CN220410930U - Unmanned aerial vehicle undercarriage - Google Patents
Unmanned aerial vehicle undercarriage Download PDFInfo
- Publication number
- CN220410930U CN220410930U CN202320018486.6U CN202320018486U CN220410930U CN 220410930 U CN220410930 U CN 220410930U CN 202320018486 U CN202320018486 U CN 202320018486U CN 220410930 U CN220410930 U CN 220410930U
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- China
- Prior art keywords
- unmanned aerial
- aerial vehicle
- connecting plate
- landing gear
- shell
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- 230000000694 effects Effects 0.000 claims abstract description 7
- 230000003139 buffering effect Effects 0.000 claims description 8
- 238000010521 absorption reaction Methods 0.000 claims description 5
- 238000005381 potential energy Methods 0.000 description 12
- 238000000034 method Methods 0.000 description 6
- 230000005484 gravity Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- 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
Abstract
The utility model discloses an unmanned aerial vehicle landing gear, which relates to the technical field of unmanned aerial vehicles and comprises an unmanned aerial vehicle body, wherein a landing gear assembly is arranged at the bottom of the unmanned aerial vehicle body and comprises a shell, the surface of the shell is fixedly connected with the bottom of the unmanned aerial vehicle body, the inner wall of the shell is fixedly connected with a circular shaft, the surface of the circular shaft is movably sleeved with a circular sleeve, the surface of the circular sleeve is fixedly connected with a connecting rod, the surface of the shell is provided with a sliding groove, the surface of the sliding groove is movably connected with the surface of the connecting rod, and the surface of the circular sleeve is fixedly connected with a connecting plate. Through setting up connecting rod, gyro wheel, shell, circle axle, circle cover, connecting block, forward energy-absorbing spring and reverse energy-absorbing spring, reached and reduced the vibrations that undercarriage and ground contact were strikeed in the twinkling of an eye and produced, can protect unmanned aerial vehicle's effect.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle landing gear.
Background
Unmanned aerial vehicle is through radio remote control or self-contained program control flight status, and unmanned aerial vehicle in use can be used for taking photo by plane, rescue, control or survey and drawing etc. when unmanned aerial vehicle drops, be through landing gear to fall to the ground, the instantaneous vibration that falls to the ground produces, so the speed that needs control whereabouts prevents unmanned aerial vehicle's damage in same direction as.
The unmanned aerial vehicle is placed on the ground and is made up through the undercarriage when being on the o-surface, secondly unmanned aerial vehicle also is made up through the undercarriage with the unmanned aerial vehicle support column when the landing, in the moment of unmanned aerial vehicle whereabouts back and ground contact, because unmanned aerial vehicle's self gravity undercarriage has certain striking with ground, and the striking will produce certain vibrations and will transmit unmanned aerial vehicle's inside through the conduction, through above-mentioned mode, unmanned aerial vehicle passes through the undercarriage and can play the effect of supporting, but landing gear and ground contact's the produced striking in the moment lets the undercarriage exist the demand of further optimization.
Disclosure of Invention
The utility model provides an unmanned aerial vehicle landing gear, which has the advantages of reducing vibration generated by the impact of the landing gear in the moment of contact with the ground and protecting the unmanned aerial vehicle so as to solve the problems in the background art.
In order to achieve the purpose of reducing vibration generated by impact between the landing gear and the ground at the moment of contact and protecting the unmanned aerial vehicle, the utility model provides the following technical scheme: the utility model provides an unmanned aerial vehicle undercarriage, includes the unmanned aerial vehicle body, the bottom of unmanned aerial vehicle body is provided with the undercarriage subassembly, the undercarriage subassembly includes the shell, the surface of shell and the bottom fixed connection of unmanned aerial vehicle body, the inner wall fixedly connected with circle axle of shell, the surface activity of circle axle has cup jointed the circle cover, the fixed surface of circle cover has the connecting rod, the spout has been seted up on the surface of shell, the surface swing joint of spout and connecting rod, the fixed surface of circle cover has the connecting plate, the connecting plate activity cup joints the surface at the spacing ring, the spacing ring passes through the inner wall fixed connection of connecting block and shell, the surface activity of spacing ring cup joints forward energy-absorbing spring, forward energy-absorbing spring keeps away from the fixed surface of connecting plate one end and connecting block, forward energy-absorbing spring is close to connecting plate one end and connecting plate's surface swing joint, the tip of connecting plate has the gyro wheel through bearing connection.
The unmanned aerial vehicle landing gear of claim, wherein: the surface of the limiting ring is movably sleeved with a reverse energy-absorbing spring, one end of the reverse energy-absorbing spring, which is far away from the connecting plate, is fixedly connected with the surface of the connecting plate, and the surface of the connecting plate, which is close to one end of the connecting plate, of the reverse energy-absorbing spring is movably connected with the surface of the connecting plate.
The unmanned aerial vehicle landing gear of claim, wherein: the outer shells are arranged in two, and the two outer shells are symmetrically arranged in the middle of the unmanned aerial vehicle body.
The unmanned aerial vehicle landing gear of claim, wherein: the width of the sliding groove is one time of the outer diameter of the connecting rod.
The unmanned aerial vehicle landing gear of claim, wherein: the surface of gyro wheel is provided with buffer assembly, buffer assembly includes the buffering connecting piece, buffering connecting piece fixed connection is at the surface of gyro wheel, the tip fixedly connected with overcoat of buffering connecting piece.
As a preferable technical scheme of the utility model, the outer sleeve is a rubber sleeve, and the surface of the outer sleeve is provided with anti-skid stripes.
Compared with the prior art, the utility model provides the landing gear of the unmanned aerial vehicle, which has the following beneficial effects:
1. this unmanned aerial vehicle undercarriage, through setting up the connecting rod, the gyro wheel, the shell, the circle axle, the circle cover, the connecting block, forward energy-absorbing spring and reverse energy-absorbing spring, when using, when unmanned aerial vehicle body falls to the ground, the gyro wheel will be with ground contact, unmanned aerial vehicle body is because there is a gravitational potential energy's reason, unmanned aerial vehicle body has a decurrent power, unmanned aerial vehicle body decurrent power passes through the shell, circle axle and circle cover will transmit on the connecting rod, the connecting rod will rotate around the circle axle this moment, the connecting rod rotates and will drive the connecting plate and rotate, the connecting plate rotates forward energy-absorbing spring will be compressed, the gravitational potential energy of unmanned aerial vehicle body will not be converted into forward energy-absorbing spring's elastic potential energy, in the time of passing forward energy-absorbing spring rebound, so repeatedly with unmanned aerial vehicle body's gravitational potential energy consumption, the vibrations that like this unmanned aerial vehicle body and ground contact all can be consumed by forward energy-absorbing spring and reverse energy-absorbing spring, the vibrations that unmanned aerial vehicle body received will be less, the vibrations that the landing gear and ground contact in the twinkling of an eye impact produced in the twinkling of an eye have been reached, the effect that can protect the unmanned aerial vehicle.
2. This unmanned aerial vehicle undercarriage through setting up buffer unit, when using, the overcoat can absorb the produced vibrations in the twinkling of an eye with ground contact, and the inside buffer connection spare of overcoat also can absorb vibrations, protects unmanned aerial vehicle body further.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present utility model;
FIG. 2 is a front cross-sectional view of the housing of the present utility model;
FIG. 3 is an enlarged view of FIG. 2A in accordance with the present utility model;
FIG. 4 is a front cross-sectional view of the connection plate of the present utility model;
FIG. 5 is a left side view of the connecting rod of the present utility model;
figure 6 is a front cross-sectional view of the jacket of the present utility model.
In the figure: 1. an unmanned aerial vehicle body; 2. landing gear assembly; 201. a connecting rod; 202. a roller; 203. a housing; 204. a circular shaft; 205. a round sleeve; 206. a connecting block; 207. a limiting ring; 208. a positive energy-absorbing spring; 209. a chute; 210. a reverse energy absorbing spring; 211. a connecting plate; 3. a buffer assembly; 301. a jacket; 302. and a buffer connection.
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.
Referring to fig. 1-6, the utility model discloses an unmanned aerial vehicle landing gear, comprising an unmanned aerial vehicle body 1, a landing gear component 2 is arranged at the bottom of the unmanned aerial vehicle body 1, the landing gear component 2 comprises a housing 203, the surface of the housing 203 is fixedly connected with the bottom of the unmanned aerial vehicle body 1, the inner wall of the housing 203 is fixedly connected with a round shaft 204, the surface of the round shaft 204 is movably sleeved with a round sleeve 205, the round sleeve 205 can be movably connected with the surface of the round shaft 204, the end of the round sleeve 205 is movably connected with the inner wall of the housing 203, the surface of the round sleeve 205 is fixedly connected with a connecting rod 201, the surface of the housing 203 is provided with a sliding groove 209, the surface of the sliding groove 209 is movably connected with the surface of the connecting rod 201, the surface of the round sleeve 205 is fixedly connected with a connecting plate 211, the connecting plate 211 can transmit the forces on a forward energy absorbing spring 208 and a reverse energy absorbing spring 210 to the round sleeve 205, the connecting plate 211 is movably sleeved on the surface of a limit ring 207, the limiting ring 207 is circular in top view cross section, the limiting ring 207 is fixedly connected with the inner wall of the shell 203 through the connecting blocks 206, the limiting ring 207 is fixedly connected with the shell 203 through the two connecting blocks 206, two limiting rings 207 are arranged in the shell 203 at a time, the surface of the limiting ring 207 is movably sleeved with a positive energy-absorbing spring 208, when the unmanned aerial vehicle body 1 descends to contact the ground, the unmanned aerial vehicle body 1 has a downward force due to gravity, the downward force is transmitted to the circular shaft 204 through the shell 203, the circular shaft 204 transmits the force to the circular sleeve 205, the connecting rod 201 is fixed in an inclined manner, the connecting rod 201 rotates around the circular shaft 204 through stress analysis, the connecting rod 201 rotates to drive the connecting plate 211 to rotate, the connecting plate 211 slides on the surface of the limiting ring 207, the positive energy-absorbing spring 208 is compressed during sliding, during compression, downward force is absorbed, the forward energy-absorbing spring 208 converts gravitational potential energy into self elastic potential energy, the forward energy-absorbing spring 208 rebounds to drive the connecting plate 211 to rotate, the connecting plate 211 compresses the reverse energy-absorbing spring 210 at the moment, the elastic potential energy of the forward energy-absorbing spring 208 is absorbed after the reverse energy-absorbing spring 210 is compressed, the reverse energy-absorbing spring 210 rebounds after absorption, so that the gravitational potential energy is repeatedly consumed, one end of the forward energy-absorbing spring 208 far away from the connecting plate 211 is fixedly connected with the surface of the connecting block 206, one end of the forward energy-absorbing spring 208 close to the connecting plate 211 is movably connected with the surface of the connecting plate 211, and the end part of the connecting plate 211 is connected with the roller 202 through a bearing.
Specifically, the surface of the limiting ring 207 is movably sleeved with a reverse energy-absorbing spring 210, one end of the reverse energy-absorbing spring 210, which is far away from the connecting plate 211, is fixedly connected with the surface of the connecting plate 211, and one end of the reverse energy-absorbing spring 210, which is near to the connecting plate 211, is movably connected with the surface of the connecting plate 211 through the connecting plate 211.
In this embodiment, by providing the reverse energy-absorbing spring 210, the reverse energy-absorbing spring 210 and the forward energy-absorbing spring 208 cooperate with each other to consume kinetic energy of the unmanned aerial vehicle body 1 at the landing moment.
Specifically, the number of the two housings 203 is two, and the two housings 203 are symmetrically arranged about the center of the unmanned aerial vehicle body 1.
In this embodiment, two shells 203 are symmetrically arranged in the middle of the unmanned aerial vehicle body 1, so that the forces received by the two sides of the unmanned aerial vehicle body 1 in the instant of landing are relatively stable, and the whole unmanned aerial vehicle body 1 is relatively stable.
Specifically, the width of the chute 209 is one time the outer diameter of the connecting rod 201.
In this embodiment, the width of the sliding groove 209 is one time the outer diameter of the connecting rod 201, so that the connecting rod 201 can slide inside the sliding groove 209 without contacting the sliding groove 209.
Specifically, the surface of the roller 202 is provided with a buffer assembly 3, the buffer assembly 3 comprises a buffer connecting piece 302, the buffer connecting piece 302 is fixedly connected to the surface of the roller 202, and an outer sleeve 301 is fixedly connected to the end portion of the buffer connecting piece 302.
In this embodiment, the outer sleeve 301 contacts the roller 202 via the buffer connection 302, and the buffer connection 302 can absorb the supporting force on the ground, so as to further reduce the overall vibration.
Specifically, the outer sleeve 301 is a rubber sleeve, and the surface of the outer sleeve 301 is provided with anti-slip stripes.
In this embodiment, if the outer sleeve 301 is a rubber sleeve and the surface of the outer sleeve 301 is provided with the anti-slip stripes, the rubber material is softer, so that the anti-slip stripes can absorb the force generated by vibration, and the anti-slip stripes can increase the friction force with the ground, so that the grip of the roller 202 is better.
The working principle and the using flow of the utility model are as follows: when using, when unmanned aerial vehicle body 1 work is accomplished the moment that falls to the ground, overcoat 301 will be with ground contact, overcoat 301 will be the produced vibrations absorption part when contacting, and still the power of a part vibrations will be absorbed by buffer connection spare 302, unmanned aerial vehicle body 1 still has a decurrent gravitational potential energy secondly, the potential energy will be passed on circle axle 204 through shell 203, transfer round cover 205 and connecting rod 201 on next, connecting rod 201 will rotate this moment, connecting rod 201's upper portion will rotate around circle axle 204, and connecting rod 201's bottom rolls subaerial through gyro wheel 202, connecting rod 201 top rotates and will drive circle cover 205 and rotate on circle axle 204 surface, circle cover 205 rotates and will drive connecting block 206 and rotate on spacing ring 207, connecting block 206 downward rotation will be compressed forward energy-absorbing spring 208, unmanned aerial vehicle body 1's gravitational potential energy will be converted into forward energy-absorbing spring 208's elastic potential energy this moment, forward energy-absorbing spring 208 will rebound after the conversion is accomplished, forward energy-absorbing spring 208 will drive 206 upward rotation, connecting block 206 will compress spring 210 again, the kinetic energy-absorbing spring 210 will be rotated on the round axle 204, this time, the unmanned aerial vehicle body's the accurate part 1 can be lost in the human body's of the impact energy-absorbing device, the accurate part 1 can be lost in this moment, this time, the unmanned aerial vehicle body's 1 can be lost in the human body's motion, so on the body's the face is lost, and the human-body's vibration can be recovered.
It should be noted that in this document, terms such as "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. Unmanned aerial vehicle undercarriage, including unmanned aerial vehicle body (1), its characterized in that: the landing gear assembly comprises a landing gear assembly (2) arranged at the bottom of an unmanned aerial vehicle body (1), the landing gear assembly (2) comprises a shell (203), the surface of the shell (203) is fixedly connected with the bottom of the unmanned aerial vehicle body (1), a round shaft (204) is fixedly connected with the inner wall of the shell (203), a round sleeve (205) is movably sleeved on the surface of the round shaft (204), a connecting rod (201) is fixedly connected with the surface of the round sleeve (205), a sliding groove (209) is formed in the surface of the shell (203), a connecting plate (211) is movably connected with the surface of the sliding groove (209), the connecting plate (211) is movably sleeved on the surface of a limiting ring (207), the limiting ring (207) is fixedly connected with the inner wall of the shell (203) through a connecting block (206), a forward energy absorption spring (208) is movably sleeved on the surface of the limiting ring (207), one end of the forward energy absorption spring (208) is far away from the surface fixedly connected with the connecting plate (206), and the surface of the forward energy absorption spring (208) is close to the connecting plate (211) through the connecting plate (211), and the connecting plate (211) is movably connected with the connecting plate (211).
2. The unmanned aerial vehicle landing gear of claim 1, wherein: the surface activity of spacing ring (207) has cup jointed reverse energy-absorbing spring (210), reverse energy-absorbing spring (210) keep away from connecting plate (211) one end and connecting plate (211) surface fixed connection, reverse energy-absorbing spring (210) are close to connecting plate (211) one end connecting plate (211) and connecting plate (211) surface swing joint.
3. The unmanned aerial vehicle landing gear of claim 1, wherein: the number of the outer shells (203) is two, and the two outer shells (203) are symmetrically arranged in the middle of the unmanned aerial vehicle body (1).
4. The unmanned aerial vehicle landing gear of claim 1, wherein: the width of the sliding groove (209) is one time of the outer diameter of the connecting rod (201).
5. The unmanned aerial vehicle landing gear of claim 1, wherein: the surface of gyro wheel (202) is provided with buffering subassembly (3), buffering subassembly (3) are including buffering connecting piece (302), buffering connecting piece (302) fixed connection is at the surface of gyro wheel (202), the tip fixedly connected with overcoat (301) of buffering connecting piece (302).
6. The unmanned aerial vehicle landing gear of claim 5, wherein: the outer sleeve (301) is a rubber sleeve, and anti-skid stripes are arranged on the surface of the outer sleeve (301).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320018486.6U CN220410930U (en) | 2023-01-05 | 2023-01-05 | Unmanned aerial vehicle undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320018486.6U CN220410930U (en) | 2023-01-05 | 2023-01-05 | Unmanned aerial vehicle undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220410930U true CN220410930U (en) | 2024-01-30 |
Family
ID=89643168
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320018486.6U Active CN220410930U (en) | 2023-01-05 | 2023-01-05 | Unmanned aerial vehicle undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220410930U (en) |
-
2023
- 2023-01-05 CN CN202320018486.6U patent/CN220410930U/en active Active
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