cover is connected with the flange to realize the anti-falling function; the silica gel layer further realizes sealing and increases the resilience rigidity; the outer skin protects the silica gel layer from external damage.
The breakable lid has the difference of bottom surface and top surface, and the face that the functional layer corresponds in the functional area is the top surface, and when the installation, the bottom surface of breakable lid is towards the launching tube in, the top surface is outside the launching tube to smooth bursting when guaranteeing the guided missile transmission, when the guided missile popped out the section of thick bamboo, the rotation of subshell is uncapped, after the guided missile goes out a section of thick bamboo, subshell automatic re-setting.
When the missile is launched, under the bursting action of the warhead, the bearing layers of the weak area and the functional area are damaged, the functional layer of the functional area is bent and greatly deformed, and the sub-cover is opened by rotating by taking the central line of the functional area as an axis; after the missile is taken out of the barrel, the sub-cover automatically resets by means of the residual rigidity (functional layer rigidity) of the functional area, and the functions of falling prevention and automatic cover closing after launching are realized. The frangible cover adopts the material of high-strength glass fiber bidirectional plain cloth reinforced epoxy resin composite material, and the layering mode is [ (0/90)/(+/-45)] n The layering sequence can enable the integral structure of the fragile cover to obtain the performance characteristic of quasi-isotropy, so that the uniform and stable bearing performance of a weak area is obtained.
Further, overlooking the whole fragile cover, and setting the central line of the functional area as the central line of the functional area; the frangible cover is fractured in the weak area under the action of the bursting force of the missile, the rigidity of the functional area is reduced to generate bending large deformation, the sub-cover rotates by taking the central line of the functional area as an axis to give way for the projectile body to advance, and the sub-cover automatically rebounds and resets by virtue of the residual rigidity of the functional area after the acting force of the projectile body disappears to close the launch canister.
Further, under the bursting force of the elastomer, the bearing layer is broken at the prefabricated defect part, so that the rigidity reduction of the functional area is realized; the functional layer is designed into a layer with moderate rigidity and relatively large strength, and the rigidity of the functional layer is lower than that of the flange, the sub-cover and the bearing layer so as to realize the functions of large bending deformation, falling prevention and automatic rebound resetting.
Furthermore, the weak area and the prefabricated defects of the bearing layer are realized by cutting off the corresponding number of layers and the number of warps or wefts.
Furthermore, the strength of the bearing layer in the weak area and the functional area is adjusted by the number of cut warps or wefts, and the rigidity and the strength of the functional layer in the functional area are adjusted by the thickness of the flexible filling layer and the number and the type of the impregnated fiber cloth in the rigid connecting layer.
The invention also discloses a preparation method of the composite material fragile cover with the automatic reset 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 plastic paper on the rubber pad;
3) Laying a bearing layer laying layer and a functional layer laying layer with required thickness on the rubber pad according to a preset laying sequence, and drawing the position of a weak area, the outline and the central line of the functional area on the two plates respectively; setting the bearing layer laying layer as a C plate; setting the functional layer laying layer as a G plate;
4) Cutting off a preset number of layers and a preset number of yarns at the central line position of the C plate functional area, and attaching a layer of demolding cloth or a polyester film in the outline of the functional area;
5) Digging out fiber cloth with the thickness of the flexible filling layer in the functional area outline on the G plate to form a groove filled with silicon rubber;
6) Pressing the two plates to form a plate, namely an A plate, by covering the G plate on the C plate and aligning by taking the position of the weak area as a standard;
7) Cutting off a preset number of layers and a preset number of yarns at the weak area of the A plate, and filling liquid silicon rubber in the groove of the functional area;
8) After curing for 3 hours at normal temperature, paving fiber cloth with required number in the subshells and the functional area to isolate the silicon rubber from air;
9) Curing at normal temperature for 24 hours, and then heating to 50 ℃ for curing for 5 hours;
10 Cutting burrs, drilling holes, polishing and finishing.
The beneficial effects of the invention and the prior art are as follows:
the composite material breakable cover with the automatic resetting function has the functions of preventing falling and automatically closing the cover. The breakable cover has the functions of falling prevention and automatic rebound resetting, has no throwing body, overcomes the defect of potential danger to surrounding personnel and equipment, greatly saves the space required by the equipment due to the automatic rebound function of the sub-cover, and is widely applied to application scenes with strict requirements on safety and space.
According to the novel fragile cover with the functions of falling prevention and automatic reset, the sub cover can be folded and greatly deformed in the function area to give way to the advancing channel of the missile when the missile is launched, and can automatically rebound and reset after the missile body is discharged from the barrel, so that the novel fragile cover is compact in structure, has the functions of falling prevention and automatic reset, and is widely suitable for launching devices with strict requirements on equipment space.
Drawings
FIG. 1 is a top view of a composite frangible cover with automatic reset feature of the present invention;
FIG. 2 is a schematic view of a functional area of the frangible cover of the present invention;
FIG. 3 is a schematic view of the functional layer bending of the functional region in the frangible cover of the present invention;
FIG. 4 is a schematic view of the frangible cover of the present invention being broken;
the method comprises the following steps of 1-a flange frame, 2-a weak area, 3-a sub-cover, 4-a functional area, 5-a functional area central line, 6-a prefabricated defect, 7-an isolation layer, 8-a rigid connection layer, 9-a flexible filling layer and 10-a skin 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.
In this implementation, a fragile lid of combined material who possesses automatic re-setting function, its preparation process includes the following step:
1) Cutting 17 layers of 400 x 400mm high-strength glass fiber bidirectional plain cloth;
2) Cleaning a mould, preparing a rubber pad, and sticking polyester plastic paper on the rubber pad;
3) Pressing [ (0/90)/(+ -45) on the rubber pad respectively] 4 Laying a bearing layer laying layer (C plate) and a functional layer laying layer (G plate) in sequence, and respectively drawing the position of a weak area, the outline and the central line of a functional area on the two plates, wherein the distance between the weak area and the edge of the plate is 50mm, the width of the functional area is 20mm, the length of the functional area is 310mm, and the distance between the middle of the functional area and the edge of the plate is 50mm;
4) Cutting off all yarns at the central line position of the C plate functional area, and attaching a layer of demolding cloth or a polyester film in the outline of the functional area;
5) Digging out the upper 6 layers of fiber cloth in the functional area outline on the G plate to form a groove filled with silicon rubber;
6) Overlaying the G plate on the C plate, aligning the G plate with the position of the weak area as a standard, and compacting the G plate and the C plate to form a plate (A plate);
7) Cutting off all yarns at the weak area of the A plate, and filling 703 silicon rubber in the groove of the functional area;
8) After curing for 3 hours at normal temperature, 1 layer of fiber cloth is laid in the subshells and the functional area to isolate the silicon rubber from air;
9) Curing at normal temperature for 24 hours, and then heating to 50 ℃ for curing for 5 hours;
10 Cutting burrs, drilling holes, polishing and finishing.
Fig. 1-3 show a composite material fragile cover with an automatic reset function prepared by the method of the present invention, the fragile cover of the present invention comprises a flange frame 1 and a sub-cover 3 in the middle area of the flange frame 1, and is characterized in that the joint of the flange frame 1 and the sub-cover 3 is quadrilateral, wherein three sides are weak areas 2, and one side is a functional area 4; the functional area 4 comprises a bearing layer and a functional layer, wherein the bearing layer is a plurality of prefabricated defects 6 vertical to the functional layer; the functional layer comprises an isolation layer 7, a rigid connecting layer 8, a flexible filling layer 9 and a skin layer 10 from bottom to top in sequence; the isolation layer 7 is a layer of demoulding cloth or a polyester film, the rigid connection layer 8 is a layer or a plurality of layers of impregnated fiber cloth, the flexible filling layer 9 is filled silicon rubber, and the skin layer 10 is a layer or a plurality of layers of fiber cloth layers covered on the flexible filling layer 9.
Under the action of the bursting force of the missile, the weak area 2 is broken, the rigidity of the functional area 4 is reduced, large bending deformation is generated, the sub-cover 3 rotates by taking the central line 5 of the functional area 4 as an axis to give way for the projectile body, and after the acting force of the projectile body disappears, the sub-cover 3 automatically rebounds and resets by virtue of the residual rigidity of the functional area 4, and the launching tube is closed. The functional area 4 is divided into a bearing layer and a functional layer, wherein the bearing layer is provided with a prefabricated defect 6, and the bearing layer is broken at the prefabricated defect 6 under the bursting force of the projectile body, so that the rigidity reduction of the functional area is realized; the functional layer is designed into a layer with moderate rigidity and relatively large strength so as to realize the functions of large bending deformation, falling prevention and automatic rebound resetting.
The composite material frangible cover with the automatic resetting function prepared by the method is arranged in a bursting test mode as shown in fig. 4, wherein one side with the functional layer faces the outside of the launching cylinder. When the warhead pushes against the fragile cover under the action of the actuating cylinder, the weak area of the fragile cover is broken, the bearing layer of the functional area is damaged, the rigidity of the functional area is reduced, the functional layer is bent and greatly deformed, and the sub-cover is opened in a rotating mode. When the bullet body goes out of the cylinder, the sub-cover rebounds to close the cover under the rigid action of the functional layer.
The foregoing is illustrative of the present invention and it will be appreciated by those skilled in the art that changes may be made in this embodiment without departing from the principles of the invention and that such changes are to be considered within the scope of the invention.
Claims (5)
1. The composite material fragile cover with the automatic reset function comprises a flange frame (1) and a sub-cover (3) in the middle area of the flange frame (1), and is characterized in that the joint of the flange frame (1) and the sub-cover (3) is in a quadrilateral shape, wherein three edges are weak areas (2), and one edge is a functional area (4);
the functional area (4) comprises a bearing layer and a functional layer, wherein the bearing layer comprises a prefabricated defect (6);
the functional layer comprises an isolation layer (7), a rigid connecting layer (8), a flexible filling layer (9) and a skin layer (10) from bottom to top in sequence; the isolation layer (7) is a layer of demoulding cloth or a polyester film, the rigid connection layer (8) is one or more layers of impregnated fiber cloth, the flexible filling layer (9) is filled silicon rubber, and the skin layer (10) is one or more layers of fiber cloth covered on the flexible filling layer (9);
overlooking the whole fragile cover, and setting the midline of the functional area (4) as a functional area midline (5); the fragile cover is provided with a bottom surface and a top surface, the surface corresponding to the functional layer in the functional area is the top surface, when the fragile cover is installed, the bottom surface of the fragile cover faces the inside of the launching tube, and the top surface of the fragile cover faces the outside of the launching tube; the fragile cover is broken in the weak area (2) under the action of the bursting force of the missile, the rigidity of the functional area (4) is reduced, the fragile cover is bent and deformed greatly, the sub-cover (3) rotates by taking the central line (5) of the functional area (4) as an axis to give way for the missile, and after the acting force of the missile disappears, the sub-cover (3) automatically rebounds and resets by virtue of the residual rigidity of the functional area (4), and the launching barrel is closed; under the bursting force of the missile, the bearing layer is broken at the prefabricated defect (6) to realize the rigidity reduction of the functional area; and the rigidity of the functional layer is respectively lower than that of the flange, the sub-cover and the bearing layer, so that the functions of large bending deformation, falling prevention and automatic rebound resetting of the functional layer are realized.
2. The composite material frangible cover with automatic reset function according to claim 1, characterized in that the weak area (2) and the bearing layer prefabrication defect (6) are realized by cutting off corresponding number of layers and number of warps or wefts.
3. The composite material frangible cover with the automatic reset function according to claim 1, wherein the strength of the bearing layer in the weak area (2) and the functional area (4) is adjusted by the number of cut warps or wefts, and the rigidity and strength of the functional layer in the functional area (4) are adjusted by the thickness of the flexible filling layer (9) and the number and type of the impregnated fiber cloth in the rigid connecting layer (8).
4. The composite material frangible cover with automatic reset function of claim 1, wherein the frangible cover is made of high-strength glass fiber bidirectional plain cloth reinforced epoxy resin composite material, and the layering mode is [ (0/90)/(± 45)] n Quasi-isotropic layup.
5. The preparation method of the composite material frangible cover with the automatic resetting function according to claim 1 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 plastic paper on the rubber pad;
3) Laying a bearing layer laying layer and a functional layer laying layer with required thickness on the rubber pad according to a preset laying sequence, and drawing the position of a weak area, the outline and the central line of the functional area on the two plates respectively; setting the bearing layer laying layer as a C plate; setting the functional layer laying layer as a G plate;
4) Cutting off a preset number of layers and a preset number of yarns at the central line position of the C plate functional area, and attaching a layer of demoulding cloth or a polyester film in the outline of the functional area;
5) Digging out fiber cloth with the thickness of the flexible filling layer in the functional area outline on the G plate to form a groove filled with silicon rubber;
6) Pressing the two plates to form a plate, namely an A plate, by covering the G plate on the C plate and aligning by taking the position of the weak area as a standard;
7) Cutting off a preset number of layers and a preset number of yarns at the weak area of the A plate, and filling liquid silicon rubber in the groove of the functional area;
8) After curing for 3 hours at normal temperature, paving fiber cloth with required number in the subshells and the functional area to isolate the silicon rubber from air;
9) Curing at normal temperature for 24 hours, and then heating to 50 ℃ for curing for 5 hours;
10 Cutting burrs, drilling holes, polishing and finishing.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111042851.9A CN113819802B (en) | 2021-09-06 | 2021-09-06 | Composite material frangible cover with automatic reset function and preparation method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111042851.9A CN113819802B (en) | 2021-09-06 | 2021-09-06 | Composite material frangible cover with automatic reset function and preparation method thereof |
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| CN113819802A CN113819802A (en) | 2021-12-21 |
| CN113819802B true CN113819802B (en) | 2022-10-21 |
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| 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 |
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| CN104864773B (en) * | 2015-05-08 | 2016-08-24 | 南京航空航天大学 | Orient composite Fragile cap and preparation method thereof of dishing out |
| FR3053455B1 (en) * | 2016-07-01 | 2019-04-19 | Mbda France | FLEXIBLE OPENER FOR MISSILE CONTAINER |
| CN109631669B (en) * | 2018-12-21 | 2021-03-12 | 上海燕兴科技实业有限公司 | Fragile cover of launching box of guided missile analog launching system |
| CN111256536B (en) * | 2020-02-28 | 2021-06-22 | 南京航空航天大学 | Penetration cutting wire laying reinforced plane integral breaking type frangible cover and preparation method thereof |
| CN111322909B (en) * | 2020-03-03 | 2021-10-15 | 南京航空航天大学 | Integrally-broken-type frangible cover with stepped cutting plane and preparation method thereof |
| CN112644111B (en) * | 2020-12-09 | 2021-10-15 | 南京航空航天大学 | Composite material plane fragile cover with mooring function and preparation method thereof |
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