CN220263086U - Multi-rotor unmanned aerial vehicle - Google Patents
Multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN220263086U CN220263086U CN202321879518.8U CN202321879518U CN220263086U CN 220263086 U CN220263086 U CN 220263086U CN 202321879518 U CN202321879518 U CN 202321879518U CN 220263086 U CN220263086 U CN 220263086U
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- 238000005859 coupling reaction Methods 0.000 claims description 14
- 230000006978 adaptation Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 10
- 206010040007 Sense of oppression Diseases 0.000 abstract description 5
- 230000003139 buffering effect Effects 0.000 abstract description 5
- 210000001015 abdomen Anatomy 0.000 description 3
- 230000001771 impaired effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 239000000575 pesticide Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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Abstract
The utility model belongs to the technical field of unmanned aerial vehicles, in particular to a multi-rotor unmanned aerial vehicle which comprises a machine body, wherein four paddle wings are arranged on the machine body, paddles are arranged on the paddle wings, and a buffer box is fixedly connected to the top of the machine body; through setting up trapezoidal piece and triangular block, when many rotor unmanned aerial vehicle meed the trouble, if the back falls to the ground, trapezoidal apron is oppressed, trapezoidal apron oppression spliced pole, under the effect of first spring, the spliced pole slides in trapezoidal piece for the striking obtains once buffering, the spliced pole is at the trapezoidal piece of downward movement oppression, trapezoidal piece downward movement, trapezoidal piece oppression triangular block moves to opposite direction, triangular block oppression slip post, under the effect of second spring, the slip post slides in the sleeve pipe, make the striking obtain secondary buffering, the buffering protect function to the fuselage has been realized, the problem that the fuselage does not have fine safeguard function and can not reach the effect of protecting fuselage internals is solved.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a multi-rotor unmanned aerial vehicle.
Background
The unmanned aerial vehicle is a unmanned aerial vehicle mainly controlled by radio remote control, wherein the multi-rotor unmanned aerial vehicle is a special unmanned aerial vehicle with three or more rotor shafts, is widely applied to various fields such as aerial photography, detection, pesticide spraying and the like, has high efficiency, low cost, accurate data and flexible operation, and can meet various different requirements.
Existing issued patent publication numbers: CN110143275B, this novel disclosure is a many rotor unmanned aerial vehicle, when many rotor unmanned aerial vehicle flies forward, promotes the rotation plane backward and emptys and produce negative rake, before the negative rake produced, pneumatic torque direction is opposite with promotion rotor rotation direction, after the negative rake produced, pneumatic torque direction becomes the same with promotion rotor rotation direction, once the negative rake produces, the direction of the pneumatic torque of air application in promotion rotor changes, promotion rotor is rotated by motor drive and is changed into air drive rotation.
At present, when the multi-rotor unmanned aerial vehicle works in the air, accidental faults can occur, the unmanned aerial vehicle is easy to fall or collide with foreign objects and only depends on the body for protection, but the body is damaged once to directly cause the damage of the inner part of the body of the multi-rotor unmanned aerial vehicle, important parts of the multi-rotor unmanned aerial vehicle are arranged in the body, the damage can influence the normal use of the unmanned aerial vehicle, and the current body cannot achieve the effect of protecting the inner part of the body due to the fact that the body does not have a good protection function.
Therefore, a multi-rotor unmanned aerial vehicle is proposed to address the above-mentioned problems.
Disclosure of Invention
In order to make up the defects of the prior art, solve the problem that the fuselage does not have a good protection function and cannot achieve the effect of protecting the internal parts of the fuselage, the multi-rotor unmanned aerial vehicle is provided.
The technical scheme adopted for solving the technical problems is as follows: the utility model relates to a multi-rotor unmanned aerial vehicle, which comprises a machine body, wherein four paddle wings are arranged on the machine body, paddles are arranged on the paddle wings, a buffer box is fixedly connected to the top of the machine body, two fixing columns are fixedly connected in the buffer box, a trapezoid block is connected between the fixing columns in a sliding manner, a connecting column is connected to the top of the trapezoid block in a sliding manner, a trapezoid cover plate is fixedly connected to the top of the connecting column in a sliding manner, the trapezoid cover plate is connected to the inner wall of the buffer box in a sliding manner, a first spring is sleeved on the outer side of the connecting column, and the first spring is fixedly connected between the trapezoid cover plate and the trapezoid block.
Preferably, the inner wall rigid coupling of buffer box has two sleeves, the equal sliding connection of sheathed tube one end has the slip post, the equal rigid coupling of one end of slip post has the triangle piece, the triangle piece all with trapezoidal piece looks adaptation, the bottom inner wall at the buffer box is all established to the triangle piece, the outside of slip post all overlaps and is equipped with the second spring, the equal rigid coupling of second spring is on triangle piece and sleeve pipe.
Preferably, all rigid coupling has the spliced pole on the oar wing, the one end of spliced pole all is connected with the rectangle piece through the round pin axle rotation, the one end of rectangle piece all is connected with the spliced pole through the pivot rotation, four slots have been seted up on the fuselage, the spliced pole all slides in the slot.
Preferably, four limit grooves are formed in the machine body, limit columns are fixedly connected to the paddle wings, and the limit columns are inserted into the limit grooves.
Preferably, two fixing plates are fixedly connected to the paddle wings, the tops of the fixing plates are rotatably connected with rotating blocks through rotating shafts, placing grooves are formed in the machine body, and the rotating blocks are rotatably connected in the placing grooves.
Preferably, the bottom of fuselage has two undercarriage through torsional spring swing joint, one of them the undercarriage is gone up and is connected with the couple through the pivot rotation, the one end card of couple is gone up at another undercarriage, the undercarriage all rigid coupling has the blotter with the outside of couple.
The utility model has the beneficial effects that:
the utility model provides a multi-rotor unmanned aerial vehicle, which is characterized in that a trapezoid block and a triangular block are arranged, so that the multi-rotor unmanned aerial vehicle can fall or collide with an external object easily due to accidental faults when in aerial operation, and therefore, a fuselage and the interior of the fuselage are damaged.
The utility model provides a multi-rotor unmanned aerial vehicle, which is characterized in that a plug post and a limit post are arranged, the multi-rotor unmanned aerial vehicle is convenient to package and carry after being used, the paddle is too long to occupy space and is easy to damage in carrying and transportation, in order to solve the problem of inconvenient carrying of the multi-rotor unmanned aerial vehicle, a rotating block is required to rotate upwards, the rotating block leaves a placing groove, the constraint on the paddle is released, the paddle can be pulled outwards, the paddle drives the plug post, the limit post and the rotating post to move outwards, the limit post leaves the limit groove, the constraint on the paddle is released, the paddle can be rotated, after the rotation degree, the paddle is rotated towards the direction of a machine body to be close, so that the paddle is folded at the side of the machine body, the space volume is reduced, and the function of the multi-rotor unmanned aerial vehicle is convenient to carry is realized.
Drawings
The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this application, illustrate embodiments of the utility model and together with the description serve to explain the utility model and do not constitute a limitation on the utility model. In the drawings:
FIG. 1 is a perspective view of the present utility model;
FIG. 2 is a perspective view of the interior of the surge tank of the present utility model;
figure 3 is a perspective view of a rotor of the present utility model;
FIG. 4 is a perspective view of a post according to the present utility model;
FIG. 5 is a perspective view of a limiting groove in the utility model;
FIG. 6 is a perspective view of the landing gear of the present utility model;
legend description:
1. a body; 2. a paddle wing; 3. a paddle; 4. a buffer box; 5. a trapezoidal cover plate; 6. a connecting column; 7. a first spring; 8. a trapezoid block; 9. a sleeve; 10. a sliding column; 11. a second spring; 12. triangular blocks; 13. inserting a column; 14. a limit column; 15. a fixing plate; 16. a rotating block; 17. rotating the column; 18. a placement groove; 19. a slot; 20. a limit groove; 21. landing gear; 22. a hook; 23. fixing the column; 24. rectangular blocks.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Specific examples are given below.
Referring to fig. 1-6, the present utility model provides a multi-rotor unmanned aerial vehicle, which comprises a machine body 1, wherein four blades 2 are arranged on the machine body 1, blades 3 are respectively arranged on the blades 2, a buffer box 4 is fixedly connected to the top of the machine body 1, two fixing columns 23 are fixedly connected to the buffer box 4, a trapezoid block 8 is slidingly connected between the fixing columns 23, a connecting column 6 is slidingly connected to the top of the trapezoid block 8, a trapezoid cover plate 5 is fixedly connected to the top of the connecting column 6, the trapezoid cover plate 5 is slidingly connected to the inner wall of the buffer box 4, a first spring 7 is sleeved on the outer side of the connecting column 6, and the first spring 7 is fixedly connected between the trapezoid cover plate 5 and the trapezoid block 8.
During operation, many rotor unmanned aerial vehicle can occasional trouble when aerial operation, easily lead to many rotor unmanned aerial vehicle to fall or strike foreign object to fuselage 1 and inside impaired, for solving the problem that fuselage 1 does not have fine safeguard function and can't reach the effect of protecting fuselage 1 internals, when many rotor unmanned aerial vehicle runs into the trouble, if the back lands, trapezoidal apron 5 is oppressed, trapezoidal apron 5 oppression spliced pole 6, under the effect of first spring 7, spliced pole 6 slides in trapezoidal piece 8 for the striking obtains once buffering, has realized the buffering protect function to fuselage 1.
Further, as shown in fig. 2, two sleeves 9 are fixedly connected to the inner wall of the buffer box 4, one ends of the sleeves 9 are all slidably connected with sliding columns 10, one ends of the sliding columns 10 are all fixedly connected with triangular blocks 12, the triangular blocks 12 are all matched with the trapezoidal blocks 8, the triangular blocks 12 are all arranged on the inner wall of the bottom of the buffer box 4, second springs 11 are all sleeved on the outer sides of the sliding columns 10, and the second springs 11 are all fixedly connected to the triangular blocks 12 and the sleeves 9.
During operation, the connecting column 6 is moved downwards and simultaneously presses the trapezoid block 8, the trapezoid block 8 is moved downwards, the trapezoid block 8 presses the triangular block 12 to move in the opposite direction, the triangular block 12 presses the sliding column 10, and the sliding column 10 slides in the sleeve 9 under the action of the second spring 11, so that the impact is secondarily buffered, and the problem that the fuselage 1 cannot achieve the effect of protecting the internal parts of the fuselage 1 due to the fact that the fuselage 1 does not have a good protection function is solved.
Further, as shown in fig. 4, the rotor blades 2 are fixedly connected with rotating columns 17, one ends of the rotating columns 17 are rotatably connected with rectangular blocks 24 through pins, one ends of the rectangular blocks 24 are rotatably connected with inserting columns 13 through rotating shafts, four slots 19 are formed in the machine body 1, and the inserting columns 13 slide in the slots 19.
During operation, many rotor unmanned aerial vehicle is after using, need packing portable, the too long occupation space of oar wing 2 and carry the easy impaired in the transportation, for the inconvenient many rotor unmanned aerial vehicle's of carrying problem of solution, outwards pull oar wing 2, oar wing 2 drives inserting post 13, spacing post 14 and rotation post 17 outward movement, spacing post 14 leaves spacing groove 20, release the constraint to oar wing 2, can rotate oar wing 2, rotatory 90 degrees back is close to oar wing 2 to fuselage 1 direction rotation, so oar wing 2 all draws in fuselage 1 side, reduce the space volume, realize conveniently carrying many rotor unmanned aerial vehicle's function.
Further, as shown in fig. 5, four limiting grooves 20 are formed in the machine body 1, and the blade 2 is fixedly connected with limiting columns 14, and the limiting columns 14 are inserted into the limiting grooves 20.
In operation, the limiting post 14 is inserted into the limiting groove 20 to stabilize the blade 2 against rotation.
Further, as shown in fig. 3, two fixing plates 15 are fixedly connected to the blade 2, the top of each fixing plate 15 is rotatably connected with a rotating block 16 through a rotating shaft, the machine body 1 is provided with a placing groove 18, and the rotating blocks 16 are rotatably connected in the placing groove 18.
When the propeller 2 is pulled during operation, the rotating block 16 needs to be rotated upwards, the rotating block 16 leaves the placing groove 18, and the constraint on the propeller 2 is released; the rotating block 16 is rotated downwards, the placing groove 18 is inserted into the rotating block 16, and the rotating block 16 fixes the paddle wings 2.
Further, as shown in fig. 6, the bottom of the body 1 is movably connected with two landing gears 21 through a torsion spring, one of the landing gears 21 is rotatably connected with a hook 22 through a rotating shaft, one end of the hook 22 is clamped on the other landing gear 21, and the landing gears 21 and the outer sides of the hooks 22 are fixedly connected with buffer cushions.
In operation, if the belly lands, the buffer pad of the landing gear 21 is firstly contacted with the ground, so that the belly-mounted camera is well protected, and the landing gear 21 is twisted by the torsion spring connection when the belly-mounted camera collides with the ground, so that the landing gear is prevented from being broken by collision.
Working principle: when the multi-rotor unmanned aerial vehicle works in the air, accidental faults can be caused, the multi-rotor unmanned aerial vehicle is easy to fall or collide with foreign objects, so that the fuselage 1 and the interior of the fuselage are damaged, in order to solve the problem that the fuselage 1 cannot achieve the effect of protecting the internal parts of the fuselage 1 due to the fact that the good protection function is not achieved, when the multi-rotor unmanned aerial vehicle encounters faults, if the multi-rotor unmanned aerial vehicle falls on the ground on the back, the trapezoidal cover plate 5 is pressed, the trapezoidal cover plate 5 presses the connecting column 6, under the action of the first spring 7, the connecting column 6 slides in the trapezoidal block 8, so that the collision is buffered once, meanwhile, the connecting column 6 presses the trapezoidal block 8 in the downward motion, the trapezoidal block 8 moves downwards, the triangular block 8 presses the triangular block 12 to move in the opposite direction, the triangular block 12 presses the sliding column 10, and under the action of the second spring 11, the sliding column 10 slides in the sleeve 9, so that the collision is buffered for the second time, the buffer protection function of the fuselage 1 is achieved, if the landing is on the abdomen, the buffer pad of the landing gear 21 contacts the ground firstly, the good protection function is achieved, and the problem that the camera mounted on the abdomen cannot achieve the effect of protecting the internal parts of the fuselage 1 due to the fact that the fuselage 1 does not have the good protection function is achieved; after the multi-rotor unmanned aerial vehicle is used, the multi-rotor unmanned aerial vehicle needs to be packaged and portable, the paddle wings 2 occupy space too long and are easy to damage in carrying and transporting, in order to solve the problem of inconvenient carrying of the multi-rotor unmanned aerial vehicle, the rotating blocks 16 need to be rotated upwards, the rotating blocks 16 leave the placing grooves 18, the constraint on the paddle wings 2 is relieved, the paddle wings 2 can be pulled outwards, the paddle wings 2 drive the inserting posts 13, the limiting posts 14 and the rotating posts 17 to move outwards, the limiting posts 14 leave the limiting grooves 20, the constraint on the paddle wings 2 is relieved, the paddle wings 2 can be rotated, after the paddle wings 2 are rotated for 90 degrees, the paddle wings 2 are rotated towards the direction of the machine body 1 to be close, so that the paddle wings 2 are all folded on the side of the machine body 1, the space volume is reduced, and the function of conveniently carrying the multi-rotor unmanned aerial vehicle is realized.
The foregoing has shown and described the basic principles, principal features and advantages of the utility model. It will be understood by those skilled in the art that the present utility model is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present utility model, and various changes and modifications may be made without departing from the spirit and scope of the utility model, which is defined in the appended claims.
Claims (6)
1. Many rotor unmanned aerial vehicle, its characterized in that: including fuselage (1), be equipped with four oar wings (2) on fuselage (1), paddle wing (2) are gone up and are all installed paddle (3), the top rigid coupling of fuselage (1) has buffer box (4), the rigid coupling has two fixed columns (23) in buffer box (4), sliding connection has trapezoidal piece (8) between fixed column (23), the top rigid coupling of trapezoidal piece (8) has spliced pole (6), the top sliding connection of spliced pole (6) has trapezoidal apron (5), trapezoidal apron (5) sliding connection is on the inner wall of buffer box (4), the outside cover of spliced pole (6) is equipped with first spring (7), first spring (7) rigid coupling is between trapezoidal apron (5) and trapezoidal piece (8).
2. The multi-rotor unmanned aerial vehicle of claim 1, wherein: the inner wall rigid coupling of buffer box (4) has two sleeve pipes (9), the equal sliding connection of one end of sleeve pipe (9) has slip post (10), the one end of slip post (10) all rigid coupling has triangle piece (12), triangle piece (12) all with trapezoidal piece (8) looks adaptation, the bottom inner wall at buffer box (4) is all established to triangle piece (12), the outside of slip post (10) all overlaps and is equipped with second spring (11), second spring (11) all rigid coupling is on triangle piece (12) and sleeve pipe (9).
3. The multi-rotor unmanned aerial vehicle of claim 2, wherein: the utility model discloses a rotor blade, including oar wing (2), rotor blade, plug and frame, all rigid coupling has rotation post (17) on oar wing (2), the one end of rotation post (17) all is connected with rectangle piece (24) through the round pin axle rotation, the one end of rectangle piece (24) all is connected with plug and frame (13) through the pivot rotation, four slot (19) have been seted up on fuselage (1), plug and frame (13) all slide in slot (19).
4. A multi-rotor unmanned aerial vehicle according to claim 3, wherein: four limit grooves (20) are formed in the machine body (1), limit columns (14) are fixedly connected to the paddle wings (2), and the limit columns (14) are inserted into the limit grooves (20).
5. The multi-rotor unmanned aerial vehicle of claim 4, wherein: two fixed plates (15) are fixedly connected to each paddle wing (2), rotating blocks (16) are connected to the tops of the fixed plates (15) through rotating shafts, placing grooves (18) are formed in the machine body (1), and the rotating blocks (16) are connected in the placing grooves (18) in a rotating mode.
6. The multi-rotor unmanned aerial vehicle of claim 5, wherein: the bottom of fuselage (1) is through torsional spring swing joint has two undercarriage (21), and one of them is connected with couple (22) through the pivot rotation on undercarriage (21), the one end card of couple (22) is on another undercarriage (21), the outside of undercarriage (21) and couple (22) all rigid coupling has the blotter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321879518.8U CN220263086U (en) | 2023-07-17 | 2023-07-17 | Multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321879518.8U CN220263086U (en) | 2023-07-17 | 2023-07-17 | Multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220263086U true CN220263086U (en) | 2023-12-29 |
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ID=89318889
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321879518.8U Active CN220263086U (en) | 2023-07-17 | 2023-07-17 | Multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220263086U (en) |
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2023
- 2023-07-17 CN CN202321879518.8U patent/CN220263086U/en active Active
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