CN114018100A - Light aviation magazine and composite material for preparing same - Google Patents
Light aviation magazine and composite material for preparing same Download PDFInfo
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- CN114018100A CN114018100A CN202111283404.2A CN202111283404A CN114018100A CN 114018100 A CN114018100 A CN 114018100A CN 202111283404 A CN202111283404 A CN 202111283404A CN 114018100 A CN114018100 A CN 114018100A
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- 239000002131 composite material Substances 0.000 title claims abstract description 31
- 239000000463 material Substances 0.000 claims abstract description 32
- 238000003860 storage Methods 0.000 claims abstract description 23
- 229910052751 metal Inorganic materials 0.000 claims abstract description 12
- 239000002184 metal Substances 0.000 claims abstract description 12
- 238000003756 stirring Methods 0.000 claims description 43
- ZMXDDKWLCZADIW-UHFFFAOYSA-N N,N-Dimethylformamide Chemical compound CN(C)C=O ZMXDDKWLCZADIW-UHFFFAOYSA-N 0.000 claims description 37
- 239000000805 composite resin Substances 0.000 claims description 26
- 238000010438 heat treatment Methods 0.000 claims description 25
- WOCGGVRGNIEDSZ-UHFFFAOYSA-N 4-[2-(4-hydroxy-3-prop-2-enylphenyl)propan-2-yl]-2-prop-2-enylphenol Chemical compound C=1C=C(O)C(CC=C)=CC=1C(C)(C)C1=CC=C(O)C(CC=C)=C1 WOCGGVRGNIEDSZ-UHFFFAOYSA-N 0.000 claims description 20
- GPNNOCMCNFXRAO-UHFFFAOYSA-N 2-aminoterephthalic acid Chemical compound NC1=CC(C(O)=O)=CC=C1C(O)=O GPNNOCMCNFXRAO-UHFFFAOYSA-N 0.000 claims description 14
- JGDITNMASUZKPW-UHFFFAOYSA-K aluminium trichloride hexahydrate Chemical compound O.O.O.O.O.O.Cl[Al](Cl)Cl JGDITNMASUZKPW-UHFFFAOYSA-K 0.000 claims description 14
- 229940009861 aluminum chloride hexahydrate Drugs 0.000 claims description 13
- 238000006243 chemical reaction Methods 0.000 claims description 13
- 239000004643 cyanate ester Substances 0.000 claims description 13
- 229920005989 resin Polymers 0.000 claims description 13
- 239000011347 resin Substances 0.000 claims description 13
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 12
- 239000004734 Polyphenylene sulfide Substances 0.000 claims description 12
- 239000000835 fiber Substances 0.000 claims description 12
- 229910021392 nanocarbon Inorganic materials 0.000 claims description 12
- 229920000069 polyphenylene sulfide Polymers 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 7
- 230000004913 activation Effects 0.000 claims description 6
- 238000009835 boiling Methods 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 6
- 238000001914 filtration Methods 0.000 claims description 6
- 238000000465 moulding Methods 0.000 claims description 6
- 230000008569 process Effects 0.000 claims description 6
- 239000002994 raw material Substances 0.000 claims description 6
- 238000009849 vacuum degassing Methods 0.000 claims description 6
- 238000005406 washing Methods 0.000 claims description 6
- 238000004519 manufacturing process Methods 0.000 claims description 5
- 239000007769 metal material Substances 0.000 abstract description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 8
- 238000001514 detection method Methods 0.000 description 4
- 238000004132 cross linking Methods 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- CFQZKFWQLAHGSL-FNTYJUCDSA-N (3e,5e,7e,9e,11e,13e,15e,17e)-18-[(3e,5e,7e,9e,11e,13e,15e,17e)-18-[(3e,5e,7e,9e,11e,13e,15e)-octadeca-3,5,7,9,11,13,15,17-octaenoyl]oxyoctadeca-3,5,7,9,11,13,15,17-octaenoyl]oxyoctadeca-3,5,7,9,11,13,15,17-octaenoic acid Chemical compound OC(=O)C\C=C\C=C\C=C\C=C\C=C\C=C\C=C\C=C\OC(=O)C\C=C\C=C\C=C\C=C\C=C\C=C\C=C\C=C\OC(=O)C\C=C\C=C\C=C\C=C\C=C\C=C\C=C\C=C CFQZKFWQLAHGSL-FNTYJUCDSA-N 0.000 description 1
- 125000003903 2-propenyl group Chemical group [H]C([*])([H])C([H])=C([H])[H] 0.000 description 1
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- 238000007259 addition reaction Methods 0.000 description 1
- 125000003277 amino group Chemical group 0.000 description 1
- -1 anionic imide Chemical class 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 150000001993 dienes Chemical class 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 150000003949 imides Chemical class 0.000 description 1
- 239000003446 ligand Substances 0.000 description 1
- 238000011068 loading method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 125000002924 primary amino group Chemical group [H]N([H])* 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000013638 trimer Substances 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
- F42B12/70—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies for dispensing radar chaff or infrared material
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L79/00—Compositions of macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing nitrogen with or without oxygen or carbon only, not provided for in groups C08L61/00 - C08L77/00
- C08L79/04—Polycondensates having nitrogen-containing heterocyclic rings in the main chain; Polyhydrazides; Polyamide acids or similar polyimide precursors
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L79/00—Compositions of macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing nitrogen with or without oxygen or carbon only, not provided for in groups C08L61/00 - C08L77/00
- C08L79/04—Polycondensates having nitrogen-containing heterocyclic rings in the main chain; Polyhydrazides; Polyamide acids or similar polyimide precursors
- C08L79/08—Polyimides; Polyester-imides; Polyamide-imides; Polyamide acids or similar polyimide precursors
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L81/00—Compositions of macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing sulfur with or without nitrogen, oxygen or carbon only; Compositions of polysulfones; Compositions of derivatives of such polymers
- C08L81/02—Polythioethers; Polythioether-ethers
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L87/00—Compositions of unspecified macromolecular compounds, obtained otherwise than by polymerisation reactions only involving unsaturated carbon-to-carbon bonds
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A9/00—Feeding or loading of ammunition; Magazines; Guiding means for the extracting of cartridges
- F41A9/61—Magazines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
- F42B39/28—Ammunition racks, e.g. in vehicles
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K2201/00—Specific properties of additives
- C08K2201/011—Nanostructured additives
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Medicinal Chemistry (AREA)
- Health & Medical Sciences (AREA)
- Polymers & Plastics (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Combustion & Propulsion (AREA)
- Compositions Of Macromolecular Compounds (AREA)
- Reinforced Plastic Materials (AREA)
Abstract
The invention relates to a light aviation magazine and a composite material for preparing the same, which comprises support plates, storage units, magazines and a connecting plate, wherein the two support plates are oppositely arranged and fixedly arranged on the upper surface of a bottom plate; the special storage structure can meet the requirement of saving space, is convenient to take out and does not influence use, and the light aviation magazine is made of composite materials, has lighter weight and high strength compared with the traditional metal magazine body material, can meet the use requirement of the magazine, is not easy to corrode by air in a special environment, and is more durable compared with the traditional metal material.
Description
Technical Field
The invention belongs to the technical field of aviation materials, and particularly relates to a light aviation magazine and a composite material for preparing the same.
Background
The magazine belongs to the aeronautical component, the loading body of the airborne jamming bomb, and the magazine is an important component on armed helicopters and military aircrafts. At present, the helicopter is manufactured by adopting special alloy steel such as aluminum alloy, and has the main problems of heavy weight, poor corrosion resistance and short service life, and the helicopter cannot meet the use requirement of a helicopter. The weight of the metal magazine is large, so that the load and the endurance of the airplane are directly influenced, the manufacturing period is long, the production efficiency is low, the qualification rate is low, and the magazine occupies space, so that the space utilization rate of the airplane is greatly limited.
Therefore, the quality of the magazine is improved, the weight of the magazine is reduced, the volume is saved, and the requirement of the use of the airplane is met.
Disclosure of Invention
In order to solve the technical problems, the invention provides a light aviation magazine and a composite material for preparing the same.
The purpose of the invention can be realized by the following technical scheme:
a light aviation magazine comprises supporting plates, storage units, magazine bodies and a connecting plate, wherein the two supporting plates are oppositely arranged and fixedly mounted on the upper surface of a bottom plate, a plurality of storage units are mounted in each supporting plate, the magazine bodies are fixedly mounted on the upper surface of the connecting plate, each storage unit can store one magazine body, a plurality of uniform grids are formed in each magazine body, and the storage units are abutted to the connecting plate;
each storage unit comprises a limiting column, a connecting column and a triangular stop block, the triangular stop block is sleeved on the connecting column, the two ends of the limiting column and the two ends of the connecting column are fixed on the surfaces of the two sides of the supporting plate, the limiting column is higher than the connecting column, and the two ends of each supporting plate are provided with L-shaped chutes which are arranged oppositely.
Further: the feed comprises the following raw materials in parts by weight: 55-75 parts of composite resin, 10-25 parts of nano carbon, 10-35 parts of polyphenylene sulfide and 5-10 parts of metal fiber.
Further: the composite material comprises the following steps:
the composite resin, the nano carbon, the polyphenylene sulfide and the metal fiber are uniformly mixed, then heated to 210 ℃, stirred at a constant speed and extruded to prepare the composite material.
Further: the composite resin is prepared by the following steps:
step S1, adding 2-amino terephthalic acid into N, N-dimethylformamide, stirring at a constant speed, heating to 110 ℃, then adding aluminum chloride hexahydrate in equal amount for two times at an interval of 30min, keeping the temperature, stirring at a constant speed for 6h, standing for reaction for 10h, cooling to room temperature after the reaction is finished, filtering, washing with absolute ethyl alcohol, and then transferring to boiling absolute ethyl alcohol for activation for 20h to obtain a primary material; controlling the ratio of the total amount of the 2-amino terephthalic acid and the aluminum chloride hexahydrate to the amount of the N, N-dimethylformamide to be 1.85-2.10 g: 2.45-2.68 g: 200 mL;
in step S1, N-dimethylformamide is used as a solvent, 2-aminoterephthalic acid is used as a ligand, aluminum chloride hexahydrate is used as a trimer, and 2-aminoterephthalic acid and aluminum chloride hexahydrate form an octahedral skeleton with uniform amino groups on each chain and micropores on each side.
Step S2, adding 2, 2-diallyl bisphenol A into a three-neck flask, heating to 120 ℃, uniformly stirring for 10min, then adding 4, 4-diphenylmethane bismaleimide, keeping the temperature and continuously stirring for 30min, then adding cyanate ester resin, continuously heating and stirring for 30min to obtain a prepolymer, controlling the molar ratio of the 2, 2-diallyl bisphenol A to the 4, 4-diphenylmethane bismaleimide to be 1: 1, and controlling the usage amount of the cyanate ester resin to be 50% of the sum of the weight of the 2, 2-diallyl bisphenol A and the 4, 4-diphenylmethane bismaleimide;
reacting 2, 2-diallyl bisphenol A with 4, 4-diphenylmethane bismaleimide in the step S2, carrying out diene addition reaction on an active double bond in the 4, 4-diphenylmethane bismaleimide and an allyl group in the 2, 2-diallyl bisphenol A in the reaction process to generate an intermediate, then reacting the intermediate with a double bond in the imide and copolymerizing the intermediate with anionic imide to form a network structure, then adding cyanate ester resin, and stirring under heating to form a ternary prepolymer;
step S3, adding the primary material and the prepolymer into a three-neck flask, uniformly stirring for 10min at 140 ℃, then heating to 150 ℃, continuing to stir for 15min, then vacuum degassing for 10min at 140 ℃, then curing and molding to obtain the composite resin, wherein the dosage of the primary material is controlled to be one third of the weight of the prepolymer, and the curing process comprises curing for 2h at 150 ℃, curing for 2h at 180 ℃, curing for 2h at 200 ℃ and curing for 2h at 220 ℃.
In step S3, the primary material and the prepolymer are mixed and then cured at high temperature to form a composite resin material with high crosslinking density, using the ternary prepolymer as a matrix and the primary material skeleton as a functional body, which has a light weight and high strength compared with the conventional metal box material, and can meet the use requirements of the magazine.
The invention has the beneficial effects that:
the light aviation magazine prepared by the invention can meet the requirement of saving space and is convenient to take out without influencing use through a special storage structure, secondly, the light aviation magazine is prepared by adopting a composite material, the weight is greatly reduced, a primary material which is an octahedral framework is prepared during the preparation process of the composite material, each chain on the framework is provided with uniform amino, each side surface is provided with micropores, secondly, a ternary prepolymer is prepared, finally, the primary material and the prepolymer are mixed and then cured at high temperature for forming, the ternary prepolymer is used as a matrix, the primary material framework is used as a functional body, a composite resin material with high crosslinking density is prepared, compared with the traditional metal magazine material, the light aviation magazine has lighter weight and high strength, can meet the use requirement of the magazine, and is not easy to corrode by air in a special environment, compared with the traditional metal material, the material is more durable.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural view of a lightweight aviation magazine according to the present invention;
FIG. 2 is a top view of a lightweight aircraft magazine;
FIG. 3 is a schematic view of the storage unit in the lightweight aeronautical magazine;
FIG. 4 is a schematic view of a structure of a box and a connecting plate.
In the drawings, the components represented by the respective reference numerals are listed below:
1. a support plate; 2. a storage unit; 21. a limiting column; 22. connecting columns; 23. a triangular stop block; 3. a case body; 4. a connecting plate.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-4, the invention is a light aviation magazine, which comprises support plates 1, storage units 2, magazines 3 and a connecting plate 4, wherein the two support plates 1 are oppositely arranged and fixedly mounted on the upper surface of a bottom plate, a plurality of storage units 2 are mounted in each support plate 1, the magazines 3 are fixedly mounted on the upper surface of the connecting plate 4, each storage unit 2 can store one magazine 3, uniform 6X6 grids are arranged on the magazines 3, and the storage units 2 are abutted against the connecting plate 4;
each storage unit 2 comprises a limiting column 21, a connecting column 22 and a triangular stop block 23, the triangular stop block 23 is sleeved on the connecting column 22, the triangular stop block 23 can freely rotate on the connecting column 22, one end of the triangular stop block 23 is installed below the limiting column 21, the other end of the triangular stop block 23 abuts against the lower surface of the box body 3, two ends of the limiting column 21 and two ends of the connecting column 22 are both fixed on the surfaces of two sides of the supporting plate 1, the limiting column 21 is higher than the connecting column 22, and two ends of each supporting plate 1 are both provided with L-shaped chutes which are arranged oppositely;
the use method of the invention comprises the following steps:
the multi-layered cartridge 3 is mounted in the storage unit 2 by the triangular stopper 23, and the cartridge 3 is moved upward from the inner bottom end of the support plate 1 during the storage, the box body 3 can be moved upwards by manual work or external force such as an air cylinder, the box body 3 moves upwards along the L-shaped sliding groove to push one end of the triangular stop block 23 upwards, the box body 3 continues to move upwards until the box body 3 completely exceeds one end of the triangular stop block 23, at the moment, the external force is removed, the box body 3 falls downwards under the action of gravity to press one end of the triangular stop block 23, but the other end of the triangular stop block 23 is arranged below the limiting column 21, the box bodies 3 are supported under the blocking of the limiting columns 21, so that the storage of the box bodies 3 is realized, a plurality of box bodies 3 can be stored in the box body storage device, and can only be upwards taken out, simple structure is but practical, can once deposit a plurality of casket bodies 3, very big space-saving.
Example 1
A composite material for preparing a light aviation magazine comprises the following raw materials in parts by weight: 55 parts of composite resin, 10 parts of nano carbon, 10 parts of polyphenylene sulfide and 5 parts of aluminum metal fiber.
The composite material comprises the following steps:
the composite resin, the nano carbon, the polyphenylene sulfide and the aluminum metal fiber are uniformly mixed, then heated to 210 ℃, stirred at a constant speed and extruded to prepare the composite material.
The composite resin is prepared by the following steps:
step S1, adding 2-amino terephthalic acid into N, N-dimethylformamide, stirring at a constant speed, heating to 110 ℃, then adding aluminum chloride hexahydrate in equal amount for two times at an interval of 30min, keeping the temperature, stirring at a constant speed for 6h, standing for reaction for 10h, cooling to room temperature after the reaction is finished, filtering, washing with absolute ethyl alcohol, and then transferring to boiling absolute ethyl alcohol for activation for 20h to obtain a primary material; the dosage ratio of the total amount of the 2-aminoterephthalic acid and the aluminum chloride hexahydrate to the N, N-dimethylformamide is controlled to be 1.85 g: 2.45 g: 200 mL.
Step S2, adding 2, 2-diallyl bisphenol A into a three-neck flask, heating to 120 ℃, uniformly stirring for 10min, then adding 4, 4-diphenylmethane bismaleimide, keeping the temperature and continuously stirring for 30min, then adding cyanate ester resin, continuously heating and stirring for 30min to obtain a prepolymer, controlling the molar ratio of the 2, 2-diallyl bisphenol A to the 4, 4-diphenylmethane bismaleimide to be 1: 1, and controlling the usage amount of the cyanate ester resin to be 50% of the sum of the weight of the 2, 2-diallyl bisphenol A and the 4, 4-diphenylmethane bismaleimide;
step S3, adding the primary material and the prepolymer into a three-neck flask, uniformly stirring for 10min at 140 ℃, then heating to 150 ℃, continuing to stir for 15min, then vacuum degassing for 10min at 140 ℃, then curing and molding to obtain the composite resin, controlling the dosage of the primary material to be one third of the weight of the prepolymer, wherein the curing process comprises the steps of curing for 2h at 150 ℃, curing for 2h at 180 ℃, curing for 2h at 200 ℃ and curing for 2h at 220 ℃, and through detection, the weight of the magazine prepared by the embodiment is 15% of the weight of the traditional metal magazine, and the magazine has the advantages of high hardness, good impact resistance and toughness, fatigue resistance, and can be safely used within the impact resistance range of 10G.
Example 2
A composite material for preparing a light aviation magazine comprises the following raw materials in parts by weight: 60 parts of composite resin, 15 parts of nano carbon, 20 parts of polyphenylene sulfide and 6 parts of aluminum metal fiber.
The composite material comprises the following steps:
the composite resin, the nano carbon, the polyphenylene sulfide and the aluminum metal fiber are uniformly mixed, then heated to 210 ℃, stirred at a constant speed and extruded to prepare the composite material.
The composite resin is prepared by the following steps:
step S1, adding 2-amino terephthalic acid into N, N-dimethylformamide, stirring at a constant speed, heating to 110 ℃, then adding aluminum chloride hexahydrate in equal amount for two times at an interval of 30min, keeping the temperature, stirring at a constant speed for 6h, standing for reaction for 10h, cooling to room temperature after the reaction is finished, filtering, washing with absolute ethyl alcohol, and then transferring to boiling absolute ethyl alcohol for activation for 20h to obtain a primary material; the dosage ratio of the total amount of the 2-aminoterephthalic acid and the aluminum chloride hexahydrate to the N, N-dimethylformamide is controlled to be 1.98 g: 2.50 g: 200 mL.
Step S2, adding 2, 2-diallyl bisphenol A into a three-neck flask, heating to 120 ℃, uniformly stirring for 10min, then adding 4, 4-diphenylmethane bismaleimide, keeping the temperature and continuously stirring for 30min, then adding cyanate ester resin, continuously heating and stirring for 30min to obtain a prepolymer, controlling the molar ratio of the 2, 2-diallyl bisphenol A to the 4, 4-diphenylmethane bismaleimide to be 1: 1, and controlling the usage amount of the cyanate ester resin to be 50% of the sum of the weight of the 2, 2-diallyl bisphenol A and the 4, 4-diphenylmethane bismaleimide;
step S3, adding the primary material and the prepolymer into a three-neck flask, uniformly stirring for 10min at 140 ℃, then heating to 150 ℃, continuing to stir for 15min, then vacuum degassing for 10min at 140 ℃, then curing and molding to obtain the composite resin, controlling the dosage of the primary material to be one third of the weight of the prepolymer, wherein the curing process comprises the steps of curing for 2h at 150 ℃, curing for 2h at 180 ℃, curing for 2h at 200 ℃ and curing for 2h at 220 ℃, and the weight of the magazine prepared by the embodiment is 16-18% of the weight of the traditional metal magazine through detection, and the magazine has the advantages of high hardness, good impact resistance, good toughness and fatigue resistance, and can be safely used within the range of impact resistance of 11G-15.3G.
Example 3
A composite material for preparing a light aviation magazine comprises the following raw materials in parts by weight: 70 parts of composite resin, 20 parts of nano carbon, 30 parts of polyphenylene sulfide and 8 parts of aluminum metal fiber.
The composite material comprises the following steps:
the composite resin, the nano carbon, the polyphenylene sulfide and the aluminum metal fiber are uniformly mixed, then heated to 210 ℃, stirred at a constant speed and extruded to prepare the composite material.
The composite resin is prepared by the following steps:
step S1, adding 2-amino terephthalic acid into N, N-dimethylformamide, stirring at a constant speed, heating to 110 ℃, then adding aluminum chloride hexahydrate in equal amount for two times at an interval of 30min, keeping the temperature, stirring at a constant speed for 6h, standing for reaction for 10h, cooling to room temperature after the reaction is finished, filtering, washing with absolute ethyl alcohol, and then transferring to boiling absolute ethyl alcohol for activation for 20h to obtain a primary material; the total amount of 2-aminoterephthalic acid and aluminum chloride hexahydrate and the amount of N, N-dimethylformamide are controlled to be 2.05 g: 2.60 g: 200 mL.
Step S2, adding 2, 2-diallyl bisphenol A into a three-neck flask, heating to 120 ℃, uniformly stirring for 10min, then adding 4, 4-diphenylmethane bismaleimide, keeping the temperature and continuously stirring for 30min, then adding cyanate ester resin, continuously heating and stirring for 30min to obtain a prepolymer, controlling the molar ratio of the 2, 2-diallyl bisphenol A to the 4, 4-diphenylmethane bismaleimide to be 1: 1, and controlling the usage amount of the cyanate ester resin to be 50% of the sum of the weight of the 2, 2-diallyl bisphenol A and the 4, 4-diphenylmethane bismaleimide;
step S3, adding the primary material and the prepolymer into a three-neck flask, uniformly stirring for 10min at 140 ℃, then heating to 150 ℃, continuing to stir for 15min, then vacuum degassing for 10min at 140 ℃, then curing and molding to obtain the composite resin, controlling the dosage of the primary material to be one third of the weight of the prepolymer, wherein the curing process comprises the steps of curing for 2h at 150 ℃, curing for 2h at 180 ℃, curing for 2h at 200 ℃ and curing for 2h at 220 ℃, and through detection, the weight of the magazine prepared by the embodiment is 15-18% of the weight of the traditional metal magazine, and the magazine has the advantages of high hardness, good impact resistance and toughness, fatigue resistance, and can be safely used within the impact resistance range of 10G-15G.
Example 4
A composite material for preparing a light aviation magazine comprises the following raw materials in parts by weight: 75 parts of composite resin, 25 parts of nano carbon, 35 parts of polyphenylene sulfide and 10 parts of aluminum metal fiber.
The composite material comprises the following steps:
the composite resin, the nano carbon, the polyphenylene sulfide and the aluminum metal fiber are uniformly mixed, then heated to 210 ℃, stirred at a constant speed and extruded to prepare the composite material.
The composite resin is prepared by the following steps:
step S1, adding 2-amino terephthalic acid into N, N-dimethylformamide, stirring at a constant speed, heating to 110 ℃, then adding aluminum chloride hexahydrate in equal amount for two times at an interval of 30min, keeping the temperature, stirring at a constant speed for 6h, standing for reaction for 10h, cooling to room temperature after the reaction is finished, filtering, washing with absolute ethyl alcohol, and then transferring to boiling absolute ethyl alcohol for activation for 20h to obtain a primary material; the total amount of 2-aminoterephthalic acid and aluminum chloride hexahydrate and the amount of N, N-dimethylformamide are controlled to be 2.10 g: 2.68 g: 200 mL.
Step S2, adding 2, 2-diallyl bisphenol A into a three-neck flask, heating to 120 ℃, uniformly stirring for 10min, then adding 4, 4-diphenylmethane bismaleimide, keeping the temperature and continuously stirring for 30min, then adding cyanate ester resin, continuously heating and stirring for 30min to obtain a prepolymer, controlling the molar ratio of the 2, 2-diallyl bisphenol A to the 4, 4-diphenylmethane bismaleimide to be 1: 1, and controlling the usage amount of the cyanate ester resin to be 50% of the sum of the weight of the 2, 2-diallyl bisphenol A and the 4, 4-diphenylmethane bismaleimide;
step S3, adding the primary material and the prepolymer into a three-neck flask, uniformly stirring for 10min at 140 ℃, then heating to 150 ℃, continuing to stir for 15min, then vacuum degassing for 10min at 140 ℃, then curing and molding to obtain the composite resin, controlling the dosage of the primary material to be one third of the weight of the prepolymer, wherein the curing process comprises the steps of curing for 2h at 150 ℃, curing for 2h at 180 ℃, curing for 2h at 200 ℃ and curing for 2h at 220 ℃, and through detection, the weight of the magazine prepared by the embodiment is 15-17% of the weight of the traditional metal magazine, and the magazine has the advantages of high hardness, good impact resistance, good toughness and fatigue resistance, and can be safely used within the impact resistance range of 9.8-15G.
In the description herein, references to the description of "one embodiment," "an example," "a specific example" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing is merely exemplary and illustrative of the principles of the present invention and various modifications, additions and substitutions of the specific embodiments described herein may be made by those skilled in the art without departing from the principles of the present invention or exceeding the scope of the claims set forth herein.
Claims (7)
1. A light aviation magazine, is made of composite material, and has specific structure, its characterized in that: the structure of the light aviation magazine comprises supporting plates (1), storage units (2), magazine bodies (3) and a connecting plate (4), wherein the two supporting plates (1) are oppositely arranged and fixedly installed on the upper surface of a bottom plate, a plurality of storage units (2) are installed in each supporting plate (1), the magazine bodies (3) are fixedly installed on the upper surface of the connecting plate (4), each storage unit (2) stores one magazine body (3), a plurality of uniform grids are formed in each magazine body (3), and the storage units (2) are abutted to the connecting plate (4);
every deposits unit (2) including spacing post (21), spliced pole (22) and triangle dog (23), triangle dog (23) cup joint on spliced pole (22), and spacing post (21) and spliced pole (22) both ends are all fixed on backup pad (1) both sides surface, and spacing post (21) are higher than spliced pole (22), and the L type spout that sets up relatively is all installed at the both ends of every backup pad (1).
2. A composite material for making a lightweight aeronautical magazine as defined in claim 1, wherein: the feed comprises the following raw materials in parts by weight: 55-75 parts of composite resin, 10-25 parts of nano carbon, 10-35 parts of polyphenylene sulfide and 5-10 parts of metal fiber.
3. A composite material for making a lightweight aeronautical magazine as defined in claim 2, wherein: the composite material comprises the following steps:
the composite resin, the nano carbon, the polyphenylene sulfide and the metal fiber are uniformly mixed, then heated to 210 ℃, stirred at a constant speed and extruded to prepare the composite material.
4. A composite material for making a lightweight aeronautical magazine as defined in claim 2, wherein: the composite resin is prepared by the following steps:
step S1, adding 2-amino terephthalic acid into N, N-dimethylformamide, stirring at a constant speed, heating to 110 ℃, then adding aluminum chloride hexahydrate in equal amount for two times at an interval of 30min, keeping the temperature, stirring at a constant speed for 6h, standing for reaction for 10h, cooling to room temperature after the reaction is finished, filtering, washing with absolute ethyl alcohol, and then transferring to boiling absolute ethyl alcohol for activation for 20h to obtain a primary material;
step S2, adding 2, 2-diallyl bisphenol A into a three-neck flask, heating to 120 ℃, uniformly stirring for 10min, then adding 4, 4-diphenylmethane bismaleimide, keeping the temperature, continuously stirring for 30min, then adding cyanate ester resin, continuously heating and stirring for 30min to obtain a prepolymer;
and step S3, adding the primary material and the prepolymer into a three-neck flask, uniformly stirring for 10min at 140 ℃, then heating to 150 ℃, continuously stirring for 15min, then carrying out vacuum degassing for 10min at 140 ℃, and then curing and molding to obtain the composite resin, wherein the dosage of the primary material is controlled to be one third of the weight of the prepolymer.
5. A composite material for the production of a lightweight aeronautical magazine according to claim 4, wherein: in step S1, the total amount of 2-aminoterephthalic acid and aluminum chloride hexahydrate and the amount of N, N-dimethylformamide are controlled to be 1.85-2.10 g: 2.45-2.68 g: 200 mL.
6. A composite material for the production of a lightweight aeronautical magazine according to claim 4, wherein: in step S2, the molar ratio of 2, 2-diallyl bisphenol A to 4, 4-diphenylmethane bismaleimide is controlled to be 1: 1, and the amount of the cyanate ester resin is 50% of the sum of the weight of 2, 2-diallyl bisphenol A and the weight of 4, 4-diphenylmethane bismaleimide.
7. A composite material for the production of a lightweight aeronautical magazine according to claim 4, wherein: the curing process in step S3 includes curing at 150 deg.C for 2h, curing at 180 deg.C for 2h, curing at 200 deg.C for 2h, and curing at 220 deg.C for 2 h.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111283404.2A CN114018100A (en) | 2021-11-01 | 2021-11-01 | Light aviation magazine and composite material for preparing same |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111283404.2A CN114018100A (en) | 2021-11-01 | 2021-11-01 | Light aviation magazine and composite material for preparing same |
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| CN114018100A true CN114018100A (en) | 2022-02-08 |
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| CN202111283404.2A Pending CN114018100A (en) | 2021-11-01 | 2021-11-01 | Light aviation magazine and composite material for preparing same |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230296338A1 (en) * | 2020-08-18 | 2023-09-21 | Saab Ab | Spring arrangement for countermeasure magazines |
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| US20200064093A1 (en) * | 2018-04-09 | 2020-02-27 | Steve Wilkinson | Ammunition packaging and loading device called a Pac & Load |
| CN111678378A (en) * | 2020-04-24 | 2020-09-18 | 哈尔滨新科锐复合材料制造有限公司 | Composite 27-hole magazine for aviation |
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