CN109896003A - A kind of VTOL is verted three rotor wing unmanned aerial vehicles - Google Patents
A kind of VTOL is verted three rotor wing unmanned aerial vehicles Download PDFInfo
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- CN109896003A CN109896003A CN201910143958.9A CN201910143958A CN109896003A CN 109896003 A CN109896003 A CN 109896003A CN 201910143958 A CN201910143958 A CN 201910143958A CN 109896003 A CN109896003 A CN 109896003A
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- wing
- right flank
- fuselage
- verted
- unmanned aerial
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Abstract
It verts three rotor wing unmanned aerial vehicles the invention discloses a kind of VTOL, including fuselage, the fuselage two sides are separately installed with wing, the wing includes the intermediate wing, left wing, right flank, the intermediate wing is mounted on the fuselage, the intermediate wing two sides are separately connected the left wing and right flank, outer boom is respectively arranged in the left wing and right flank, and the left wing and the outer boom in right flank are symmetrically parallel, inclining rotary mechanism is installed on the outer boom, rotor is connected on the inclining rotary mechanism, the front end of the fuselage is equipped with reconnaissance system, the back body is equipped with foot piece, power device is installed on the foot piece, tailplane is installed on the end of the foot piece.Easy disassembly of the present invention, cruise duration are long, compact-sized, easy to carry.
Description
Technical field
The present invention relates to air vehicle technique field, specially a kind of VTOL is verted three rotor wing unmanned aerial vehicles.
Background technique
Unmanned plane is a kind of with wireless remotecontrol or by the not manned aircraft based on itself control, and unmanned plane is widely used in
It takes photo by plane, rescue, patrolling, monitoring, surveying and drawing, investigating, the fields such as movies-making, news report, express transportation, it is existing most of more
Wind resistance is weak for rotor wing unmanned aerial vehicle, and flying speed is slow, and cruise duration is short, when encountering bad weather, leads to the use of unmanned plane
Efficiency greatly reduces, and fixed-wing nobody, the main thrust generated using propeller or turbogenerator makes nobody
Forward, relative motion of the prevailing lift from wing and air is both economical for machine, but fixed-wing unmanned plane to landing site,
Flight operation all has high requirements, and more rotors mainly balance the gravity of aircraft by lift that multiple rotors generate, allows nothing
Man-machine fly up is come, but existing multi-rotor unmanned aerial vehicle command range is short, and cruise duration is short.
Summary of the invention
The present invention is in view of the above-mentioned problems of the prior art, provide that a kind of easy disassembly, cruise duration are long, and structure is tight
It gathers, portable VTOL is verted three rotor wing unmanned aerial vehicles.
In order to achieve the above object, the present invention is achieved by the following technical programs: a kind of VTOL is verted three rotors
Unmanned plane, including fuselage, the fuselage two sides are separately installed with wing, and the wing includes the intermediate wing, left wing, right flank, described
The intermediate wing is mounted on the fuselage, and the intermediate wing two sides are separately connected the left wing and right flank, in the left wing and right flank
It is respectively arranged with outer boom, and the left wing and the outer boom in right flank are symmetrically parallel, are equipped with and incline on the outer boom
Rotation mechanism, rotor is connected on the inclining rotary mechanism, and the front end of the fuselage is equipped with reconnaissance system, the back body installation
There is foot piece, power device is installed on the foot piece, tailplane is installed on the end of the foot piece.
Further: the left wing includes interior left wing and extreme left flank, and the right flank includes interior right flank and extreme right flank, it is described in
Between the wing connect with the fuselage by bolt, the interior left wing and interior right flank pass through circlip respectively and are connected to the intermediate wing two
Side, the extreme left flank are connect with the interior left wing by circlip, and the extreme right flank is connect with the interior right flank by circlip.
Further: the outer boom is connected separately in the interior left wing and interior right flank.
Further: height sensor being installed in the interior right flank, GPS antenna is installed on the extreme right flank.
Further: being respectively articulated with aileron on the extreme left flank and extreme right flank.
Further: image data transmission system, supplying cell and flight control system are installed in the fuselage.
Further: the foot piece is connected through a screw thread with the back body, and the junction of foot piece and the fuselage
It is provided with sealing rubber ring, the end of the foot piece is connect with the tailplane by circlip, is equipped with below the foot piece
Elastic slice bracket.
Further: buffer unit being installed below the fuselage.
Further: fuselage shell made of the blended composite material of Kevlar and carbon fiber.
Further: the power device includes motor, and fixed rotor is connected on the output shaft of the motor.
Beneficial effects of the present invention:
1. intermediate wing two sides pass through respectively compared with prior art, by the way that the intermediate wing to be mounted on fuselage using bolt
Circlip is connected with left wing and right flank, and outer boom is respectively arranged in left wing and right flank, inclining rotary mechanism is equipped on outer boom, verts
Rotor is installed, back body has been connected through a screw thread foot piece, has been equipped with power device on foot piece, passes through inclining rotary mechanism in mechanism
It is effectively combined with rotor and power device, this unmanned plane is made not only to be able to achieve VTOL, but also be able to achieve steady flat winged and flat winged
When power utilization rate it is high, electric energy energy consumption is few, and cruise duration is long, and compact-sized, convenient for disassembly and assembly, easy to carry, environmental suitability is high.
2. the connecting bracket on the driven rocker arm of inclining rotary mechanism, wheel is installed on bracket, is provided with elastic slice below foot piece
Bracket passes through three and supports using the wheel and elastic slice bracket three supporting points of composition on two symmetrical inclining rotary mechanisms
Point stops unmanned plane vertically upright on the ground, without installing other undercarriage.
3. playing the role of protecting fuselage by installing buffer unit below fuselage.
Detailed description of the invention
Fig. 1 is schematic structural view of the invention；
Fig. 2 is side view of the present invention；
Fig. 3 is inclining rotary mechanism VTOL status architecture schematic diagram；
Fig. 4 is the flat winged status architecture schematic diagram of inclining rotary mechanism.
In figure: 1- fuselage, the wing among 21-, left wing in 22-, 23- extreme left flank, right flank in 24-, 25- extreme right flank, 4- vert
Mechanism, 5- foot piece, 6- tailplane, 7- reconnaissance system, 8- power device, 9- aileron, 10, elastic slice bracket, 11- buffer unit,
12- image data transmission system, 13- supplying cell, 14- flight control system, 15- antenna, 16- height sensor, 17-GPS
Antenna, the outer boom of 18-, 19- rotor, the fixed rotor of 81-, 41- steering engine, 42- firm banking, the fixed footstock of 43-, 45- are actively put
Arm, 46- motor, 47- motor connecting base, the driven swing arm of 48-, 49- bracket, 410- wheel.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
A kind of VTOL three rotor wing unmanned aerial vehicle example structures of verting are provided as Figure 1-Figure 4 for the present invention to illustrate
Figure: including fuselage 1, the shell made of Kevlar and carbon fiber blended composite material of fuselage 1 is equipped with picture number in fuselage 1
According to Transmission system 12, supplying cell 13 and flight control system 14, supplying cell 13 is magnesium-based battery, is bonded with below fuselage 1
Buffer unit 11,1 two sides of fuselage are separately installed with wing, and wing includes the intermediate wing 21, left wing, right flank, and the intermediate wing 21 is mounted on
On fuselage 1, intermediate 21 two sides of the wing are separately connected left wing and right flank, and left wing includes interior left wing 22 and extreme left flank 23, and right flank includes interior
Right flank 24 and extreme right flank 25, the intermediate wing 21 are connect by bolt with fuselage 1, and interior left wing 22 and interior right flank 24 are connected by circlip respectively
It connects in intermediate 21 two sides of the wing, extreme left flank 23 is connect with interior left wing 22 by circlip, and extreme right flank 25 and interior right flank 24 are connected by circlip
It connects, aileron 9 has been respectively articulated on extreme left flank 23 and extreme right flank 25, has been respectively arranged with outer boom in interior left wing 22 and interior right flank 24
18, and left wing is symmetrically parallel with the outer boom 18 in right flank, and height sensor 16, extreme right flank 25 are equipped in interior right flank 24
On GPS antenna 17 is installed, inclining rotary mechanism 4 is installed on outer boom 18, is connected with rotor 19 on inclining rotary mechanism 4, before fuselage 1
End is equipped with reconnaissance system 7, and 1 rear end of fuselage is equipped with foot piece 5, and power device 8 is equipped on foot piece 5, and power device 8 includes electricity
Machine is connected with fixed rotor 81 on the output shaft of motor, is equipped with tailplane 6 on the end of foot piece 5, after foot piece 5 and fuselage 1
End is connected through a screw thread, and the junction of foot piece 5 and fuselage 1 is provided with salt spray resistance sealing rubber ring resistant to high temperature, the end of foot piece 5
It is connect by circlip with tailplane 6, the lower section of foot piece 5 is equipped with elastic slice bracket 10 by screw, and the end of foot piece 5 is equipped with
Antenna 15；
Supplying cell 13 respectively with inclining rotary mechanism 4, reconnaissance system 7, power device 8, image data transmission system 12, flight
Control system 14, height sensor 16, GPS antenna 17 are electrically connected；
The intermediate wing 21, interior left wing 22, extreme left flank 23, interior right flank 24, extreme right flank 25 are all made of NACA4409 modified aerofoil profile；
The intermediate wing 21 is connect by bolt with fuselage 1, and interior left wing 22 and interior right flank 24 are connected to centre by circlip
21 two sides of the wing, extreme left flank 23 are connect by circlip with interior left wing 22, and extreme right flank 25 is connect by circlip with interior right flank 24, foot piece 5
It is threadedly attached in 1 rear end of fuselage, power device 8 is mounted on foot piece 5 by bolt, and tailplane 6 and foot piece 5 pass through card
Spring connection, so that this unmanned plane is convenient for disassembly and assembly, it is easy to carry；It has been bolted respectively in interior left wing 22 and interior right flank 24 outer
Boom 18 is equipped with inclining rotary mechanism 4 on outer boom 18, rotor 19 is connected on inclining rotary mechanism 4, passes through interior left wing 22 and interior right flank
Rotor 19 on 24 on two symmetrical inclining rotary mechanisms 4 is made rotor 18 be able to achieve 90 ° or more and is inclined by inclining rotary mechanism 4
Turn and foot piece 5 on power device 8 fixation rotor 81, be not only able to achieve the VTOL of this unmanned plane, but also be able to achieve steady flat
Fly, power utilization rate is higher when putting down winged, reduces electric energy consume, and cruise duration is long, and manipulation side is convenient, compact-sized；Supplying cell
13 be magnesium-based battery, can be worked in the environment of temperature is subzero 40 °, environmental suitability is high；Fuselage 1 uses Kevlar and carbon fiber
Blended composite material is made, and alleviates the weight of unmanned plane, and integral strength is high；
As Figure 3-Figure 4, inclining rotary mechanism 4 includes steering engine 41, and steering engine 41 is fixedly mounted on firm banking 42 and fixed top
Between seat 43,41 two sides of steering engine are separately installed with active swing arm 45 and driven swing arm 48, the side of driven swing arm 48 and steering engine 41
Hingedly, active swing arm 45 and the active axis connection inside steering engine 41, the upper end of the driven swing arm 48 of active swing arm 45 is connected with motor
Attachment base 47 is equipped with motor 46 on motor connecting base 47, and the output shaft of motor 46 is connect with rotor 19, is connected in driven swing arm 48
It is connected to bracket 49, the lower end of bracket 49 is provided with wheel 410, and the carbon fibre tube 21 of outer boom 18 is bolted to connection in fixation
Between pedestal 42 and fixed footstock 43；
When work, including VTOL state (as shown in Figure 3), the motor inside steering engine 41 passes through driving shaft driving actively
Swing arm 45 rotates, and active swing arm 45 drives motor connecting base 47 and driven swing arm 48 to rotate, and makes active swing arm 45 and slave pendulum
Angle between arm 48 and fixed footstock 43 is 90 ° (i.e. the tilt angle of active swing arm 45 and driven swing arm 48 is 90 °), makes to produce
Power direction and fixed footstock 43 it is vertical, by control generation climbing power or down-force, to control the vertical ascent of unmanned plane
And decline, realize VTOL；
Flat winged state (as shown in Figure 4): the motor inside steering engine 41 is rotated by main shaft drives active swing arm 45, is actively put
Arm 45 drives motor connecting base 47 and driven swing arm 48 to rotate, and make active swing arm 45 and driven swing arm 48 and fixed footstock 43 it
Between angle be 0 °, generate the direction of power and fixed footstock 43 be parallel, realize unmanned plane flat winged；
By the wheel 410 on the bracket 49 of the symmetrical inclining rotary mechanism 4 of two in interior left wing 22 and interior right flank 24,
Three supporting points are constituted with the elastic slice bracket 10 of 5 lower section of foot piece, rest in unmanned plane vertically upright by three supporting points
On ground, without installing other undercarriage, by the buffer unit 11 of 1 lower section of fuselage, play the role of protecting fuselage 1.
In conclusion intermediate 21 two sides of the wing are connected by circlip respectively by the way that the intermediate wing 21 to be connect by bolt with fuselage 1
It is connected to interior left wing 22 and interior right flank 24, symmetrical outer boom 18 is separately installed in interior left wing 22 and interior right flank 24, it is overhanging
Inclining rotary mechanism 4 is installed on bar 18, rotor 19 is connected on inclining rotary mechanism 4, interior left wing 22 is connected with extreme left flank 23. by circlip
Interior right flank 24 is connected with extreme right flank 25 by circlip, and 1 rear end of fuselage has been connected through a screw thread foot piece 5, has installed on foot piece 5 dynamic
Device 8 makes this unmanned plane have the function of to vert by inclining rotary mechanism 4 and power device 8, realizes fixed-wing and more rotor phases
Mutually conversion, it is convenient for disassembly and assembly, it is easy to carry, it is compact-sized, altitude environment can be applicable in.
The above content is a further detailed description of the present invention in conjunction with specific preferred embodiments, and it cannot be said that
Specific implementation of the invention is only limited to these instructions.For those of ordinary skill in the art to which the present invention belongs, exist
Under the premise of not departing from present inventive concept, a number of simple deductions or replacements can also be made, all shall be regarded as belonging to of the invention
Protection scope.
Claims (10)
- Three rotor wing unmanned aerial vehicles 1. a kind of VTOL is verted, including fuselage (1), fuselage (1) two sides are separately installed with wing, It is characterized by: the wing includes the intermediate wing (21), left wing, right flank, the intermediate wing (21) is mounted on the fuselage (1) On, the intermediate wing (21) two sides are separately connected the left wing and right flank, and outer boom is respectively arranged in the left wing and right flank (18), and the left wing is symmetrically parallel with the outer boom (18) in right flank, is equipped with the machine that verts on the outer boom (18) Structure (4) is connected with rotor (19) on the inclining rotary mechanism (4), and the front end of the fuselage (1) is equipped with reconnaissance system (7), described Fuselage (1) rear end is equipped with foot piece (5), is equipped with power device (8) on the foot piece (5), is pacified on the end of the foot piece (5) Equipped with tailplane (6).
- 2. a kind of VTOL according to claim 1 is verted three rotor wing unmanned aerial vehicles, it is characterised in that: the left wing includes interior Left wing (22) and extreme left flank (23), the right flank include interior right flank (24) and extreme right flank (25), and the intermediate wing (21) is by inserting Pin is connect with the fuselage (1), and the interior left wing (22) and interior right flank (24) are connected to the intermediate wing by circlip respectively (21) two sides, the extreme left flank (23) are connect with the interior left wing (22) by circlip, the extreme right flank (25) and the interior right side The wing (24) is connected by circlip.
- 3. a kind of VTOL according to claim 2 is verted three rotor wing unmanned aerial vehicles, it is characterised in that: the interior left wing (22) With the outer boom (18) is connected separately on interior right flank (24).
- 4. a kind of VTOL according to claim 3 is verted three rotor wing unmanned aerial vehicles, it is characterised in that: the interior right flank (24) On be equipped with height sensor (16), GPS antenna (17) are installed on the extreme right flank (25).
- 5. a kind of VTOL according to claim 4 is verted three rotor wing unmanned aerial vehicles, it is characterised in that: the extreme left flank (23) With aileron (9) have been respectively articulated on extreme right flank (25).
- 6. a kind of VTOL according to claim 1 is verted three rotor wing unmanned aerial vehicles, it is characterised in that: in the fuselage (1) Image data transmission system (12), supplying cell (13) and flight control system (14) are installed.
- 7. a kind of VTOL according to claim 1 is verted three rotor wing unmanned aerial vehicles, it is characterised in that: the foot piece (5) with Fuselage (1) rear end is connected through a screw thread, and the junction of foot piece (5) and the fuselage (1) is provided with sealing rubber ring, described The end of foot piece (5) is connect by circlip with the tailplane (6), is equipped with elastic slice bracket below the foot piece (5) (10)。
- 8. a kind of VTOL according to claim 1 is verted three rotor wing unmanned aerial vehicles, it is characterised in that: under the fuselage (1) Side is equipped with buffer unit (11).
- 9. a kind of VTOL according to claim 1 is verted three rotor wing unmanned aerial vehicles, it is characterised in that: the fuselage (1) by Shell made of Kevlar and the blended composite material of carbon fiber.
- 10. a kind of VTOL according to claim 1 is verted three rotor wing unmanned aerial vehicles, it is characterised in that: the power device (8) include motor, fixed rotor (81) are connected on the output shaft of the motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910143958.9A CN109896003A (en) | 2019-02-27 | 2019-02-27 | A kind of VTOL is verted three rotor wing unmanned aerial vehicles |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910143958.9A CN109896003A (en) | 2019-02-27 | 2019-02-27 | A kind of VTOL is verted three rotor wing unmanned aerial vehicles |
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| CN109896003A true CN109896003A (en) | 2019-06-18 |
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| CN201910143958.9A Pending CN109896003A (en) | 2019-02-27 | 2019-02-27 | A kind of VTOL is verted three rotor wing unmanned aerial vehicles |
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Cited By (4)
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| CN111532428A (en) * | 2020-04-28 | 2020-08-14 | 北京航空航天大学 | Tilting power micro fixed wing unmanned aerial vehicle capable of freely taking off and landing |
| CN112810813A (en) * | 2021-02-02 | 2021-05-18 | 珠海市边锋智驱科技有限公司 | Tilting structure and unmanned aerial vehicle |
| CN114104276A (en) * | 2021-12-01 | 2022-03-01 | 朱翠红 | Aerial survey unmanned aerial vehicle capable of improving balance through buffering |
| DE102022119831A1 (en) | 2022-08-07 | 2024-02-08 | Robert Brun | Wings, aircraft, vehicles, procedures for them |
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| CN111532428A (en) * | 2020-04-28 | 2020-08-14 | 北京航空航天大学 | Tilting power micro fixed wing unmanned aerial vehicle capable of freely taking off and landing |
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| DE102022119831A1 (en) | 2022-08-07 | 2024-02-08 | Robert Brun | Wings, aircraft, vehicles, procedures for them |
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