CN210912864U - Many rotor unmanned aerial vehicle shock attenuation undercarriage - Google Patents
Many rotor unmanned aerial vehicle shock attenuation undercarriage Download PDFInfo
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- CN210912864U CN210912864U CN201921553033.3U CN201921553033U CN210912864U CN 210912864 U CN210912864 U CN 210912864U CN 201921553033 U CN201921553033 U CN 201921553033U CN 210912864 U CN210912864 U CN 210912864U
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Abstract
The utility model discloses a many rotor unmanned aerial vehicle shock attenuation undercarriage, including the install bin, the installation cover has all been welded to four sides of install bin bottom outer wall, and four installation cover bottom inner walls all are connected with damper, four damper bottom outer wall has two bases through the bolt fastening respectively, install bin top outer wall passes through the bolt fastening organism, damper includes the sleeve pipe, and sheathed tube both sides inner wall sliding connection has same support column, sleeve pipe bottom inner wall has the electro-magnet through the bolt fastening, the mounting groove has been seted up to support column bottom outer wall. The utility model discloses a cooperation of spring, magnet and electro-magnet in the damper can cushion the impact force when unmanned aerial vehicle descends, and the cooperation through fixed epaxial sliding sleeve and second spring further helps unmanned aerial vehicle to carry out the shock attenuation, has solved current unmanned aerial vehicle undercarriage simple structure, and the landing impact force is big, the poor problem of stationarity that rises and falls.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to a many rotor unmanned aerial vehicle shock attenuation undercarriage.
Background
Unmanned aerial vehicle is abbreviated as UAV and refers to an aircraft which does not carry an operator and can fly autonomously or be driven by remote control. A multi-rotor unmanned aerial vehicle is a special unmanned helicopter with three or more rotor shafts. It is rotated by a motor on each shaft, driving the rotor, thereby generating lift. The collective pitch of the rotors is fixed and not variable as in a typical helicopter. Through changing the relative speed between the different rotors, the size of unipolar propulsive force can be changed to the orbit of control aircraft.
The existing landing gear of the multi-rotor unmanned aerial vehicle has a general damping effect, the impact force of the unmanned aerial vehicle is great when the unmanned aerial vehicle descends, and the parts in the unmanned aerial vehicle are easily damaged.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the shortcoming that exists among the prior art, and the many rotor unmanned aerial vehicle shock attenuation undercarriage that proposes.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the utility model provides a many rotor unmanned aerial vehicle shock attenuation undercarriage, includes the install bin, the installation cover has all been welded to four sides of install bin bottom outer wall, and four installation cover bottom inner walls all are connected with damper, four damper bottom outer walls are respectively there are two bases through the bolt fastening, install bin top outer wall passes through the bolt fastening organism, damper includes the sleeve pipe, and sheathed tube both sides inner wall sliding connection has same support column, sleeve pipe bottom inner wall has the electro-magnet through the bolt fastening, the mounting groove has been seted up to support column bottom outer wall, and the bottom inner wall of mounting groove has magnet through the bolt fastening, electro-magnet top outer wall has first spring through the bolt fastening, and first spring top outer wall passes through the bolt fastening on support column bottom outer wall.
Preferably, two the both ends of the relative one side outer wall of base all have the fixed axle through the bolt fastening, and four sliding sleeves have all been cup jointed to the outer wall of two fixed axles.
Preferably, the outer walls of the two fixed shafts are sleeved with second springs, and the two second springs are connected to the four sliding sleeves respectively.
Preferably, four the outer wall of one side of installation cover all articulates there is the connecting rod, and four connecting rods.
Preferably, one end of each of the four connecting rods is hinged to the outer wall of each of the four sliding sleeves.
Preferably, two rectangle mounting grooves have all been seted up to base bottom outer wall, and the inner wall of two rectangle mounting grooves all is fixed with the roller through the bearing.
Preferably, the electromagnet is connected with a switch through a lead, and the switch is connected with a microprocessor through a lead.
The utility model has the advantages that:
1. this many rotor unmanned aerial vehicle shock attenuation undercarriage, be provided with four damper through at the install bin bottom outer wall, the electro-magnet circular telegram through damper produces the magnetism that is the same with magnet and deuterogamies the spring, according to the same magnetism repulsion can cushion the impact force when unmanned aerial vehicle descends each other, set up the fixed axle again between two bases, further help unmanned aerial vehicle to carry out the shock attenuation through the cooperation of the sliding sleeve on the fixed axle and second spring, current unmanned aerial vehicle undercarriage simple structure has been solved, it is big that the impact force lands to descend, the poor problem of stationarity that rises and falls.
Drawings
Fig. 1 is a schematic view of a main view structure of a multi-rotor unmanned aerial vehicle shock absorption undercarriage provided by the present invention;
fig. 2 is a schematic structural view of a damping mechanism of a multi-rotor unmanned aerial vehicle damping undercarriage provided by the present invention;
fig. 3 is the utility model provides a base structure schematic diagram of many rotor unmanned aerial vehicle shock attenuation undercarriage.
In the figure: the damping mechanism comprises an installation box 1, an installation box 2, an installation sleeve 3, a damping mechanism 4, a base 5, a fixed shaft 6, a sliding sleeve 7, a second spring 8, a connecting rod 9, a sleeve 10, a support column 11, an electromagnet 12, a first spring 13, a magnet 14 and a roller shaft 15.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
Referring to fig. 1-3, a multi-rotor unmanned plane damping landing gear comprises a mounting box 1, wherein mounting sleeves 3 are welded on four sides of the outer wall of the bottom of the mounting box 1, damping mechanisms 4 are connected with the inner walls of the bottoms of the four mounting sleeves 3, two bases 5 are respectively fixed on the outer walls of the bottoms of the four damping mechanisms 4 through bolts, an organism 2 is fixed on the outer wall of the top of the mounting box 1 through bolts, each damping mechanism 4 comprises a sleeve 10, the inner walls of two sides of each sleeve 10 are slidably connected with a same supporting column 11, an electromagnet 12 is fixed on the inner wall of the bottom of each sleeve 10 through bolts, a mounting groove is formed in the outer wall of the bottom of each supporting column 11, a magnet 14 is fixed on the inner wall of the bottom of each mounting groove through bolts, a first spring 13 is fixed on the outer wall of the top of each electromagnet 12 through bolts, the outer wall of, and four sliding sleeves 7 have all been cup jointed to the outer wall of two fixed axles 6, second spring 8 has all been cup jointed to the outer wall of two fixed axles 6, and two second springs 8 are connected respectively on four sliding sleeves 7, one side outer wall of four installation cover 3 all articulates there is connecting rod 9, and four connecting rod 9, the one end of four connecting rod 9 articulates respectively on the outer wall of four sliding sleeves 7, the rectangle mounting groove has all been seted up to two base 5 bottom outer walls, and the inner wall of two rectangle mounting grooves all is fixed with roller 15 through the bearing, electro-magnet 12 is connected with the switch through the wire, and the switch is connected with microprocessor through the wire.
The working principle is as follows: during the use, 2 oppression install bins 1 of organism when unmanned aerial vehicle descends, 1 oppression damper 4 of install bins, the impact force that unmanned aerial vehicle received is cushioned in the compression of the 13 atress of first spring in the damper 4, produce through 12 circular telegrams of electro-magnet and carry out the shock attenuation with the same magnetism of magnet 14, it has connecting rod 9 to articulate again through 3 outer at the installation cover, promote connecting rod 9 when the installation cover 3 descends, connecting rod 9 promotes sliding sleeve 7 and then the further buffering impact force of compression second spring 8 on fixed axle 6.
The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (7)
1. The damping undercarriage of the multi-rotor unmanned aerial vehicle comprises an installation box (1) and is characterized in that installation sleeves (3) are welded on four sides of the outer wall of the bottom of the installation box (1), damping mechanisms (4) are connected to the inner walls of the bottoms of the four installation sleeves (3), two bases (5) are fixed to the outer walls of the bottoms of the damping mechanisms (4) through bolts respectively, an organism (2) is fixed to the outer wall of the top of the installation box (1) through the bolts, each damping mechanism (4) comprises a sleeve (10), the inner walls of two sides of each sleeve (10) are connected with the same supporting column (11) in a sliding mode, an electromagnet (12) is fixed to the inner wall of the bottom of each sleeve (10) through the bolts, a mounting groove is formed in the outer wall of the bottom of each supporting column (11), a magnet (14) is fixed to the inner wall of the bottom of the, and the outer wall of the top of the first spring (13) is fixed on the outer wall of the bottom of the support column (11) through a bolt.
2. The multi-rotor unmanned aerial vehicle shock absorption undercarriage according to claim 1, wherein two ends of the outer wall of the two bases (5) on the opposite sides are fixed with fixed shafts (6) through bolts, and four sliding sleeves (7) are sleeved on the outer walls of the two fixed shafts (6).
3. The multi-rotor unmanned aerial vehicle shock absorption undercarriage according to claim 2, wherein the two second springs (8) are sleeved on the outer walls of the two fixed shafts (6), and the two second springs (8) are respectively connected to the four sliding sleeves (7).
4. A multi-rotor unmanned aerial vehicle shock absorption landing gear according to claim 1, wherein four of the mounting sleeves (3) are hinged at one outer wall thereof with a connecting rod (9), and four connecting rods (9).
5. A multi-rotor unmanned aerial vehicle shock absorption undercarriage according to claim 4, wherein one end of each of the four links (9) is hinged to the outer wall of each of the four sliding sleeves (7).
6. The damping landing gear for multi-rotor unmanned aerial vehicles according to claim 1, wherein rectangular mounting grooves are formed in the outer walls of the bottoms of the two bases (5), and the inner walls of the two rectangular mounting grooves are fixed with roller shafts (15) through bearings.
7. A multi-rotor unmanned landing gear according to claim 1, wherein the electromagnet (12) is wired to a switch, and the switch is wired to a microprocessor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921553033.3U CN210912864U (en) | 2019-09-18 | 2019-09-18 | Many rotor unmanned aerial vehicle shock attenuation undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921553033.3U CN210912864U (en) | 2019-09-18 | 2019-09-18 | Many rotor unmanned aerial vehicle shock attenuation undercarriage |
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| CN210912864U true CN210912864U (en) | 2020-07-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921553033.3U Active CN210912864U (en) | 2019-09-18 | 2019-09-18 | Many rotor unmanned aerial vehicle shock attenuation undercarriage |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112109885A (en) * | 2020-09-23 | 2020-12-22 | 泊鹭（荆门）飞机有限公司 | Airplane shock absorption undercarriage and installation method thereof |
| CN112678153A (en) * | 2021-01-19 | 2021-04-20 | 刘江 | Magnetic buffering undercarriage for unmanned aerial vehicle |
| CN112849704A (en) * | 2020-12-17 | 2021-05-28 | 深圳晋阳精密模具有限公司 | A carrier for SMT tool |
| CN113022855A (en) * | 2021-04-14 | 2021-06-25 | 江苏航空职业技术学院 | Water intaking device based on many rotor unmanned aerial vehicle |
-
2019
- 2019-09-18 CN CN201921553033.3U patent/CN210912864U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112109885A (en) * | 2020-09-23 | 2020-12-22 | 泊鹭（荆门）飞机有限公司 | Airplane shock absorption undercarriage and installation method thereof |
| CN112849704A (en) * | 2020-12-17 | 2021-05-28 | 深圳晋阳精密模具有限公司 | A carrier for SMT tool |
| CN112678153A (en) * | 2021-01-19 | 2021-04-20 | 刘江 | Magnetic buffering undercarriage for unmanned aerial vehicle |
| CN112678153B (en) * | 2021-01-19 | 2023-12-05 | 中天航科(山东)航空科技有限责任公司 | Magnetic force buffering undercarriage for unmanned aerial vehicle |
| CN113022855A (en) * | 2021-04-14 | 2021-06-25 | 江苏航空职业技术学院 | Water intaking device based on many rotor unmanned aerial vehicle |
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