CN213083480U - Wing structure of composite material unmanned aerial vehicle - Google Patents
Wing structure of composite material unmanned aerial vehicle Download PDFInfo
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- CN213083480U CN213083480U CN202022145541.7U CN202022145541U CN213083480U CN 213083480 U CN213083480 U CN 213083480U CN 202022145541 U CN202022145541 U CN 202022145541U CN 213083480 U CN213083480 U CN 213083480U
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- wall body
- wing
- unmanned aerial
- aerial vehicle
- wall
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- 239000002131 composite material Substances 0.000 title claims description 8
- 239000000463 material Substances 0.000 claims abstract description 8
- 239000007787 solid Substances 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 230000035515 penetration Effects 0.000 claims 1
- FGRBYDKOBBBPOI-UHFFFAOYSA-N 10,10-dioxo-2-[4-(N-phenylanilino)phenyl]thioxanthen-9-one Chemical compound O=C1c2ccccc2S(=O)(=O)c2ccc(cc12)-c1ccc(cc1)N(c1ccccc1)c1ccccc1 FGRBYDKOBBBPOI-UHFFFAOYSA-N 0.000 description 1
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Abstract
The utility model discloses a combined material unmanned aerial vehicle's wing structure, which comprises a fuselage, there is the wing on fuselage one side front end and the rear end wall body respectively fixed mounting, fuselage bottom one side is equipped with the wheel respectively with two bottom of wing one sides, still be equipped with the screw in the fuselage one side wall body, two be equipped with the connecting rod on the wall body of wing top one side respectively, connecting rod one side is equipped with locking mechanism, locking mechanism includes locking ring and connecting axle, two be equipped with the fin between the wall body of connecting rod opposite side, locking mechanism has still seted up first spiral shell groove in fin one side front end and rear end wall body respectively, locking mechanism still has the fixed block at wing top one side wall body fixed mounting. A combined material unmanned aerial vehicle's wing structure, relate to unmanned aerial vehicle equipment technical field, through its locking mechanism's setting, be convenient for carry out the dismouting with its fin from the wing, can be more convenient and efficient maintain its fin.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle equipment technical field, in particular to combined material unmanned aerial vehicle's wing structure.
Background
Unmanned planes, abbreviated as "drones" in english and "UAVs" in short, are unmanned planes operated by radio remote control devices and self-contained program control devices, or operated autonomously, either completely or intermittently, by an on-board computer, and are often more suitable for tasks that are too "fool, dirty, or dangerous" than unmanned planes, which can be classified into military and civilian applications, depending on the field of application. For military use, unmanned aerial vehicles are divided into reconnaissance aircraft and target drone, and for civil use, unmanned aerial vehicles + industrial application are really just needed for unmanned aerial vehicles; at present at the aerial photography, agriculture, plant protection, miniature autodyne, express delivery transportation, disaster relief, observe wild animal, control infectious disease, survey and drawing, news report, electric power is patrolled and examined, relief of disaster, the film and television is shot, make the application in fields such as romantic, great expansion unmanned aerial vehicle's use itself, developed country is also actively expanding the industry and is using and developing unmanned aerial vehicle technique, and unmanned aerial vehicle rotor unmanned aerial vehicle and fixed wing unmanned aerial vehicle respectively, especially, the fin of part fixed wing unmanned aerial vehicle all is through connecting rod fixed mounting on two wings, when maintaining its fin, it is comparatively troublesome to dismantle.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a combined material unmanned aerial vehicle's wing structure can effectively solve the problem in the background art.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the utility model provides a combined material unmanned aerial vehicle's wing structure, includes the fuselage, there is the wing respectively fixed mounting on fuselage one side front end and the back end wall body, fuselage bottom one side is equipped with the wheel respectively with two wing bottom one sides, still be equipped with the screw in the fuselage lateral wall body, two be equipped with the connecting rod on the wall body of wing top lateral wall respectively, connecting rod one side is equipped with locking mechanism, locking mechanism includes locking ring and connecting axle, two be equipped with the fin between the wall body of connecting rod opposite side.
Preferably, the locking mechanism is provided with first screw grooves in the front end of one side of the tail wing and the rear end wall body respectively, the locking mechanism is further fixedly provided with a fixed block on the wall body on one side of the top of the wing, and a second screw groove is formed in the wall body of the fixed block.
Preferably, the outer wall of one side of each of the two connecting rods is provided with a third thread, and the two connecting rods are screwed into the corresponding first thread grooves through the third threads on the outer wall of one side of each of the two connecting rods.
Preferably, fixed mounting has solid fixed ring on the connecting rod opposite side outer wall, fixed ring fixed mounting has the rubber circle on the wall body of a lateral wall, it has fixed commentaries on classics piece still fixed mounting on the wall body of a lateral wall of connecting rod.
Preferably, the inner wall of one side of the locking ring is provided with a rotary groove, the inner wall of the other side of the locking ring is provided with a third screw groove, and the locking ring is arranged on the fixing ring in an inserting manner through the rotary groove.
Preferably, the connecting shaft is inserted and installed on the fixed rotating block through a limiting groove in a side wall body, a first thread is further arranged on the outer wall of one side of the connecting shaft, a plurality of anti-slip strips are fixedly installed on the outer wall, close to one side of the first thread, of the connecting shaft, a second thread is further arranged on the outer wall of the other side of the connecting shaft, and one side of the connecting shaft is installed in the corresponding second thread groove through the second thread in a screwed mode.
Compared with the prior art, the utility model discloses following beneficial effect has:
a combined material unmanned aerial vehicle's wing structure, through its locking mechanism's setting, be convenient for carry out the dismouting with the fin from the wing, can be more convenient and efficient maintain its fin.
Drawings
FIG. 1 is a schematic view of the main structure of the present invention;
FIG. 2 is an exploded view of the locking mechanism of the present invention;
FIG. 3 is a side view of a wing of the present invention;
fig. 4 is an enlarged view of a portion a in fig. 2.
In the figure: 1. a body; 2. an airfoil; 3. a machine wheel; 4. a propeller; 5. a connecting rod; 6. a locking mechanism; 7. locking a ring; 8. a connecting shaft; 9. a tail wing; 10. a first screw groove; 11. a fixed block; 12. a second screw groove; 13. a fixing ring; 14. a rubber ring; 15. fixing the rotating block; 16. rotating the groove; 17. a third screw groove; 18. a first thread; 19. anti-slip strips; 20. a second thread; 21. a third thread.
Detailed Description
In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element to which the reference is made must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, and for example, "connected" may be either fixedly connected or detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1-4, the utility model provides a pair of combined material unmanned aerial vehicle's wing structure, including fuselage 1, there are wing 2 on 1 one side front end of fuselage and the rear end wall body respectively fixed mounting, fuselage 1 bottom one side is equipped with wheel 3 respectively with two 2 bottom sides of wing one side, still is equipped with screw 4 in the 1 lateral wall body of fuselage, is equipped with connecting rod 5 on the 2 top lateral wall bodies of two wings respectively, and connecting rod 5 one side is equipped with locking mechanism 6, and locking mechanism 6 includes locking ring 7 and connecting axle 8, is equipped with fin 9 between the 5 opposite side wall bodies of two connecting rods.
The locking mechanism 6 is also provided with a first screw groove 10 in the front end of one side of the empennage 9 and the rear end wall body respectively, the locking mechanism 6 is also fixedly provided with a fixed block 11 on the wall body of one side of the top of the wing 2, and a second screw groove 12 is arranged in the wall body of the fixed block 11.
The outer walls of one sides of the two connecting rods 5 are respectively provided with a third thread 21, and the two connecting rods 5 are respectively screwed and installed in the corresponding first screw grooves 10 through the third threads 21 on the outer walls of one sides.
The outer wall of the other side of the connecting rod 5 is fixedly provided with a fixing ring 13, the wall body of one side of the fixing ring 13 is fixedly provided with a rubber ring 14, the wall body of one side of the connecting rod 5 is also fixedly provided with a fixing rotating block 15, and the fixing ring 13 and the rubber ring 14 are arranged to facilitate the installation of the locking ring 7.
The inner wall of one side of the locking ring 7 is provided with a rotary groove 16, the inner wall of the other side of the locking ring 7 is provided with a third screw groove 17, the locking ring 7 is arranged on the fixing ring 13 in a penetrating manner through the rotary groove 16, the locking ring 7 can be conveniently arranged on the connecting rod 5 through the arrangement of the rotary groove 16, and meanwhile, the locking ring can be conveniently locked on the connecting shaft 8 through the arrangement of the third screw groove 17.
Connecting axle 8 passes through the spacing groove interlude in the lateral wall body and installs on fixed commentaries on classics piece 15, still be equipped with first screw thread 18 on the outer wall of connecting axle 8 one side, connecting axle 8 fixed mounting has a plurality of antislip strip 19 on the outer wall that is close to first screw thread 18 one side, connecting axle 8 still is equipped with second screw thread 20 on the opposite side outer wall, and install in corresponding second spiral shell groove 12 through second screw thread 20 screw in connecting axle 8 one side, through the setting of connecting axle 8, can be with in the fixed block 11 of its connecting rod 5 fixed mounting on wing 2.
It should be noted that, the utility model relates to a wing structure of composite material unmanned aerial vehicle, when using, when needing to install its fin 9 on wing 2, only need to screw in respectively its two connecting rods 5 into the first thread groove 10 of fin 9 one side through the third screw 21 on one side outer wall first, then, screw in respectively the connecting axle 8 of its two connecting rods 5 one side into the second thread groove 12 of installing in wing 2 top fixed block 11 through the second screw 20 of its one side outer wall, then, through the spanner centre gripping on the outer wall that connecting axle 8 is located antislip strip 19 position, and then continue to rotate its connecting axle 8, and then make connecting axle 8 screw in second thread groove 12 through the second screw 20 of one side, in addition, the connecting axle 8 rotates on the solid fixed ring 13 of connecting rod 5 one side through the spacing groove of its one side when rotatory, after the connecting shaft 8 is screwed in the corresponding second thread groove 12, the locking ring 7 is rotated, so that the locking ring 7 is screwed into the first thread 18 on the outer wall of the other side of the connecting shaft 8 through the third thread groove 17 on the inner wall of one side, the locking ring 7 moves on the fixing ring 13 through the rotating groove 16 on the inner wall of the other side, and along with the rotation of the locking ring 7, the inner wall of the rotating groove 16 is gradually extruded on the rubber ring 14, so that the connecting shaft 8 and the connecting rod 5 are fixed more firmly, and the shaking is prevented.
The basic principles and the main features of the invention and the advantages of the invention have been shown and described above. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (6)
1. The utility model provides a combined material unmanned aerial vehicle's wing structure which characterized in that: including fuselage (1), there are wing (2) on fuselage (1) one side front end and the rear end wall body respectively fixed mounting, fuselage (1) bottom one side is equipped with wheel (3) respectively with two wing (2) bottom one side, still be equipped with screw (4), two in fuselage (1) one side wall body be equipped with connecting rod (5) on the wall body of wing (2) top one side respectively, connecting rod (5) one side is equipped with locking mechanism (6), locking mechanism (6) include locking ring (7) and connecting axle (8), two be equipped with fin (9) between connecting rod (5) the opposite side wall body.
2. The wing structure of composite material unmanned aerial vehicle of claim 1, wherein: locking mechanism (6) have still seted up first thread groove (10) respectively in fin (9) one side front end and rear end wall body, locking mechanism (6) still fixed mounting has fixed block (11) on a wing (2) top lateral wall body, set up second thread groove (12) in fixed block (11) wall body.
3. The wing structure of composite material unmanned aerial vehicle of claim 2, wherein: and third threads (21) are respectively arranged on the outer wall of one side of each of the two connecting rods (5), and the two connecting rods (5) are respectively screwed in and installed in the corresponding first screw grooves (10) through the third threads (21) on the outer wall of one side.
4. The wing structure of composite material unmanned aerial vehicle of claim 3, wherein: fixed mounting has solid fixed ring (13) on connecting rod (5) opposite side outer wall, fixed mounting has rubber circle (14) on solid fixed ring (13) a lateral wall body, it has fixed commentaries on classics piece (15) to go back fixed mounting on connecting rod (5) a lateral wall body.
5. The wing structure of composite material unmanned aerial vehicle of claim 4, wherein: the inner wall of one side of the locking ring (7) is provided with a rotary groove (16), the inner wall of the other side of the locking ring is provided with a third screw groove (17), and the locking ring (7) is arranged on the fixing ring (13) in a penetrating manner through the rotary groove (16).
6. The wing structure of composite material unmanned aerial vehicle of claim 5, wherein: the connecting shaft (8) is installed on the fixed rotating block (15) through the penetration of a limiting groove in a side wall body, a first thread (18) is further arranged on the outer wall of one side of the connecting shaft (8), a plurality of anti-slip strips (19) are fixedly installed on the outer wall close to one side of the first thread (18) of the connecting shaft (8), a second thread (20) is further arranged on the outer wall of the other side of the connecting shaft (8), and one side of the connecting shaft (8) is installed in the corresponding second thread groove (12) through the second thread (20) in a screwed mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022145541.7U CN213083480U (en) | 2020-09-25 | 2020-09-25 | Wing structure of composite material unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022145541.7U CN213083480U (en) | 2020-09-25 | 2020-09-25 | Wing structure of composite material unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213083480U true CN213083480U (en) | 2021-04-30 |
Family
ID=75612781
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022145541.7U Active CN213083480U (en) | 2020-09-25 | 2020-09-25 | Wing structure of composite material unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213083480U (en) |
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2020
- 2020-09-25 CN CN202022145541.7U patent/CN213083480U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 710089 No. 38, Hangkong 1st Road, National Aviation high tech industry base, Xi'an, Shaanxi Province Patentee after: Xi'an Yalong Aviation Electromechanical Co.,Ltd. Country or region after: China Address before: No.38, Hangkong 1st Road, Xi'an Aviation base, Shaanxi 710000 Patentee before: XI'AN YALONG AVIATION ELECTROMECHANICAL CO.,LTD. Country or region before: China |