CN219969986U - Structure for quickly disassembling and assembling main wings of fixed-wing aircraft - Google Patents
Structure for quickly disassembling and assembling main wings of fixed-wing aircraft Download PDFInfo
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- CN219969986U CN219969986U CN202321277214.4U CN202321277214U CN219969986U CN 219969986 U CN219969986 U CN 219969986U CN 202321277214 U CN202321277214 U CN 202321277214U CN 219969986 U CN219969986 U CN 219969986U
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- main wing
- wing
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- fixed
- bracket
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 16
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 16
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 10
- 229910052782 aluminium Inorganic materials 0.000 claims description 10
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 7
- 239000010949 copper Substances 0.000 claims description 7
- 229910052802 copper Inorganic materials 0.000 claims description 7
- 238000005452 bending Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000004033 plastic Substances 0.000 claims description 3
- 229920001296 polysiloxane Polymers 0.000 claims description 2
- 238000009434 installation Methods 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a structure for quickly disassembling and assembling a main wing of a fixed-wing aircraft, which comprises a main wing assembly, wherein the main wing assembly comprises a first main wing and a second main wing which are symmetrically arranged, the first main wing and the second main wing are connected through a main wing bracket, a circular carbon tube is arranged between the first main wing and the second main wing, two sides of the circular carbon tube respectively extend into the first main wing and the second main wing, circular grooves matched with the circular carbon tube are formed in the first main wing and the second main wing, and a fuselage assembly is arranged at the bottom end of the main wing bracket. The beneficial effects are that: the main wing assembly is connected with the fuselage assembly in a spliced mode, so that the main wing assembly is convenient for a consumer to assemble and disassemble, the transportation is also convenient, the main wing assembly is connected with the fuselage assembly through the positioning column and the hand screw, a screwdriver is not required to be used, the installation is simpler and more convenient, the quick disassembly is convenient, the connection is firmer, and meanwhile, the existence of the anti-slip gasket prevents the vibration from loosening the hand screw to further improve the safety of the hand screw.
Description
Technical Field
The utility model relates to the technical field of aircrafts, in particular to a structure for quickly disassembling and assembling a main wing of a fixed-wing aircraft.
Background
The aircraft is any flying object which is manufactured by human beings, can fly off the ground, flies in space and is controlled by people and is provided for individuals, the main wings of the existing aircraft are designed to be assembled for convenient transportation, the main wings can be detached in the transportation process to enable the transportation to be more convenient, when the consumer takes the aircraft, the main wings are required to be assembled and fixed, a large number of screws are adopted for assembling and connecting all parts of the main wings in the existing assembling and fixing process, thus time is wasted, assembling steps are complex due to the fact that the parts are scattered, and the personnel are difficult to get on hand quickly.
For the problems in the related art, no effective solution has been proposed at present.
Disclosure of Invention
Aiming at the problems in the related art, the utility model provides a structure for quickly disassembling and assembling a main wing of a fixed-wing aircraft, so as to overcome the technical problems in the prior art.
For this purpose, the utility model adopts the following specific technical scheme:
the utility model provides a fixed wing aircraft main wing quick detach and assembled structure, includes the main wing subassembly, the main wing subassembly includes main wing first and main wing second that the symmetry set up, main wing first with main wing second is connected through the main wing support, main wing first with be equipped with circular carbon tube between the main wing second, circular carbon tube both sides extend to respectively main wing first with in the main wing second, main wing first with all seted up in the main wing second with circular carbon tube assorted circular slot, main wing support bottom is equipped with the fuselage subassembly, the fuselage subassembly includes main wing front fixed bolster that main wing support bottom one side was equipped with, main wing support bottom is kept away from main wing front fixed bolster's one side is equipped with main wing rear fixed bolster, main wing front fixed bolster top be equipped with a plurality of evenly distributed's reference column, main wing first main wing second with main wing support is last all seted up respectively with in the main wing second main wing support with in the main wing second, main wing first with all seted up with circular carbon tube assorted circular carbon tube's circular slot, main wing support bottom is equipped with the fuselage bottom half is equipped with the fuselage assembly through main wing rear fixed bolster, main wing screw and main wing aluminium pipe front and front fixed bolster are equipped with respectively with through main wing rear fixed bolster and main wing front and rear fixed bolster, front and back aircraft fuselage fixed bolster all are equipped with respectively.
Preferably, a positioning groove is formed in one side, close to the second main wing, of the first main wing, and a positioning boss matched with the positioning groove is arranged on one side of the second main wing.
Preferably, copper nuts matched with the hand-screwed screws are pre-buried in the main wing support, and a positioning hole II matched with the hand-screwed screws is formed in the top end of the main wing rear fixing support.
Preferably, a limiting wall is arranged on one side of the top end of the main wing rear fixing support.
Preferably, the anti-slip straight lines are formed in the screw head of the hand-screwed screw, and the anti-slip washer is sleeved on the outer wall of the hand-screwed screw.
Preferably, the anti-slip washer is one of a rubber washer or a silica gel washer.
Preferably, the first main wing and the second main wing are provided with mounting grooves matched with the main wing brackets.
Preferably, the main wing bracket is made of plastic material, and bending ends respectively wrapping the front edges of the first main wing and the second main wing are arranged on two sides of the main wing bracket.
The beneficial effects of the utility model are as follows: the main wing assembly is connected with the fuselage assembly in a spliced mode, so that the main wing assembly is convenient for a consumer to assemble and disassemble, the transportation is also convenient, the main wing assembly is connected with the fuselage assembly through the positioning column and the hand screw, a screwdriver is not required to be used, the installation is simpler and more convenient, the quick disassembly is convenient, the connection is firmer, and meanwhile, the existence of the anti-slip gasket prevents the vibration from loosening the hand screw to further improve the safety of the hand screw.
Drawings
In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic overall structural view of a fast disassembled and assembled structure of a main wing of a fixed wing aircraft in accordance with an embodiment of the present utility model;
FIG. 2 is another angular structural schematic view of a fast disassembly and assembly of a fixed wing aircraft main wing in accordance with an embodiment of the present utility model;
FIG. 3 is a schematic illustration of a main wing of a fixed wing aircraft in a main sectional view with rapid disassembly and assembly in accordance with an embodiment of the present utility model;
FIG. 4 is an enlarged view of a portion of FIG. 3 at A;
FIG. 5 is an exploded view of a structure for quick disassembly and assembly of a main wing of a fixed wing aircraft in accordance with an embodiment of the present utility model;
FIG. 6 is a schematic view of a main wing front fixed bracket in a fast disassembly and assembly configuration of a main wing of a fixed wing aircraft in accordance with an embodiment of the present utility model;
FIG. 7 is a schematic view of a rear fixed bracket structure of a main wing in a structure for quick disassembly and assembly of the main wing of a fixed wing aircraft according to an embodiment of the present utility model;
FIG. 8 is a schematic side cross-sectional view of a structure for quick disassembly and assembly of a main wing of a fixed wing aircraft in accordance with an embodiment of the utility model.
In the figure:
1. a primary wing I; 2. a second main wing; 3. a main wing bracket; 4. a circular carbon tube; 5. a main wing front fixing bracket; 6. a main wing rear fixing bracket; 7. positioning columns; 8. screwing the screw by hand; 9. an aluminum pipe in the direction of the machine body; 10. a direction fixing groove; 11. a screw; 12. a positioning groove; 13. positioning the boss; 14. a copper nut; 15. positioning holes II; 16. positioning holes I; 17. a limiting wall; 18. an anti-slip washer.
Detailed Description
For the purpose of further illustrating the various embodiments, the present utility model provides the accompanying drawings, which are a part of the disclosure of the present utility model, and which are mainly used to illustrate the embodiments and, together with the description, serve to explain the principles of the embodiments, and with reference to these descriptions, one skilled in the art will recognize other possible implementations and advantages of the present utility model, wherein elements are not drawn to scale, and like reference numerals are generally used to designate like elements.
According to an embodiment of the utility model, a structure for quick disassembly and assembly of a main wing of a fixed-wing aircraft is provided.
Embodiment one;
as shown in fig. 1-7, the fast disassembly and assembly structure of the main wing of the fixed wing aircraft according to the embodiment of the utility model comprises a main wing component, wherein the main wing component comprises a main wing 1 and a main wing 2 which are symmetrically arranged, the main wing 1 and the main wing 2 are connected through a main wing bracket 3, a circular carbon tube 4 is arranged between the main wing 1 and the main wing 2, two sides of the circular carbon tube 4 respectively extend into the main wing 1 and the main wing 2, circular grooves matched with the circular carbon tube 4 are respectively arranged in the main wing 1 and the main wing 2, a fuselage component is arranged at the bottom end of the main wing bracket 3, the fuselage component comprises a main wing front fixed bracket 5 arranged at one side of the bottom end of the main wing bracket 3, a main wing rear fixed bracket 6 is arranged at one side of the bottom end of the main wing bracket 3 away from the main wing front fixed bracket 5, the top end of the main wing front fixing bracket 5 is provided with a plurality of evenly distributed positioning columns 7, the main wing I1, the main wing II 2 and the main wing bracket 3 are respectively provided with a positioning hole I16 matched with the positioning columns 7, the main wing rear fixing bracket 6 is respectively connected with the main wing rear fixing bracket 6, the main wing I1 and the main wing II 2 through hand screws 8, a main body direction aluminum pipe 9 respectively penetrating through the main wing front fixing bracket 5 and the main wing rear fixing bracket 6 is arranged between the main wing front fixing bracket 5 and the main wing rear fixing bracket 6, the main wing front fixing bracket 5 and the main wing rear fixing bracket 6 are respectively provided with a direction fixing groove 10 matched with the main body direction aluminum pipe 9, the main wing front fixing support 5 and the main wing rear fixing support 6 are respectively connected with the machine body direction aluminum pipe 9 through screws 11.
Embodiment two;
as shown in fig. 1-7, the second embodiment further includes, based on the first embodiment: a positioning groove 12 is formed in one side, close to the second main wing 2, of the first main wing 1, and a positioning boss 13 matched with the positioning groove 12 is arranged on one side of the second main wing 2. Copper nuts 14 matched with the hand-screwed screws 8 are embedded in the main wing bracket 3, and positioning holes II 15 matched with the hand-screwed screws 8 are formed in the top ends of the main wing rear fixing brackets 6. And a limiting wall 17 is arranged on one side of the top end of the main wing rear fixing support 6. The main wing support 3 is made of plastic materials, and bending ends which wrap the front edges of the main wing I1 and the main wing II 2 respectively are arranged on two sides of the main wing support 3. The butt joint of the first main wing 1 and the second main wing 2 is faster, more accurate and time-saving through the positioning groove 12 and the positioning boss 13, the screw 8 is conveniently screwed by hand to be connected and installed through arranging the copper nut 14 in the main wing bracket 3, and the rear side of the main wing bracket 3 can be limited through arranging the limiting wall 17.
Embodiment three;
as shown in fig. 1-7, the third embodiment further includes, based on the first embodiment or the second embodiment: the anti-slip straight lines are formed in the screw head of the hand-screwed screw 8, and an anti-slip washer 18 is sleeved on the outer wall of the hand-screwed screw 8. The anti-slip washer 18 is one of a rubber washer or a silicone washer. And the first main wing 1 and the second main wing 2 are provided with mounting grooves matched with the main wing bracket 3. By providing the anti-slip straight lines, people can conveniently screw the hand-screwed screws 8, and by adding the anti-slip washers 18, the loosening of the hand-screwed screws 8 can be prevented, and the safety of the hand-screwed screws is improved.
In practical application, assembling, namely firstly assembling a main wing assembly, namely firstly inserting two ends of a circular carbon tube 4 into circular grooves on a main wing I1 and a main wing II 2 respectively, then pushing the main wing I1 and the main wing II 2 to enable a positioning boss 13 on the main wing II 2 to be clamped into a positioning groove 12 on the main wing I1, and then installing a main wing bracket 3 in installation grooves on the main wing I1 and the main wing II 2; secondly, assembling a main body assembly, namely sleeving a main wing front fixing bracket 5 and a main wing rear fixing bracket 6 on a main body direction aluminum pipe 9 through a direction fixing groove 10, and locking the main wing front fixing bracket 5 and the main wing rear fixing bracket 6 on the main body direction aluminum pipe 9 by adopting screws 11; the third step is to fix the main wing assembly and the fuselage assembly, firstly, the positioning column 7 on the main wing front fixing support 5 is inserted into the positioning holes 16 on the main wing support 3, the main wing 1 and the main wing 2, then the anti-slip washer 18 is sleeved on the outer wall of the hand-screwing screw 8, the tip of the hand-screwing screw 8 is inserted into the positioning hole 15 from the bottom end of the main wing rear fixing support 6, when the tip of the hand-screwing screw 8 approaches to the copper nut 14 in the main wing support 3, the hand-screwing screw 8 is in threaded connection with the copper nut 14, the main wing assembly is fixedly arranged on the fuselage assembly through the hand-screwing screw 8, the assembly is particularly convenient and simple, the quick disassembly is convenient, the head of the hand-screwing screw 8 has anti-slip threads, the hand-screwing screw 8 is convenient to operate manually, and the existence of the anti-slip washer 18 prevents the vibration from loosening the hand-screwing screw 8.
In summary, by means of the technical scheme of the utility model, the main wing assembly and the machine body assembly are spliced and connected, so that the main wing assembly is convenient for a consumer to assemble and disassemble, and the main wing assembly and the machine body assembly are convenient to transport, meanwhile, the main wing assembly and the machine body assembly are connected through the positioning column and the hand screw without a screwdriver, the installation is simpler and more convenient, the quick disassembly is convenient, the connection is firmer, and meanwhile, the loosening of the hand screw caused by vibration is prevented by the anti-slip gasket, so that the safety of the machine is further improved.
The foregoing description of the preferred embodiments of the utility model is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the utility model.
Claims (8)
1. The utility model provides a fast dismantlement and assembled structure of fixed wing aircraft main wing, its characterized in that includes the main wing subassembly, main wing subassembly includes symmetrical main wing first (1) and main wing second (2) that set up, main wing first (1) with main wing second (2) are connected through main wing support (3), main wing first (1) with be equipped with circular carbon tube (4) between main wing second (2), circular carbon tube (4) both sides extend respectively to main wing first (1) with in main wing second (2), main wing first (1) with circular groove with circular carbon tube (4) assorted is all seted up in main wing second (2), main wing support (3) bottom is equipped with the fuselage subassembly, the fuselage subassembly includes main wing front fixing support (5) that main wing support (3) bottom one side was equipped with, main wing front fixing support (5) one side is kept away from, main wing first (6) are equipped with respectively, main wing first (7) and second (2) are equipped with evenly distributed in main wing first (3) and second (2) are equipped with locating post (16), the utility model provides a wing rear fixing support (6) through hand screw (8) respectively with wing rear fixing support (6) main wing one (1) with wing two (2) are connected, fixed bolster (5) before the main wing with be equipped with between wing rear fixing support (6) respectively run through before the main wing fixed bolster (5) with fuselage direction aluminum pipe (9) of wing rear fixing support (6), before the main wing fixed bolster (5) with all set up respectively on wing rear fixing support (6) with fuselage direction aluminum pipe (9) assorted direction fixed slot (10), before the main wing fixed bolster (5) with wing rear fixing support (6) all are connected through screw (11) respectively with fuselage direction aluminum pipe (9).
2. The structure for quickly disassembling and assembling the main wing of the fixed wing aircraft according to claim 1, wherein a positioning groove (12) is formed in one side, close to the main wing two (2), of the main wing one (1), and a positioning boss (13) matched with the positioning groove (12) is formed in one side of the main wing two (2).
3. The structure for quickly disassembling and assembling the main wing of the fixed wing aircraft according to claim 1, wherein copper nuts (14) matched with the hand-screwed screws (8) are embedded in the main wing bracket (3), and positioning holes (15) matched with the hand-screwed screws (8) are formed in the top ends of the main wing rear fixed bracket (6).
4. The structure for quickly disassembling and assembling the main wing of the fixed wing aircraft according to claim 1, wherein a limiting wall (17) is arranged on one side of the top end of the rear fixed wing bracket (6).
5. The structure for quickly disassembling and assembling the main wing of the fixed wing aircraft according to claim 1, wherein the screw head of the hand-screwed screw (8) is provided with anti-slip straight lines, and the outer wall of the hand-screwed screw (8) is sleeved with an anti-slip gasket (18).
6. The structure for rapid disassembly and assembly of a main wing of a fixed wing aircraft according to claim 5, characterized in that said anti-slip gasket (18) is one of a rubber gasket or a silicone gasket.
7. The structure for quickly disassembling and assembling the main wings of the fixed wing aircraft according to claim 1, wherein the first main wing (1) and the second main wing (2) are provided with mounting grooves matched with the main wing bracket (3).
8. The structure for quickly disassembling and assembling the main wing of the fixed wing aircraft according to claim 1, wherein the main wing bracket (3) is made of plastic materials, and bending ends for respectively wrapping the front edges of the first main wing (1) and the second main wing (2) are arranged on two sides of the main wing bracket (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321277214.4U CN219969986U (en) | 2023-05-24 | 2023-05-24 | Structure for quickly disassembling and assembling main wings of fixed-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321277214.4U CN219969986U (en) | 2023-05-24 | 2023-05-24 | Structure for quickly disassembling and assembling main wings of fixed-wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219969986U true CN219969986U (en) | 2023-11-07 |
Family
ID=88582353
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321277214.4U Active CN219969986U (en) | 2023-05-24 | 2023-05-24 | Structure for quickly disassembling and assembling main wings of fixed-wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219969986U (en) |
-
2023
- 2023-05-24 CN CN202321277214.4U patent/CN219969986U/en active Active
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant |