CN213892872U - Many rotor unmanned aerial vehicle's radome fairing structure - Google Patents
Many rotor unmanned aerial vehicle's radome fairing structure Download PDFInfo
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- CN213892872U CN213892872U CN202022746315.4U CN202022746315U CN213892872U CN 213892872 U CN213892872 U CN 213892872U CN 202022746315 U CN202022746315 U CN 202022746315U CN 213892872 U CN213892872 U CN 213892872U
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Abstract
The utility model relates to the technical field of unmanned aerial vehicle accessories, and discloses a fairing structure of a multi-rotor unmanned aerial vehicle, which comprises an unmanned aerial vehicle power supply device, wherein a power supply cover is fixedly arranged at the upper end of the unmanned aerial vehicle power supply device, when the unmanned aerial vehicle is used and is used in flight, when the unmanned aerial vehicle meets rainy weather, then a fairing on the unmanned aerial vehicle power supply device moves in the air, rainwater in the air can enter the interior of the fairing through an air inlet hole during the high-speed movement of the fairing, and a liquid discharge groove is communicated with the interior of a circular groove, at the moment, the immersed rainwater in the circular groove can be discharged out of the outside through a plurality of liquid discharge grooves on a fixing ring, thus avoiding the circuit damage caused by the rainwater entering the interior of the fairing through the air inlet hole on the fairing and contacting with the interior of the unmanned aerial vehicle power supply device during the heat dissipation through the air inlet hole on the fairing, thereby reach automatic waterproof and drainage, prolong this unmanned aerial vehicle power supply unit's life's effect.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle accessory technical field especially relates to a many rotor unmanned aerial vehicle's radome fairing structure.
Background
Currently, unmanned aerial vehicles have been widely used in military and civilian applications. In short, the unmanned aerial vehicle is an unmanned aerial vehicle operated by using a radio remote control device and a program control device of the unmanned aerial vehicle, or is completely or intermittently and autonomously operated by an on-board computer, and is currently applied to various fields such as aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation and the like, so that the use of the unmanned aerial vehicle is greatly expanded.
Current unmanned aerial vehicle's radome fairing structure blocks the air current resistance when the external world, and the hole on the radome fairing when unmanned aerial vehicle internal power supply device dispels the heat, and unmanned aerial vehicle is when going in overcast and rainy weather, and the rainwater probably will get into inside unmanned aerial vehicle power supply device through the hole on the radome fairing to cause the damage to unmanned aerial vehicle internal power supply circuit, influence this unmanned aerial vehicle's use, for this reason, we provide a many rotor unmanned aerial vehicle's radome fairing structure.
SUMMERY OF THE UTILITY MODEL
Technical problem to be solved
The utility model mainly solves the technical problem existing in the prior art and provides a fairing structure of a multi-rotor unmanned aerial vehicle.
(II) technical scheme
In order to realize the purpose, the utility model adopts the following technical proposal that the fairing structure of the multi-rotor unmanned aerial vehicle comprises an unmanned aerial vehicle power supply device, the upper end of the unmanned aerial vehicle power supply device is fixedly provided with a power supply cover which is a semicircular cover body, the interior of the power supply cover is hollow, seven radiating holes which are arranged at equal intervals are arranged on the outer wall surface of the power supply cover, the radiating holes are in a circular hole shape, the outer wall surface of the power supply cover is fixedly provided with a fixing ring which is in a circular hollow ring shape, the outer wall surface of the fixing ring is provided with external threads which are arranged at equal intervals, the fixing ring is connected with a fairing through the external threads, the fairing is a semi-circular hollow cover body, the upper end fixed mounting of radome fairing has the air guide piece, and the air guide piece is rectangular block shape, the top guard is provided with above the air guide piece, and the top guard is the semi-circular cover body.
As preferred, the circular slot has been seted up to solid fixed ring's upper end, and the circular slot is circular inside cavity cyclic annular, the inside of circular slot is provided with the filter screen, and the filter screen is the fretwork netted, gu fixed ring's outer wall has seted up the flowing back groove that the equidistance was arranged, the flowing back groove is oval flute shape, the flowing back groove communicates with each other with the circular slot is inside, the intake air of equidistance range is seted up to the outer wall of radome fairing, and the intake air is circular poroid.
Preferably, four air passing holes which are arranged at equal intervals are formed in the air guide block, the air passing holes are circular holes, a fixing rod is fixedly mounted on the upper wall surface of the air guide block, and the fixing rod is fixedly connected with the top cover.
Preferably, the upper wall surface of the top cover is provided with three resistance grooves which are arranged at equal intervals, each resistance groove is in a rectangular groove shape, and one side wall surfaces of the three resistance grooves, which are close to each other, are arc-shaped wall surfaces respectively.
As preferred, unmanned aerial vehicle power supply unit's lower extreme fixed mounting has two mirror symmetry's bracing piece, and the bracing piece is circular shaft-like, two the equal fixed mounting of lower extreme of bracing piece has the floor pole, and the floor pole is circular shaft-like.
Preferably, the lower wall surface of the top cover is an arc-shaped wall surface.
Advantageous effects
The utility model provides a many rotor unmanned aerial vehicle's radome fairing structure. The method has the following beneficial effects:
(1) when the fairing structure of the multi-rotor unmanned aerial vehicle is used, when the unmanned aerial vehicle is in flight and is in rainy days, rainwater in the air can enter the interior of the fairing through the air inlet during high-speed movement of the fairing when the fairing on a power supply device of the unmanned aerial vehicle moves in the air, heat dissipation holes on the power supply cover are arranged at the top of the power supply cover for dissipating heat through the air inlet, external rainwater enters the interior of the fairing through the air inlet and enters the interior of the circular groove through the filter screen along with the radian of the power supply cover, the liquid discharge groove is communicated with the interior of the circular groove, and the immersed rainwater in the circular groove can be discharged out of the exterior through the liquid discharge grooves on the fixing ring, so that the problem that when the traditional power supply device of the unmanned aerial vehicle dissipates heat through the air inlet on the fairing, the rainwater enters the interior of the fairing through the air inlet and contacts with the interior of the power supply device of the unmanned aerial vehicle to cause circuit damage can be avoided, thereby reach automatic waterproof and drainage, prolong this unmanned aerial vehicle power supply unit's life's effect.
(2) This many rotor unmanned aerial vehicle's radome fairing structure, the air guide piece is installed to the upper end of radome fairing, and has seted up a plurality of holes of crossing on the air guide piece, at this moment when unmanned aerial vehicle flies the use, the air guide piece on the radome fairing can advance unmanned aerial vehicle in flight, reduces unmanned aerial vehicle self's flight resistance, improves unmanned aerial vehicle's flight speed to reach the effect that improves the stability of unmanned aerial vehicle flight.
(3) This many rotor unmanned aerial vehicle's radome fairing structure, the wind-guiding piece has the overhead guard through wind hole fixed mounting, and the overhead guard semicircular cover body, the lower wall of overhead guard is the arc wall, and the overhead guard top is provided with a plurality of resistance grooves, when unmanned aerial vehicle shifts up, at this moment external air when contacting with the overhead guard, the air alright in order to derive through the resistance groove, when the overhead guard descends downwards, at this moment the overhead guard can carry out the increase windage through self arc lower wall again, thereby reach the effect that improves unmanned aerial vehicle self's lift nature.
Drawings
FIG. 1 is an overall structure diagram of the present invention;
FIG. 2 is a partial schematic view of the drainage tank of the present invention;
fig. 3 is an enlarged view of a in fig. 1 according to the present invention.
Illustration of the drawings:
1. an unmanned aerial vehicle power supply device; 2. a power supply cover; 3. heat dissipation holes; 4. a fixing ring; 5. a circular groove; 6. a filter screen; 7. a liquid discharge tank; 8. an external thread; 9. a cowling; 10. an air inlet hole; 11. a wind guide block; 12. air passing holes; 13. fixing the rod; 14. a top cover; 15. a resistance groove; 16. a support bar; 17. a floor pole.
Detailed Description
The technical solution of the present invention is further described in detail by the following embodiments with reference to the accompanying drawings.
Example (b): a fairing structure of a multi-rotor unmanned aerial vehicle is disclosed, as shown in figures 1-3, and comprises an unmanned aerial vehicle power supply device 1, wherein the unmanned aerial vehicle power supply device 1 is of an existing structure, which is not described herein, a power supply cover 2 is fixedly installed at the upper end of the unmanned aerial vehicle power supply device 1, the power supply cover 2 is a semicircular cover body, the interior of the power supply cover 2 is hollow, seven radiating holes 3 are formed in the outer wall surface of the power supply cover 2 and are arranged at equal intervals, the radiating holes 3 are circular holes, a fixing ring 4 is fixedly installed on the outer wall surface of the power supply cover 2, the fixing ring 4 is a circular hollow ring, a circular groove 5 is formed in the upper end of the fixing ring 4, the circular groove 5 is a circular hollow ring, a filter screen 6 is arranged in the circular groove 5, the filter screen 6 is hollow-mesh-shaped, a liquid discharge groove 7 is formed in the outer wall surface of the fixing ring 4 and is arranged at equal intervals, the liquid discharge groove 7 is elliptical, the liquid discharge groove 7 is communicated with the interior of the circular groove 5, the outer wall surface of the fixing ring 4 is provided with external threads 8 which are arranged at equal intervals, the fixing ring 4 is in threaded connection with a fairing 9 through the external threads 8, the fairing 9 is a semicircular hollow cover body, the outer wall surface of the fairing 9 is provided with air inlet holes 10 which are arranged at equal intervals, the air inlet holes 10 are in a circular hole shape, the upper end of the fairing 9 is fixedly provided with an air guide block 11, the air guide block 11 is in a rectangular block shape, the air guide block 11 is provided with four air passing holes 12 which are arranged at equal intervals, the air passing holes 12 are in a circular hole shape, the upper wall surface of the air guide block 11 is fixedly provided with a fixing rod 13, the fixing rod 13 is fixedly connected with a top cover 14, a top cover 14 is arranged above the air guide block 11, the top cover 14 is a semicircular cover body, the lower wall surface of the top cover 14 is an arc-shaped wall surface, the upper wall surface of the top cover 14 is provided with three resistance grooves 15 which are arranged at equal intervals, the resistance grooves 15 are in a rectangular groove shape, one side wall surface of the three resistance grooves 15 which are close to each other is respectively in an arc-shaped wall surface, the lower extreme fixed mounting of unmanned aerial vehicle power supply unit 1 has two mirror symmetry's bracing piece 16, and bracing piece 16 is circular shaft-like, and the equal fixed mounting of lower extreme of two bracing pieces 16 has floor pole 17, and floor pole 17 is circular shaft-like.
The utility model discloses a theory of operation: when using, radome fairing 9 is connected on solid fixed ring 4, at this moment unmanned aerial vehicle is driving radome fairing 9 on solid fixed ring 4 when the flight removes, at this moment if rainwater in the air passes through fresh air inlet 10 and gets into inside back of radome fairing 9, at this moment the inside rainwater of radome fairing 9 alright with the circular slot 5 through solid fixed ring 4 on discharge to the fluid-discharge tank 7 inside external at the outflow, air guide block 11 on the radome fairing 9 is when unmanned aerial vehicle carries out the flight removal, at this moment air guide block 11 alright reduce unmanned aerial vehicle self flight resistance, and when unmanned aerial vehicle is carrying out self when going up and down, roof cover 14 alright carry out through self arc wall and resistance groove 15 reduce and increase the lift nature of unmanned aerial vehicle self in radome fairing 9 top.
The basic principles and main features of the present invention, i.e. the advantages of the present invention, have been shown and described above. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (6)
1. The utility model provides a many rotor unmanned aerial vehicle's radome fairing structure, includes unmanned aerial vehicle power supply unit (1), its characterized in that: the utility model discloses an unmanned aerial vehicle power supply unit, including unmanned aerial vehicle power supply unit (1), the upper end fixed mounting of power cover (2), louvre (3) that seven equidistance were arranged are seted up to the outer wall of power cover (2), the outer wall fixed mounting of power cover (2) has solid fixed ring (4), external screw thread (8) that the equidistance was arranged are seted up to the outer wall of solid fixed ring (4), gu fixed ring (4) have radome fairing (9) through external screw thread (8) threaded connection, the upper end fixed mounting of radome fairing (9) has wind guide block (11), the top of wind guide block (11) is provided with overhead guard (14).
2. The fairing structure of a multi-rotor drone according to claim 1, characterized in that: circular slot (5) have been seted up to the upper end of solid fixed ring (4), the inside of circular slot (5) is provided with filter screen (6), fluid-discharge tank (7) that the equidistance was arranged are seted up to the outer wall of solid fixed ring (4), fluid-discharge tank (7) communicate with each other with circular slot (5) are inside, intake opening (10) that the equidistance was arranged are seted up to the outer wall of radome fairing (9).
3. The fairing structure of a multi-rotor drone according to claim 1, characterized in that: the air guide device is characterized in that four air passing holes (12) arranged at equal intervals are formed in the air guide block (11), a fixing rod (13) is fixedly mounted on the upper wall face of the air guide block (11), and the fixing rod (13) is fixedly connected with the top cover (14).
4. The fairing structure of a multi-rotor drone according to claim 1, characterized in that: the upper wall surface of the top cover (14) is provided with three resistance grooves (15) which are arranged at equal intervals, and one side wall surface of the inner parts of the resistance grooves (15) which are close to each other is an arc-shaped wall surface respectively.
5. The fairing structure of a multi-rotor drone according to claim 1, characterized in that: the lower extreme fixed mounting of unmanned aerial vehicle power supply unit (1) has two mirror symmetry's bracing piece (16), two the equal fixed mounting of lower extreme of bracing piece (16) has floor pole (17).
6. The fairing structure of a multi-rotor drone according to claim 1, characterized in that: the lower wall surface of the top cover (14) is an arc-shaped wall surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022746315.4U CN213892872U (en) | 2020-11-24 | 2020-11-24 | Many rotor unmanned aerial vehicle's radome fairing structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022746315.4U CN213892872U (en) | 2020-11-24 | 2020-11-24 | Many rotor unmanned aerial vehicle's radome fairing structure |
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| CN213892872U true CN213892872U (en) | 2021-08-06 |
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| CN202022746315.4U Active CN213892872U (en) | 2020-11-24 | 2020-11-24 | Many rotor unmanned aerial vehicle's radome fairing structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113650775A (en) * | 2021-08-25 | 2021-11-16 | 东莞市利芯智能科技有限公司 | Unmanned aerial vehicle's flight structure |
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2020
- 2020-11-24 CN CN202022746315.4U patent/CN213892872U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113650775A (en) * | 2021-08-25 | 2021-11-16 | 东莞市利芯智能科技有限公司 | Unmanned aerial vehicle's flight structure |
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