CN212378605U - Composite material 30-hole magazine for aviation - Google Patents
Composite material 30-hole magazine for aviation Download PDFInfo
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- CN212378605U CN212378605U CN202020633183.1U CN202020633183U CN212378605U CN 212378605 U CN212378605 U CN 212378605U CN 202020633183 U CN202020633183 U CN 202020633183U CN 212378605 U CN212378605 U CN 212378605U
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Abstract
The utility model relates to a composite material 30-hole magazine for aviation, the existing magazine for aviation generally adopts aluminum alloy forging blank to be processed by an insert bed, the prior magazine for aviation mainly has the defects of multiple and complicated processes, heavy weight, high cost, easy occurrence of local deformation of parts and the like, aiming at the defects, the utility model provides a composite material 30-hole magazine for aviation, which adopts a square box type formed by carbon fiber composite material layering design and integral co-curing and a hollow frame structure of 30 square hole symmetrical type interval grids, and consists of a top plate, a magazine rectangular hole, a top plate cavity, wing plates, a cavity, a bottom plate, side plates, transition convex fillets, transition concave fillets, mounting holes, positioning holes and the like, the carbon fiber prepreg is layered according to design through a mould, the layers are directly layered on a professional forming mould, the integral co-curing and forming is connected into a whole, the defect that the glue amount is increased and the weight is increased due to the prior forming and glue, the weight of the aluminum alloy is about 25 percent lighter than that of the aluminum alloy with the same structure.
Description
Technical Field
The utility model relates to a combined material 30 hole magazine for aviation.
Background
The magazine belongs to the loading body of aviation part, airborne interference bullet, and the weight is reduced as far as possible as priority factor in the design and manufacturing process of aviation part products on the premise of guaranteeing function and quality. The primary design of the magazine adopts an aluminum alloy forging blank processed by an slotting machine, and has the main defects of multiple and complex processes, heavy weight, high cost, easy occurrence of local deformation of parts, poor corrosion resistance, poor oxidation resistance, poor vibration resistance, poor impact resistance, poor fatigue resistance, complex manufacturing process, easy occurrence of vibration, metal fatigue to influence the service life, and large mass to reduce the effective load of the whole machine. Aiming at the defects, in order to achieve the purpose of reducing the weight of an aircraft part, how to design a light-weight and vibration-resistant magazine is an urgent problem to be solved in the manufacturing process of the actual aircraft part on the premise of ensuring the requirements of the quality and the precision of the part.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that according to aviation metal magazine manufacturing process, the part manufacturing process is many and complicated, and weight is big, and anti-vibration performance is poor, and shock resistance is poor, and fatigue resistance is poor, and the technology is complicated, and is not enough with high costs. Redesigning a carbon fiber composite material integral co-curing technology to integrally form and manufacture the aviation 30-hole magazine, adopting carbon fiber composite material layering and changing the layering direction to adapt to the stress of a product, reducing the weight, reducing the vibration, overcoming the metal fatigue and meeting the requirements of the product manufacturing precision and integral interchangeability. The utility model provides a 30 hole magazine of combined material for aviation, adopt and spread the layer design through carbon-fibre composite, whole cocuring fashioned square box type, interval grid frame construction, by the roof, magazine rectangular hole, the roof cavity, the pterygoid lamina cavity, the bottom plate, the curb plate, the protruding fillet of transition, the concave fillet of transition, the mounting hole, components such as locating hole, realize through the mould that carbon fiber preimpregnation material is spread the layer according to the design, whole cocuring, one shot forming, product quality has both been guaranteed, and the service life is prolonged again, high durability and convenient installation, whole atress is good, reduce vibration, reduce and control fatigue and the manufacturing process degree of difficulty.
The utility model aims at providing a 30 hole magazine of combined material for aviation adopts carbon-fibre composite to adopt the manual layer of spreading, whole co-curing shaping, the manufacturing quality is light, improve anti-vibration fatigue, improve cartridge clip life through the mould promptly, can increase flight continuation of the journey mileage effectively, provides a 30 hole magazine that is fit for the aviation.
The utility model provides a technical scheme that its technical problem adopted is:
the utility model provides a 30 hole magazine of combined material for aviation, by roof (1), the square hole of magazine I (2), roof cavity (3), pterygoid lamina (4), pterygoid lamina cavity I (5), pterygoid lamina cavity II (6), bottom plate (7), the square hole of magazine II (8), curb plate (9), well cavity (10), transition radius angle (11), transition radius angle (12), mounting hole (13), locating hole (14) constitute, its characterized in that: the device mainly comprises a top plate (1), 30 magazine square holes I (2), a top plate cavity (3), 2 wing plates (4), a wing plate cavity I (5), a wing plate cavity II (6), a bottom plate (7), 30 magazine square holes II (8), 2 side plates (9), a hollow cavity (10), a transition convex fillet (11), a transition concave fillet (12), a mounting hole (13) and a positioning hole (14), wherein the carbon fiber composite material network cross laying and the integral curing molding are adopted to form an integral symmetrical, square box type grid and hollow type frame structure with different laying thicknesses; the top plate (1) consists of a top plate panel (1-1), 30 magazine square holes I (2), a top plate cavity (3), a transition convex fillet (11) and a transition concave fillet (12), which are mutually connected into a 30 square hole symmetrical grid interval integral frame structure by adopting the same material and layer thickness through one-time co-curing molding, wherein 3 square holes are installed in the first vertical row of 2 vertical rows at two sides, and 4 square holes are installed in each vertical row of 6 vertical rows in the middle; the top plate (1) consists of a top plate panel (1-1), 30 magazine square holes I (2), a top plate cavity (3), a transition convex fillet (11) and a transition concave fillet (12), which are mutually connected into a 30 square hole symmetrical grid interval integral frame structure by adopting the same material and layer thickness through one-time co-curing molding, wherein 3 square holes are installed in the first vertical row of 2 vertical rows at two sides, and 4 square holes are installed in each vertical row of 6 vertical rows in the middle;
the magazine square hole I (2) and the magazine square hole II (8) are of the same structure, the same materials and the same layer thickness are adopted, the magazine square hole I (2) is integrally co-cured and formed into an integral square interval grid type frame at one time, the magazine square hole I (2) is composed of a magazine square hole I transverse plate (2-1), a magazine square hole I longitudinal plate (2-2) and a transition concave fillet (12), and the magazine square hole II (8) is composed of a magazine square hole II transverse plate (8-1), a magazine square hole II longitudinal plate (8-2) and a transition concave fillet (12);
drawings
Fig. 1 is a schematic front perspective view of the present invention.
Fig. 2 is a schematic diagram of a back three-dimensional structure of the present invention.
The magazine comprises a top plate 1, a magazine square hole I2, a top plate cavity 3, wing plates 4, a wing plate cavity 5, a wing plate cavity II 6, a wing plate cavity 7, a bottom plate 8, a magazine square hole II 9, side plates 10, a hollow cavity 11, a transition convex circular bead 12, a transition concave circular bead 13, a mounting hole 14 and a positioning hole 14.
Detailed Description
The technical solution can be realized by the following technical measures and the following description of the present invention is further described with reference to the accompanying drawings:
fig. 1 is the utility model discloses a preceding spatial structure schematic diagram, fig. 2 is the utility model discloses a back spatial structure schematic diagram, a combined material 30 holes magazine for aviation, by roof (1), the square hole of magazine I (2), roof cavity (3), pterygoid lamina (4), pterygoid lamina cavity I (5), pterygoid lamina cavity II (6), bottom plate (7), the square hole of magazine II (8), curb plate (9), well cavity (10), transition convex circular bead (11), transition concave circular bead (12), mounting hole (13), locating hole (14) are constituteed, its characterized in that: the composite type square box type hollow frame mainly comprises a top plate (1), 30 magazine square holes I (2), a top plate cavity (3), 2 wing plates (4), a wing plate cavity I (5), a wing plate cavity II (6), a bottom plate (7), 30 magazine square holes II (8), 2 side plates (9), a hollow cavity (10), a transition convex fillet (11), a transition concave fillet (12), a mounting hole (13) and a positioning hole (14), wherein the integral type symmetrical square box type grid type hollow frame structure with different layer thicknesses is formed by adopting carbon fiber composite material network cross-layered adhesive curing, the length, the width and the height are 225 x 115 x 206mm, and the integral type symmetrical square box type grid type hollow frame structure is formed by directly layering on a professional forming die, adhering and performing one-step curing forming to form into a whole; the top plate (1) consists of a top plate panel (1-1), 30 magazine square holes I (2), a top plate cavity (3), a transition convex fillet (11) and a transition concave fillet (12), the magazine square holes I, the transition convex fillet (11) and the transition concave fillet (12) are mutually connected into a 30 square hole symmetrical grid interval integral frame structure by adopting the same material and layer thickness through one-step curing molding, the first vertical row of 2 vertical rows at two sides is provided with 3 square holes, and each vertical row of 6 vertical rows in the middle is provided with 4 square holes; the bottom plate (7) consists of a bottom plate panel (7-1), 30 magazine square holes II (8), mounting holes (13) and positioning holes (14), the same material and the same layer thickness are adopted to be cured, molded and connected into a 30 square hole symmetrical grid type interval integral frame structure in a gluing mode at one time, the first vertical row of 2 vertical rows on two sides is provided with 3 square holes, each vertical row of 6 vertical rows in the middle is provided with 4 square holes, and the size of each square hole is 25 multiplied by 25 mm; the magazine square hole I (2) and the magazine square hole II (8) are of the same structure, the same materials and the same layer thickness are adopted to be formed in a one-step curing and gluing mode to form a square interval grid type frame, the magazine square hole I (2) is composed of a magazine square hole I transverse plate (2-1), a magazine square hole I longitudinal plate (2-2) and a transition concave fillet (12), and the magazine square hole II (8) is composed of a magazine square hole II transverse plate (8-1), a magazine square hole II longitudinal plate (8-2) and a transition concave fillet (12); the defect that the weight is increased due to the increase of glue consumption caused by molding and gluing is overcome, and finally the whole part is finished by milling fins and drilling.
Claims (5)
1. The utility model provides a 30 hole magazine of combined material for aviation, by roof (1), the square hole of magazine I (2), roof cavity (3), pterygoid lamina (4), pterygoid lamina cavity I (5), pterygoid lamina cavity II (6), bottom plate (7), the square hole of magazine II (8), curb plate (9), well cavity (10), transition radius angle (11), transition radius angle (12), mounting hole (13), locating hole (14) constitute, its characterized in that: the device mainly comprises a top plate (1), 30 magazine square holes I (2), a top plate cavity (3), 2 wing plates (4), a wing plate cavity I (5), a wing plate cavity II (6), a bottom plate (7), 30 magazine square holes II (8), 2 side plates (9), a hollow cavity (10), a transition convex fillet (11), a transition concave fillet (12), a mounting hole (13) and a positioning hole (14), wherein the carbon fiber composite material network cross laying and the integral curing molding are adopted to form an integral symmetrical, square box type grid and hollow type frame structure with different laying thicknesses; the magazine square hole I (2) and the magazine square hole II (8) are of the same structure, and are integrally co-cured and formed into an integral square interval grid type frame at one time by adopting the same material and layer thickness.
2. The composite aeronautical 30-hole magazine according to claim 1, characterized in that: roof (1) comprises roof panel (1-1), 30 magazine square hole I (2), roof cavity (3), transition convex circular bead (11), transition concave circular bead (12), adopts same material each other, spreads layer thickness one shot co-curing shaping and connects into and have 30 square hole symmetrical formula net interval integral frame structure, forms 2 of both sides and erects the row in the first and install 3 square holes, and every erects the row in 6 middle vertical rows and installs 4 square holes.
3. The composite aeronautical 30-hole magazine according to claim 1, characterized in that: roof (1) comprises roof panel (1-1), 30 magazine square hole I (2), roof cavity (3), transition convex circular bead (11), transition concave circular bead (12), adopts same material each other, spreads layer thickness one shot co-curing shaping and connects into and have 30 square hole symmetrical formula net interval integral frame structure, forms 2 of both sides and erects the row in the first and install 3 square holes, and every erects the row in 6 middle vertical rows and installs 4 square holes.
4. The composite aeronautical 30-hole magazine according to claim 1, characterized in that: the magazine square hole I (2) is composed of a transverse plate I (2-1) in the magazine square hole I, a longitudinal plate I (2-2) in the magazine square hole I and a transition concave fillet (12).
5. The composite aeronautical 30-hole magazine according to claim 1, characterized in that: the magazine square hole II (8) is composed of a magazine square hole II transverse plate (8-1), a magazine square hole II longitudinal plate (8-2) and a transition concave fillet (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020633183.1U CN212378605U (en) | 2020-04-24 | 2020-04-24 | Composite material 30-hole magazine for aviation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020633183.1U CN212378605U (en) | 2020-04-24 | 2020-04-24 | Composite material 30-hole magazine for aviation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212378605U true CN212378605U (en) | 2021-01-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020633183.1U Active CN212378605U (en) | 2020-04-24 | 2020-04-24 | Composite material 30-hole magazine for aviation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212378605U (en) |
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2020
- 2020-04-24 CN CN202020633183.1U patent/CN212378605U/en active Active
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