CN214690167U - Reconnaissance type composite wing VTOL unmanned aerial vehicle - Google Patents
Reconnaissance type composite wing VTOL unmanned aerial vehicle Download PDFInfo
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- CN214690167U CN214690167U CN202121130300.3U CN202121130300U CN214690167U CN 214690167 U CN214690167 U CN 214690167U CN 202121130300 U CN202121130300 U CN 202121130300U CN 214690167 U CN214690167 U CN 214690167U
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Abstract
The utility model discloses a reconnaissance type composite wing VTOL unmanned aerial vehicle relates to reconnaissance unmanned aerial vehicle technical field. Including the unmanned aerial vehicle fuselage, the equal fixed mounting in outer wall both sides of unmanned aerial vehicle fuselage is provided with the unmanned aerial vehicle wing, and the installation of the outer wall right side of unmanned aerial vehicle wing is provided with the unmanned aerial vehicle rotor, and the installation of the outer wall bottom of unmanned aerial vehicle wing is provided with the dead lever, and the outer wall right-hand member of dead lever slides and inlays and be equipped with the telescopic link, and the outer wall right-hand member of telescopic link is fixed and is provided with the connecting rod, and the outer wall surface mounting of connecting rod is provided with the unmanned aerial vehicle fin. Through the dead lever, preceding rotor block and back rotor block, can reduce unmanned aerial vehicle's whole weight, improve the speed that unmanned aerial vehicle climbed, descend and fly, wholly improve unmanned aerial vehicle's performance, through unmanned aerial vehicle fin, afterbody rotor and connecting rod, can improve the stationarity that unmanned aerial vehicle flies, make unmanned aerial vehicle can keep steady in fast-speed flight, make unmanned aerial vehicle fly farther.
Description
Technical Field
The utility model relates to a reconnaissance unmanned air vehicle technical field specifically is a reconnaissance type composite wing VTOL unmanned aerial vehicle.
Background
The unmanned aerial vehicle is an unmanned aerial vehicle operated by a radio remote control device or a self program control device, and can be divided into several categories of unmanned helicopters, unmanned fixed wing aircrafts, unmanned multi-rotor aircrafts, unmanned airships and unmanned parachute aircrafts from the technical perspective.
At present unmanned aerial vehicle receives many factors at the in-process of flight to influence unmanned aerial vehicle's flight, lead to the effectual flight of unmanned aerial vehicle to reduce, flight speed reduces, and secondly, unmanned aerial vehicle is when flying, and is fast more, and unmanned aerial vehicle's stationarity is worse, leads to unmanned aerial vehicle to appear rocking at the in-process of flying, leads to unmanned aerial vehicle to damage.
SUMMERY OF THE UTILITY MODEL
The utility model provides a reconnaissance type composite wing VTOL unmanned aerial vehicle, through dead lever, preceding turning block and back turning block, can reduce unmanned aerial vehicle's whole weight, improve the speed that unmanned aerial vehicle climbed, descend and fly, wholly improve unmanned aerial vehicle's performance, through unmanned aerial vehicle fin, afterbody rotor and connecting rod, can improve the stationarity that unmanned aerial vehicle flies, make unmanned aerial vehicle can keep steady in fast-speed flight, make unmanned aerial vehicle fly farther.
In order to achieve the above purpose, the utility model discloses a following technical scheme realizes: the utility model provides a reconnaissance type composite wing VTOL unmanned aerial vehicle, includes the unmanned aerial vehicle fuselage, and the equal fixed mounting in outer wall both sides of unmanned aerial vehicle fuselage is provided with the unmanned aerial vehicle wing, the outer wall right side installation of unmanned aerial vehicle wing is provided with the unmanned aerial vehicle rotor, the outer wall bottom installation of unmanned aerial vehicle wing is provided with the dead lever, the outer wall right-hand member of dead lever slides and inlays and is equipped with the telescopic link, the fixed connecting rod that is provided with of outer wall right-hand member of telescopic link, the outer wall surface mounting of connecting rod is provided with the unmanned aerial vehicle fin, the outer wall right side installation of unmanned aerial vehicle fin is provided with the afterbody rotor, the outer wall left side installation of dead lever is provided with preceding turning block, and the fixed back rotating vane that is provided with in outer wall top of preceding turning block, the outer wall right side installation of dead lever is provided with the back turning block, and the fixed back rotating vane that is provided with in outer wall top of back turning block.
As the utility model relates to a reconnaissance type composite wing VTOL unmanned aerial vehicle, the outside extension of outer wall right-hand member of unmanned aerial vehicle fuselage is provided with the connecting piece, the one end installation that the unmanned aerial vehicle fuselage was kept away from to the connecting rod is provided with the afterbody and changes the leaf.
As the utility model relates to a reconnaissance type composite wing VTOL unmanned aerial vehicle, the installation of the outer wall bottom of unmanned aerial vehicle fuselage is provided with the support frame.
As the utility model relates to a reconnaissance type composite wing VTOL unmanned aerial vehicle, the fixed auxiliary wing piece that is provided with in outer wall top of unmanned aerial vehicle fin.
As the utility model relates to a reconnaissance type composite wing VTOL unmanned aerial vehicle the outer wall left side slip cover of connecting rod is equipped with solid fixed ring, and gu fixed ring's inner wall left side threaded connection is in the outer wall department of telescopic link.
As the utility model relates to a reconnaissance type composite wing VTOL unmanned aerial vehicle, the installation of the outer wall top of unmanned aerial vehicle fuselage is provided with power visor.
The utility model provides a reconnaissance type composite wing VTOL unmanned aerial vehicle. The method has the following beneficial effects:
(1) this reconnaissance type composite wing VTOL unmanned aerial vehicle through dead lever, preceding turning block and back turning block, can reduce unmanned aerial vehicle's whole weight, improves the speed that unmanned aerial vehicle climbed, descends and fly, wholly improves unmanned aerial vehicle's performance.
(2) This reconnaissance type composite wing VTOL unmanned aerial vehicle through unmanned aerial vehicle fin, afterbody rotor and connecting rod, can improve the stationarity that unmanned aerial vehicle flies, makes unmanned aerial vehicle can keep steady in fast-speed flight, makes unmanned aerial vehicle fly farther.
Drawings
Fig. 1 is a front view of the present invention;
fig. 2 is a rear view of the present invention;
fig. 3 is a bottom view of the present invention.
In the figure: 1. an unmanned aerial vehicle body; 2. wings of the unmanned aerial vehicle; 3. a rotor wing of the unmanned aerial vehicle; 4. fixing the rod; 5. a telescopic rod; 6. a connecting rod; 7. an unmanned aerial vehicle empennage; 8. a tail rotor; 9. a front rotary block; 10. a front rotary blade; 11. a rear turning block; 12. a rear rotating blade; 13. rotating the leaves at the tail part; 14. a support frame; 15. an auxiliary wing block; 16. a fixing ring; 17. a power supply protective cover; 18. a connecting member.
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. All other embodiments obtained by persons skilled in the art based on the embodiments in the present application without any creative work belong to the protection scope of the present application.
In the description of the present application, it is to be noted that the terms "upper", "lower", "inner", "outer", "top/bottom", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "sleeved/connected," "connected," and the like are to be construed broadly, e.g., "connected," which may be fixedly connected, detachably connected, or integrally connected; the connection can be mechanical connection or electrical connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those skilled in the art.
Referring to fig. 1-3, the present invention provides a technical solution: a reconnaissance type composite wing vertical take-off and landing unmanned aerial vehicle comprises an unmanned aerial vehicle body 1, wherein two sides of the outer wall of the unmanned aerial vehicle body 1 are fixedly provided with unmanned aerial vehicle wings 2, the right side of the outer wall of the unmanned aerial vehicle wings 2 is provided with unmanned aerial vehicle rotors 3, the bottom of the outer wall of the unmanned aerial vehicle wings 2 is provided with a fixed rod 4, the right end of the outer wall of the fixed rod 4 is embedded with a telescopic rod 5 in a sliding manner, the right end of the outer wall of the telescopic rod 5 is fixedly provided with a connecting rod 6, the surface of the outer wall of the connecting rod 6 is provided with an unmanned aerial vehicle empennage 7, the right side of the outer wall of the unmanned aerial vehicle empennage 7 is provided with a tail rotor 8, the left side of the outer wall of the fixed rod 4 is provided with a front rotating block 9, and the top of the outer wall of the front rotating block 9 is fixedly provided with a front rotating blade 10, the right side of the outer wall of the fixed rod 4 is provided with a rear rotating block 11, and the top of the outer wall of the rear rotating block 11 is fixedly provided with a rear rotating blade 12.
In this embodiment: the unmanned aerial vehicle wing 2 can drive wind power to enable the unmanned aerial vehicle to fly more smoothly through the unmanned aerial vehicle body 1 and the unmanned aerial vehicle wing 2 made of composite materials, the unmanned aerial vehicle wing 2 can enable the unmanned aerial vehicle to fly in flight, the air flow on the unmanned aerial vehicle wing 2 can be changed through the unmanned aerial vehicle rotor wing 3, so as to control the flight of the unmanned aerial vehicle, the front rotating block 9 and the rear rotating block 11 are arranged on the unmanned aerial vehicle through the fixed rod 4, the front rotating block 9 and the rear rotating block 11 can respectively control the rotation of the front rotating blade 10 and the rear rotating blade 12, so that the climbing, descending and flying speeds of the unmanned aerial vehicle are improved, the performance of the unmanned aerial vehicle is integrally improved, the distance between the unmanned aerial vehicle empennage 7 and the unmanned aerial vehicle body 1 can be adjusted through the telescopic rod 5, the flying tail rotor wing 8 can improve the flying stability of the unmanned aerial vehicle, so that the unmanned aerial vehicle can keep stable in high-speed flight, the unmanned aerial vehicle flies farther.
Specifically, the outer wall right-hand member of unmanned aerial vehicle fuselage 1 outwards extends and is provided with connecting piece 18, and the one end installation that unmanned aerial vehicle fuselage 1 was kept away from to connecting rod 6 is provided with afterbody commentaries on classics leaf 13.
In this embodiment: through connecting piece 18, can make the afterbody change leaf 13 and fix on unmanned aerial vehicle fuselage 1, the rotation of afterbody change leaf 13 can promote unmanned aerial vehicle to move ahead.
Specifically, the outer wall bottom installation of unmanned aerial vehicle fuselage 1 is provided with support frame 14.
In this embodiment: through support frame 14, support frame 14 supports unmanned aerial vehicle and places subaerial.
Specifically, the top of the outer wall of the unmanned aerial vehicle empennage 7 is fixedly provided with an auxiliary wing block 15.
In this embodiment: through the auxiliary wing piece 15, the influence that many and overcome the air obstacle and introduce for unmanned aerial vehicle can be subtracted to auxiliary wing piece 15, under the high-speed state of traveling, can reduce air resistance, makes speed accelerate.
Specifically, the outer wall left side of connecting rod 6 is slided to overlap and is equipped with solid fixed ring 16, and the outer wall department of the inner wall left side threaded connection of solid fixed ring 16 in telescopic link 5.
In this embodiment: through the fixed ring 16, the connecting rod 6 can be fixed on the telescopic rod 5, and the connecting rod 6 is prevented from moving in flight.
Specifically, the outer wall top installation of unmanned aerial vehicle fuselage 1 is provided with power visor 17.
In this embodiment: the power protection cover 17 may protect the motor interface by the power protection cover 17.
During the use, put unmanned aerial vehicle in spacious area earlier, control unmanned aerial vehicle's start, make unmanned aerial vehicle preceding rotor blade 10 rotate earlier with back rotor blade 12, afterbody rotor blade 13's rotation can promote unmanned aerial vehicle to move ahead, at the in-process of flight, unmanned aerial vehicle rotor 3 can change the air current on the unmanned aerial vehicle with afterbody rotor blade 8, improve the stationarity that unmanned aerial vehicle flies, make unmanned aerial vehicle can keep steady in fast-speed flight, make unmanned aerial vehicle fly farther.
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 (6)
1. The utility model provides a reconnaissance type composite wing VTOL unmanned aerial vehicle, includes unmanned aerial vehicle fuselage (1), its characterized in that: both sides of the outer wall of an unmanned aerial vehicle body (1) are fixedly provided with unmanned aerial vehicle wings (2), the right side of the outer wall of the unmanned aerial vehicle wings (2) is provided with unmanned aerial vehicle rotors (3), the bottom of the outer wall of the unmanned aerial vehicle wings (2) is provided with a fixed rod (4), the right end of the outer wall of the fixed rod (4) is slidably embedded with a telescopic rod (5), the right end of the outer wall of the telescopic rod (5) is fixedly provided with a connecting rod (6), the surface of the outer wall of the connecting rod (6) is provided with an unmanned aerial vehicle empennage (7), the right side of the outer wall of the unmanned aerial vehicle empennage (7) is provided with a tail rotor (8), the left side of the outer wall of the fixed rod (4) is provided with a front rotating block (9), the top of the outer wall of the front rotating block (9) is fixedly provided with a front rotating blade (10), and the right side of the outer wall of the fixed rod (4) is provided with a rear rotating block (11), and the top of the outer wall of the rear rotating block (11) is fixedly provided with a rear rotating blade (12).
2. The reconnaissance type composite wing VTOL UAV of claim 1, wherein: the outer wall right-hand member of unmanned aerial vehicle fuselage (1) outwards extends and is provided with connecting piece (18), the one end installation that unmanned aerial vehicle fuselage (1) was kept away from in connecting rod (6) is provided with afterbody commentaries on classics leaf (13).
3. The reconnaissance type composite wing VTOL UAV of claim 1, wherein: the outer wall bottom installation of unmanned aerial vehicle fuselage (1) is provided with support frame (14).
4. The reconnaissance type composite wing VTOL UAV of claim 1, wherein: the outer wall top of unmanned aerial vehicle fin (7) is fixed and is provided with supplementary wing piece (15).
5. The reconnaissance type composite wing VTOL UAV of claim 1, wherein: the outer wall left side sliding sleeve of connecting rod (6) is equipped with solid fixed ring (16), and the outer wall department of inner wall left side threaded connection in telescopic link (5) of solid fixed ring (16).
6. The reconnaissance type composite wing VTOL UAV of claim 1, wherein: the outer wall top installation of unmanned aerial vehicle fuselage (1) is provided with power visor (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121130300.3U CN214690167U (en) | 2021-05-25 | 2021-05-25 | Reconnaissance type composite wing VTOL unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121130300.3U CN214690167U (en) | 2021-05-25 | 2021-05-25 | Reconnaissance type composite wing VTOL unmanned aerial vehicle |
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| CN214690167U true CN214690167U (en) | 2021-11-12 |
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| CN202121130300.3U Active CN214690167U (en) | 2021-05-25 | 2021-05-25 | Reconnaissance type composite wing VTOL unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275157A (en) * | 2021-12-31 | 2022-04-05 | 重庆交通大学绿色航空技术研究院 | Composite wing unmanned aerial vehicle and pneumatic balancing method |
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2021
- 2021-05-25 CN CN202121130300.3U patent/CN214690167U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275157A (en) * | 2021-12-31 | 2022-04-05 | 重庆交通大学绿色航空技术研究院 | Composite wing unmanned aerial vehicle and pneumatic balancing method |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: A Reconnaissance UAV with Composite Wing for Vertical Takeoff and Landing Effective date of registration: 20221019 Granted publication date: 20211112 Pledgee: Agricultural Bank of China Limited Tianjin Dongli Sub branch Pledgor: Yifei Xinghe (Tianjin) Intelligent Technology Co.,Ltd. Registration number: Y2022980018948 |
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| PE01 | Entry into force of the registration of the contract for pledge of patent right |