CN213384693U - Unmanned aerial vehicle is with frame shock-absorbing structure that plays - Google Patents
Unmanned aerial vehicle is with frame shock-absorbing structure that plays Download PDFInfo
- Publication number
- CN213384693U CN213384693U CN202022453892.4U CN202022453892U CN213384693U CN 213384693 U CN213384693 U CN 213384693U CN 202022453892 U CN202022453892 U CN 202022453892U CN 213384693 U CN213384693 U CN 213384693U
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- aerial vehicle
- unmanned aerial
- disc
- absorbing structure
- strip
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Abstract
The utility model discloses an unmanned aerial vehicle is with having fallen frame shock-absorbing structure, which comprises a roof, the circular slot has been seted up to the centre of roof bottom, and the centre of roof encircles the circular slot equidistance distributes and has a plurality of bar holes, just the one end in bar hole with the circular slot is linked together, be provided with the disc in the circular slot, the diameter of disc is less than the diameter of circular slot, and the outer wall of disc rotates the one end that is connected with the straight-bar, and the other end of straight-bar is inserted and is located in the bar is downthehole, and the straight-bar is located the downthehole one end of bar is connected with the one end of piston, the outer wall of piston with the inner wall sliding connection in bar hole, and. This unmanned aerial vehicle is with frame shock-absorbing structure that rises adopts structural design such as roof, disc, straight-bar, piston, compression spring and chassis for unmanned aerial vehicle can obtain effectual buffering when receiving arbitrary direction's transverse impact, thereby has improved the shock attenuation effect.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle equipment technical field specifically is an unmanned aerial vehicle is with having fallen frame shock-absorbing structure.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other equipment. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar. The aircraft can take off like a common airplane under the radio remote control or launch and lift off by a boosting rocket, and can also be thrown into the air by a mother aircraft for flying. During recovery, the aircraft can land automatically in the same way as the common aircraft landing process, and can also be recovered by a parachute or a barrier net for remote control. Can be repeatedly used for many times. The method is widely used for aerial reconnaissance, monitoring, communication, anti-submergence, electronic interference and the like.
Unmanned aerial vehicle can bump with the ground contact when descending, and huge vibrations can lead to the fact the damage to unmanned aerial vehicle, and unmanned aerial vehicle is descending with oblique line route sometimes, can receive partial transverse impact this moment, and traditional unmanned aerial vehicle is relatively poor to transverse impact force shock attenuation effect with the frame that plays.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an undercarriage shock-absorbing structure for unmanned aerial vehicle to solve the problem that proposes among the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme: a landing frame damping structure for an unmanned aerial vehicle comprises a top plate, wherein a circular groove is formed in the middle of the bottom of the top plate, a plurality of strip-shaped holes are equidistantly distributed in the middle of the top plate around the circular groove, one ends of the strip-shaped holes are communicated with the circular groove, a disc is arranged in the circular groove, the diameter of the disc is smaller than that of the circular groove, the outer wall of the disc is rotatably connected with one end of a straight rod, the other end of the straight rod is inserted into the strip-shaped holes, one end, located in the strip-shaped holes, of the straight rod is connected with one end of a piston, the outer wall of the piston is slidably connected with the inner wall of the strip-shaped holes, the other end of the piston is connected with one end of a compression spring, the other end of the compression spring is connected with the bottom edges of the strip-shaped holes, air holes are, the bottoms of the two sides of the underframe are respectively provided with a supporting rod.
Preferably, the connection mode between the chassis and the disc is welding.
Preferably, the upper ends of the supporting rods are rotatably connected with the underframe, pull rods are respectively arranged on one sides, close to the supporting rods on the two sides of the underframe, of the supporting rods, and the pull rods are connected with each other through a sleeve and an extension spring.
Preferably, the two ends of the sleeve are respectively provided with a round hole, one end of the pull rod is inserted into the round hole, and the end of the pull rod in the round hole is connected with the bottom edge of the round hole through an extension spring.
Preferably, the supporting rods are respectively arranged on two sides of the underframe at equal intervals.
Preferably, the lower end of the supporting rod is provided with a buffering foot made of rubber materials, and the buffering foot is of a frame-shaped structure.
Compared with the prior art, the beneficial effects of the utility model are that: this unmanned aerial vehicle is with frame shock-absorbing structure that rises adopts structural design such as roof, disc, straight-bar, piston, compression spring and chassis for unmanned aerial vehicle can obtain effectual buffering when receiving arbitrary direction's transverse impact, thereby has improved the shock attenuation effect.
Drawings
Fig. 1 is a front view of a landing gear damping structure for an unmanned aerial vehicle of the present invention;
fig. 2 is a cross-sectional view of a top plate of a landing gear shock-absorbing structure for an unmanned aerial vehicle;
fig. 3 is a bottom view of the undercarriage of the landing gear shock-absorbing structure for the unmanned aerial vehicle;
fig. 4 is the utility model relates to an unmanned aerial vehicle is with having risen and fallen frame shock-absorbing structure branch side view.
In the figure: 1. the device comprises an underframe, 2, a disc, 3, a top plate, 4, a straight rod, 5, a piston, 6, a compression spring, 7, an air hole, 8, an extension spring, 9, a sleeve, 10, a pull rod, 11, a support rod, 12 and a buffering foot.
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. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-4, the present invention provides a technical solution: a shock absorption structure of a landing frame for an unmanned aerial vehicle comprises a top plate 3, a circular groove is formed in the middle of the bottom of the top plate 3, a plurality of strip-shaped holes are equidistantly distributed in the middle of the top plate 3 around the circular groove, one end of each strip-shaped hole is communicated with the circular groove, a disc 2 is arranged in the circular groove, the disc 2 is in sliding connection with the top edge of the circular groove, the diameter of the disc 2 is smaller than that of the circular groove, the outer wall of the disc 2 is rotatably connected with one end of a straight rod 4, the straight rod 4 and the straight groove are rotatably connected through a pin shaft, the other end of the straight rod 4 is inserted into the strip-shaped holes, one end of the straight rod 4, which is located in each strip-shaped hole, is connected with one end of a piston 5, the outer wall of the piston 5 is in sliding connection with the inner wall of each strip-shaped hole, the other end of the, one end of the air hole 7 is connected with one end of the strip-shaped hole, the bottom of the disc 2 is connected with the base frame 1, the connection mode between the base frame 1 and the disc 2 is welding, the connection mode is more stable, the bottom parts of the two sides of the base frame 1 are respectively provided with the supporting rod 11, the structure enables the disc 2 to move in any direction of 360 degrees, and the disc 2 can be supported by the piston 5 and the compression spring 6 when moving in any direction, so that the unmanned aerial vehicle can obtain effective buffering when being transversely impacted in any direction, the shock absorption effect is improved, the upper end of the supporting rod 11 is rotatably connected with the base frame 1, one side of the two sides of the base frame 1, which is close to the supporting rod 11, is respectively provided with the pull rod 10, the pull rods 10 are connected with the extension spring 8 through the sleeve 9, the structure enables the supporting rods 11 to obtain elastic connection, the round hole has been seted up respectively at the both ends of sleeve pipe 9, and the one end of pull rod 10 is inserted and is located in the round hole, and pull rod 10 is located the one end in the round hole and is connected with the base of round hole through extension spring 8, extension spring 8's both ends accessible clamp connection is fixed, this structure makes the elastic coupling effect between the pull rod 10 more stable, branch 11 is a plurality ofly respectively about the both sides of chassis 1 equidistance, this structure makes the device receive the cushioning effect more evenly stable, the lower extreme of branch 11 is provided with the buffering foot 12 of rubber material, and buffering foot 12 is the frame shape structure, sunken deformation when this structure can receive vertical impact, through warping the buffering to the impact force.
The working principle is as follows: when the shock absorption structure of the landing frame for the unmanned aerial vehicle is used, whether parts are damaged or not or the connection is not firm is checked, the device is used after the parts are checked to be correct, the unmanned aerial vehicle is arranged on the top plate 3, when the unmanned aerial vehicle is impacted vertically when landing, firstly the buffering feet 12 can buffer the impact force through the concave deformation, meanwhile, the support rods 11 on the two sides of the underframe 1 are opened towards the two sides, the pull rod 10 and the extension spring 8 can elastically pull the support rods 11, so as to counteract and buffer the impact, and when the disc 2 is transversely impacted, the disc can transversely move in any direction of 360 degrees, can receive piston 5 and compression spring 6's support at disc 2 removal in-process to make unmanned aerial vehicle can obtain effectual buffering when receiving arbitrary direction's horizontal impact, improved the shock attenuation effect, this is exactly this unmanned aerial vehicle with landing frame shock-absorbing structure's theory of operation.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the invention.
Claims (6)
1. The utility model provides an unmanned aerial vehicle is with landing frame shock-absorbing structure, includes roof (3), its characterized in that: the middle of the bottom of the top plate (3) is provided with a circular groove, the middle of the top plate (3) is surrounded with a plurality of strip-shaped holes with equal distance distribution, one end of each strip-shaped hole is communicated with the circular groove, a disc (2) is arranged in the circular groove, the diameter of the disc (2) is smaller than that of the circular groove, the outer wall of the disc (2) is rotatably connected with one end of a straight rod (4), the other end of the straight rod (4) is inserted into the strip-shaped holes, one end of the straight rod (4) in each strip-shaped hole is connected with one end of a piston (5), the outer wall of the piston (5) is slidably connected with the inner wall of each strip-shaped hole, the other end of the piston (5) is connected with one end of a compression spring (6), the other end of the compression spring (6) is connected with the bottom edges of the strip-shaped holes, and one end of the air hole (7) is connected with one end of the strip-shaped hole, the bottom of the disc (2) is connected with the bottom frame (1), and the bottoms of two sides of the bottom frame (1) are respectively provided with a support rod (11).
2. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the underframe (1) and the disc (2) are connected by welding.
3. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the upper end of the supporting rod (11) is rotatably connected with the chassis (1), one side, close to the supporting rod (11), of the two sides of the chassis (1) is respectively provided with a pull rod (10), and the pull rods (10) are connected with an extension spring (8) through a sleeve (9).
4. The landing gear shock-absorbing structure for unmanned aerial vehicle of claim 3, wherein: round holes are respectively formed in two ends of the sleeve (9), one end of the pull rod (10) is inserted into the round holes, and the end, located in the round holes, of the pull rod (10) is connected with the bottom edges of the round holes through the extension spring (8).
5. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the supporting rods (11) are respectively arranged on two sides of the bottom frame (1) at equal intervals.
6. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the lower end of the supporting rod (11) is provided with a buffering foot (12) made of rubber, and the buffering foot (12) is of a frame-shaped structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022453892.4U CN213384693U (en) | 2020-10-30 | 2020-10-30 | Unmanned aerial vehicle is with frame shock-absorbing structure that plays |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022453892.4U CN213384693U (en) | 2020-10-30 | 2020-10-30 | Unmanned aerial vehicle is with frame shock-absorbing structure that plays |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213384693U true CN213384693U (en) | 2021-06-08 |
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|---|---|---|---|
| CN202022453892.4U Expired - Fee Related CN213384693U (en) | 2020-10-30 | 2020-10-30 | Unmanned aerial vehicle is with frame shock-absorbing structure that plays |
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| CN (1) | CN213384693U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115649428A (en) * | 2022-12-14 | 2023-01-31 | 江苏省盐城中学 | Retractable double-damping undercarriage of flight model airplane |
-
2020
- 2020-10-30 CN CN202022453892.4U patent/CN213384693U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115649428A (en) * | 2022-12-14 | 2023-01-31 | 江苏省盐城中学 | Retractable double-damping undercarriage of flight model airplane |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20210608 Termination date: 20211030 |
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| CF01 | Termination of patent right due to non-payment of annual fee |