CN116513451A - Folding unmanned aerial vehicle undercarriage - Google Patents
Folding unmanned aerial vehicle undercarriage Download PDFInfo
- Publication number
- CN116513451A CN116513451A CN202310371628.1A CN202310371628A CN116513451A CN 116513451 A CN116513451 A CN 116513451A CN 202310371628 A CN202310371628 A CN 202310371628A CN 116513451 A CN116513451 A CN 116513451A
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- CN
- China
- Prior art keywords
- aerial vehicle
- unmanned aerial
- buffer
- vehicle body
- landing gear
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 241000251730 Chondrichthyes Species 0.000 claims abstract description 6
- 238000013016 damping Methods 0.000 claims description 12
- 230000006835 compression Effects 0.000 claims description 6
- 238000007906 compression Methods 0.000 claims description 6
- 239000002184 metal Substances 0.000 abstract description 3
- 238000001179 sorption measurement Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 9
- 239000011324 bead Substances 0.000 description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 230000005389 magnetism Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/001—Devices not provided for in the groups B64C25/02 - B64C25/68
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vehicle Body Suspensions (AREA)
Abstract
The invention discloses a folding type unmanned aerial vehicle landing gear, which comprises a supporting rod distributed along the periphery of an unmanned aerial vehicle body, wherein a sleeve is arranged on the outer side of the supporting rod, the sleeve is of a shark fin structure, the sleeve is rotationally connected with the unmanned aerial vehicle body through a hinge piece, a buffer assembly is arranged at the bottom end of the supporting rod, the buffer assembly is rotationally connected with the supporting rod through a rotating block, an electromagnet is arranged on the rotating block, a metal sheet matched with the electromagnet for adsorption is arranged on the buffer assembly, the buffer assembly comprises a buffer column and a buffer wheel, a bottom plate is arranged at the bottom of the buffer column, and the buffer wheel is rotationally connected with the bottom plate. The folding type unmanned aerial vehicle landing gear provided by the invention has the advantages that the stable landing of an unmanned aerial vehicle is ensured, meanwhile, the air flow resistance is effectively reduced, the precision is high, the occupied area is small, and the practicability is strong.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle landing gears, in particular to a folding unmanned aerial vehicle landing gear.
Background
The unmanned aerial vehicle is an aircraft which does not need any manual driving operation of a driver to carry out boarding, can automatically complete all flight processes under the monitoring of electronic equipment, and the appearance of the unmanned aerial vehicle makes the research of various countries on the aircraft enter a brand-new era. The unmanned aerial vehicle has the advantages of strong survivability, high flexibility, good maneuverability, very convenient use, zero casualty risk and the like, can play an extremely important role in modern war, and has very wide application prospect in civil and commercial fields.
The landing place of the unmanned aerial vehicle has certain requirements, and due to low operation accuracy and inaccurate landing posture, the unmanned aerial vehicle has larger impact force when landing, so that the unmanned aerial vehicle body is easy to topple, further the wings or the body are damaged, and the unmanned aerial vehicle is not beneficial to landing safely.
The unmanned aerial vehicle undercarriage is a part of the bottom of the unmanned aerial vehicle for supporting the unmanned aerial vehicle during take-off and landing or on the ground. The unmanned aerial vehicle undercarriage is an important part for supporting the whole unmanned aerial vehicle and is an indispensable part of the unmanned aerial vehicle.
In the prior art, the landing gear of the unmanned aerial vehicle can reduce vibration to the machine body and stabilize the flight control working environment. However, when the unmanned aerial vehicle with larger mass falls, under the action of larger impact force, a large recoil force can be caused to the landing gear, and even the structure of the unmanned aerial vehicle is seriously damaged. Longer undercarriage makes unmanned aerial vehicle inconvenient in flight easily, makes unmanned aerial vehicle damage easily when flying in narrow and small space, and the air current resistance when great undercarriage increases the flight easily is inconvenient for unmanned aerial vehicle to fly steadily. Therefore, there is an urgent need for a folding unmanned aerial vehicle landing gear that solves the above-mentioned problems.
Disclosure of Invention
The invention aims to provide a folding type unmanned aerial vehicle landing gear, which can effectively reduce air flow resistance, has high accuracy, small occupied area and strong practicability while ensuring stable landing of an unmanned aerial vehicle.
In order to achieve the above purpose, the invention provides a folding type unmanned aerial vehicle landing gear, which comprises a supporting rod distributed along the periphery of an unmanned aerial vehicle body, wherein a sleeve is arranged on the outer side of the supporting rod, the sleeve is of a shark fin structure, the sleeve is rotationally connected with the unmanned aerial vehicle body through a hinging piece, a buffer assembly is arranged at the bottom end of the supporting rod, the buffer assembly is rotationally connected with the supporting rod through a rotating block, an electromagnet is arranged on the rotating block, a metal sheet matched with the electromagnet for adsorption is arranged on the buffer assembly, the buffer assembly comprises a buffer column and a buffer wheel, a bottom plate is arranged at the bottom of the buffer column, and the buffer wheel is rotationally connected with the bottom plate.
Preferably, the hinge piece includes disc damping pivot and set up in fixed block on the unmanned aerial vehicle body, the upper end of disc damping pivot with fixed block fixed connection, the lower extreme of disc damping pivot through a plurality of gaskets with telescopic top rotates to be connected, the bracing piece runs through the bearing telescopic bottom.
Preferably, the buffer column comprises a piston rod and a compression spring sleeved on the outer wall of the piston rod, a gear is arranged at the upper end of the piston rod, the center of the gear is rotationally connected with the rotating block, and the lower end of the piston rod is fixedly connected with the bottom plate.
Preferably, the buffer wheel comprises a sector wheel and a rubber layer arranged along a sector ring of the sector wheel, two sides of the sector wheel are respectively provided with an automatic telescopic rod perpendicular to the edges of the sector wheel, the other end of the automatic telescopic rod is fixedly connected with the bottom plate, and the central angle of the sector wheel is rotationally connected with the bottom plate through a rotating shaft.
Preferably, the rotating block is of a hollow structure, a rack is arranged in the rotating block, a thin air cylinder is arranged at one end of the rack, the other end of the rack is meshed with the gear, and the length of the rack is smaller than half of the circumference of the gear.
Preferably, the unmanned aerial vehicle body is last still to be equipped with infrared LED lamp pearl, be equipped with range sensor on the bracing piece.
Preferably, the thin cylinder and the electromagnet are electrically connected with the unmanned aerial vehicle body.
Preferably, each buffer assembly takes the rotating block as an axial direction and rotates clockwise around the unmanned aerial vehicle body.
Therefore, the folding type unmanned aerial vehicle landing gear has the following technical effects:
(1) The invention adopts the sleeve with the shark fin structure, automatically rotates in the flight process, and the streamline structure can cut vortex, reduce the air flow resistance in the unmanned aerial vehicle flight process and improve the flight speed.
(2) The folding type buffer assembly is adopted, and the free folding structure is adopted, so that the occupied area of the unmanned aerial vehicle can be reduced, the unmanned aerial vehicle can smoothly pass through a small space, and the unmanned aerial vehicle can be stored and maintained conveniently.
(3) The invention adopts the structure of combining the buffer column and the buffer wheel, can lighten the impact force of the unmanned aerial vehicle in the whole aspect, has high stability and avoids the phenomenon that the unmanned aerial vehicle leans forward or even overturns.
(4) According to the invention, the distance measuring sensor is matched with the infrared LED lamp to accurately land, so that the operation accuracy is further improved, the landing posture is ensured to be accurate, and the unmanned aerial vehicle is prevented from landing position deviation and damage to the wing or the airframe.
The technical scheme of the invention is further described in detail through the drawings and the embodiments.
Drawings
FIG. 1 is a schematic structural view of an embodiment of a folding unmanned aerial vehicle landing gear of the present invention;
FIG. 2 is a bottom view of a folded state of an embodiment of a folding unmanned aerial vehicle landing gear of the present invention;
fig. 3 is a schematic view of the structure of a turning block of an embodiment of a landing gear of a folding unmanned aerial vehicle according to the present invention.
Reference numerals
1. An unmanned aerial vehicle body; 2. a support rod; 3. a sleeve; 4. a disc damping rotating shaft; 5. a fixed block; 6. a bearing; 7. a rotating block; 8. an electromagnet; 9. a metal sheet; 10. a rack; 11. a bottom plate; 12. a piston rod; 13. a compression spring; 14. a gear; 15. a sector wheel; 16. a rubber layer; 17. an automatic telescopic rod; 18. a rotating shaft; 19. a thin cylinder; 20. an infrared LED lamp bead; 21. a distance measuring sensor.
Detailed Description
The technical scheme of the invention is further described below through the attached drawings and the embodiments.
Unless defined otherwise, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this invention belongs. The terms "first," "second," and the like, as used herein, do not denote any order, quantity, or importance, but rather are used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that elements or items preceding the word are included in the element or item listed after the word and equivalents thereof, but does not exclude other elements or items. The terms "connected" or "connected," and the like, are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "upper", "lower", "left", "right", etc. are used merely to indicate relative positional relationships, which may also be changed when the absolute position of the object to be described is changed.
As shown in fig. 1, a folding unmanned aerial vehicle undercarriage includes bracing piece 2 that lays all around along unmanned aerial vehicle body 1, and the outside of bracing piece 2 is equipped with sleeve 3, and sleeve 3 is the shark's fin structure, and sleeve 3 rotates with unmanned aerial vehicle body 1 through the hinge and is connected. The hinge piece includes disc damping pivot 4 and sets up fixed block 5 on unmanned aerial vehicle body 1, and the upper end and the fixed block 5 fixed connection of disc damping pivot 4, and the lower extreme of disc damping pivot 4 is rotated with the top of sleeve 3 through a plurality of gaskets and is connected, and bracing piece 2 runs through the bottom of sleeve 3 through bearing 6. The supporting rod 2 and the sleeve 3 are made of carbon fiber materials, and have high strength and light weight.
The disc damping rotating shaft 4 generates friction force through the extrusion between the gaskets, and in the flying process, wind resistance drives the disc damping rotating shaft 4 to rotate for a certain angle without shaking, namely, the sleeve 3 is driven to rotate for a certain angle. Make unmanned aerial vehicle body 1 change the flight direction anyway, sleeve 3's shark fin formula streamline structure changes along with the wind direction all the time, can cut the vortex, reduce unmanned aerial vehicle body 1's air current resistance, improve the flight speed.
The bottom of bracing piece 2 is equipped with buffer assembly, and buffer assembly rotates through rotating piece 7 and bracing piece 2 to be connected, is equipped with electro-magnet 8 on the rotating piece 7, is equipped with on buffer assembly's the outer wall with electro-magnet 8 matched with absorptive sheetmetal 9, electro-magnet 8 and unmanned aerial vehicle body 1 electric connection, the accessible mobile terminal changes the intensity of electric current to control electro-magnet 8's magnetism size, guarantee that sheetmetal 9 and electro-magnet 8's cooperatees or separate, make buffer assembly rotate back and tightly laminate rotating piece 7, reach the locking state.
The buffer assembly comprises a buffer column and a buffer wheel, the bottom of the buffer column is provided with a bottom plate 11, and the buffer wheel is rotationally connected with the bottom plate 11. Specifically, the buffering post includes piston rod 12 and the compression spring 13 of suit in the outer wall of piston rod 12, and the upper end of piston rod 12 is equipped with gear 14, and the lower extreme and the bottom plate 11 fixed connection of piston rod 12. The buffer wheel comprises a sector wheel 15 and a rubber layer 16 arranged along a sector ring of the sector wheel 15, two sides of the sector wheel 15 are respectively provided with an automatic telescopic rod 17 perpendicular to the sides of the sector wheel 15, the other end of the automatic telescopic rod 17 is fixedly connected with the bottom plate 11, and the central angle of the sector wheel 15 is rotationally connected with the bottom plate 11 through a rotating shaft 18.
The rubber layer 16 of the sector wheel 15 is grounded, a vertically upward recoil force is generated and transmitted to the base plate 11 through the sector wheel 15, and finally acts on the piston rod 12 of the buffer column and the compression spring 13, and gradually decompresses under the action of the compression spring 13. Meanwhile, the sector wheel 15 also has a friction recoil force in a counterclockwise direction, the sector wheel 15 is driven to rotate counterclockwise, and under the combined action of the automatic telescopic rods 17 at the two sides of the sector wheel 15, the sector wheel 15 slowly returns to the original position after rotating counterclockwise, so that the impact force caused by forward tilting is greatly reduced.
The center of the gear 14 is rotationally connected with the rotating block 7, and the rotating block 7 is of a hollow structure. As shown in fig. 3, a rack 10 is provided in the rotating block 7, one end of the rack 10 is provided with a thin air cylinder 19, and the thin air cylinder 19 is electrically connected with the unmanned aerial vehicle body 1. The other end of the rack 10 is meshed with the gear 14, and the length of the rack 10 is smaller than half the circumference of the gear 14, so that the rotation angle of the gear 14 is ensured not to exceed 180 degrees. The thin air cylinder 19 drives the rack 10 to move, and simultaneously the gear 14 rotates to drive the piston rod 12 to rotate to a preset angle. As shown in fig. 2, each buffer assembly is driven to rotate clockwise around the unmanned aerial vehicle body 1 to a preset angle by taking the rotating block 7 as an axial direction. The landing gear folding and unfolding and free retraction structure during flight are realized. Reduce the impact force of landing, simultaneously, further reduce the influence of air resistance to unmanned aerial vehicle body 1, be convenient for unmanned aerial vehicle body 1 pass through some narrow and small spaces.
The unmanned aerial vehicle body 1 is further provided with an infrared LED lamp bead 20, the supporting rod 2 is provided with a ranging sensor 21, and the ranging sensor 21 is a ranging sensor in the Y-axis direction. The infrared light source of the infrared LED lamp beads 20 is identified to be combined with the Y-axis ranging sensor 21 for accurate positioning, so that the unmanned aerial vehicle body 1 can accurately land. In addition, visual recognition can be performed in daytime or at night, and accurate tracking of an infrared light source within a distance of 20m can be achieved at the maximum.
In the actual use process, the thin air cylinder 19 and the electromagnet 8 are electrically connected with the unmanned aerial vehicle body 1, the mobile terminal controls the thin air cylinder 19 to drive the rack 10 to move, so that the buffer assembly rotates, the landing gear is in a folded state, the current of the electromagnet 8 is increased, the electromagnet is in a locking state, and the air resistance is reduced in the flying process; when the unmanned aerial vehicle falls, the current of the electromagnet 8 is reduced, the buffer assembly is in an unlocking state, the thin type air cylinder 19 is controlled by the mobile terminal to drive the rack 10 to move reversely, the buffer assembly is unfolded, the impact force of landing can be reduced, and the unmanned aerial vehicle is prevented from overturning and damaging the machine body.
During the unmanned aerial vehicle storage process, the thin type air cylinder 19 can be controlled by the mobile terminal again to drive the rack 10 to move, so that the buffer assembly rotates, and the landing gear is in a folded state. The unmanned aerial vehicle automatically keeps a folded state without increasing the current of the electromagnet 8. The power supply is turned off, the storage of the unmanned aerial vehicle is not affected, and the power supply is turned on again in the next use process.
Therefore, the folding type unmanned aerial vehicle landing gear effectively reduces the air flow resistance in the unmanned aerial vehicle flight process, improves the flight speed, ensures accurate landing posture and high precision, ensures that the unmanned aerial vehicle stably lands, and has small occupied area during storage and strong practicability.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention and not for limiting it, and although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that: the technical scheme of the invention can be modified or replaced by the same, and the modified technical scheme cannot deviate from the spirit and scope of the technical scheme of the invention.
Claims (8)
1. A foldable unmanned aerial vehicle undercarriage, its characterized in that: including the bracing piece of laying all around along the unmanned aerial vehicle body, the outside of bracing piece is equipped with the sleeve, the sleeve is shark's fin type structure, the sleeve with the unmanned aerial vehicle body rotates through the hinge and is connected, the bottom of bracing piece is equipped with buffer assembly, buffer assembly pass through the rotating block with the bracing piece rotates to be connected, be equipped with the electro-magnet on the rotating block, be equipped with on the buffer assembly with the electro-magnet cooperatees absorptive sheetmetal, buffer assembly includes the buffer post and buffer wheel, the bottom of buffer post is equipped with the bottom plate, the buffer wheel with the bottom plate rotates to be connected.
2. The folding unmanned aerial vehicle landing gear of claim 1, wherein: the hinge piece include disc damping pivot and set up in fixed block on the unmanned aerial vehicle body, the upper end of disc damping pivot with fixed block fixed connection, the lower extreme of disc damping pivot through a plurality of gaskets with telescopic top rotates to be connected, the bracing piece runs through the bearing telescopic bottom.
3. The folding unmanned aerial vehicle landing gear of claim 1, wherein: the buffer column comprises a piston rod and a compression spring sleeved on the outer wall of the piston rod, a gear is arranged at the upper end of the piston rod, the center of the gear is rotationally connected with the rotating block, and the lower end of the piston rod is fixedly connected with the bottom plate.
4. The folding unmanned aerial vehicle landing gear of claim 1, wherein: the buffer wheel comprises a sector wheel and a rubber layer arranged along a sector ring of the sector wheel, two sides of the sector wheel are respectively provided with an automatic telescopic rod perpendicular to the sides of the sector wheel, the other end of the automatic telescopic rod is fixedly connected with the bottom plate, and the central angle of the sector wheel is rotationally connected with the bottom plate through a rotating shaft.
5. The folding unmanned aerial vehicle landing gear of claim 1, wherein: the rotating block is of a hollow structure, a rack is arranged in the rotating block, a thin air cylinder is arranged at one end of the rack, the other end of the rack is meshed with the gear, and the length of the rack is smaller than half of the circumference of the gear.
6. The folding unmanned aerial vehicle landing gear of claim 1, wherein: still be equipped with infrared LED lamp pearl on the unmanned aerial vehicle body, be equipped with range finding sensor on the bracing piece.
7. The folding unmanned aerial vehicle landing gear of claim 1, wherein: the thin air cylinder and the electromagnet are electrically connected with the unmanned aerial vehicle body.
8. The folding unmanned aerial vehicle landing gear of claim 1, wherein: each buffer assembly takes the rotating block as an axial direction and rotates clockwise around the unmanned aerial vehicle body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310371628.1A CN116513451A (en) | 2023-04-10 | 2023-04-10 | Folding unmanned aerial vehicle undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310371628.1A CN116513451A (en) | 2023-04-10 | 2023-04-10 | Folding unmanned aerial vehicle undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116513451A true CN116513451A (en) | 2023-08-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310371628.1A Pending CN116513451A (en) | 2023-04-10 | 2023-04-10 | Folding unmanned aerial vehicle undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116513451A (en) |
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