CN207631486U - A kind of VTOL composite wing unmanned plane that rotor can vert - Google Patents
A kind of VTOL composite wing unmanned plane that rotor can vert Download PDFInfo
- Publication number
- CN207631486U CN207631486U CN201720968036.8U CN201720968036U CN207631486U CN 207631486 U CN207631486 U CN 207631486U CN 201720968036 U CN201720968036 U CN 201720968036U CN 207631486 U CN207631486 U CN 207631486U
- Authority
- CN
- China
- Prior art keywords
- rotor
- wing
- tail
- wings
- fixed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
The utility model discloses the VTOL composite wing unmanned planes that a kind of rotor can vert, including unmanned aerial vehicle body, pusher side fixed-wing, tail fixed-wing, preceding rotor, rear rotor, preceding rotor motor, rear rotor motor, navigation module, rotor wings frame and preceding rotor inclining rotary mechanism；The two horizontally disposed pusher side fixed-wings are symmetrically fixed at unmanned aerial vehicle body both sides；The two tail fixed-wings are symmetrically fixed at the tail both sides of unmanned aerial vehicle body；Two rotor wings frames are symmetricly set on two pusher sides and fix underwing, two rotor wings frames are parallel to each other, and rotor wings frame length direction is parallel with unmanned aerial vehicle body front-rear direction, the leading portion of the rotor wings frame is stretched out in pusher side fixed-wing front, and the back segment of the rotor wings frame stretches out at pusher side fixed-wing rear portion；The utility model has the advantages of simple structure, reduces rotor quantity, realizes to take off vertically to flat winged peace for preceding rotor design inclining rotary mechanism and flies to the instant switching of landing.
Description
Technical field
The VTOL composite wing that the utility model belongs to unmanned plane field more particularly to a kind of rotor can vert nobody
Machine.
Background technology
In recent years, since the advantages that multi-rotor unmanned aerial vehicle do not limit by place, can hover, at low cost is influenced, model
And quantity rapidly increases, but the factors such as power, aerodynamic arrangement are limited by, more rotors are in voyage, speed, flight time etc.
It is difficult to meet more and more harsh user demand.Fixed-wing unmanned plane length in cruise duration, speed are high, but need takeoff runway,
Its availability is constrained significantly.
Have at present using composite wing form, based on conventional Fixed Wing AirVehicle, increased more rotor power units,
According to multiaxis mode flight under landing and lower-speed state, the pulling force generated by multiple propellers overcomes gravity and aerodynamic drag
It flies；And at high speeds, according to fixed-wing mode flight, gravity is overcome by aerodynamic lift, forward by pulling force
Propeller overcome aerodynamic drag realize flight.Composite wing scheme is not necessarily to additional mechanism, simple in structure；There is no significantly fly
Attitudes vibration, navigation calculation are easy.Therefore, composite wing VTOL scheme is current reliability highest, and technical risk is minimum
Long endurance vertical take-off and landing drone scheme.
Although composite wing unmanned plane effectively compensate for fixed-wing unmanned plane can not VTOL short slab, in order to
This short slab is solved, most useless load is carried above fixed-wing unmanned plane, when composite wing unmanned plane enters with fixation
When wing mode flight, rotor system stops work, is only the useless load for improving complete machine, reduces fixed-wing pattern
The performance of lower flight.
Invention content
Goal of the invention：In order to overcome the deficiencies in the prior art, the utility model provides what a kind of rotor can vert
VTOL composite wing unmanned plane can promote flying quality, extend the flight time.
Technical solution：To achieve the above object, the VTOL composite wing that a kind of rotor of the utility model can vert without
It is man-machine, including unmanned aerial vehicle body, pusher side fixed-wing, tail fixed-wing, preceding rotor, rear rotor, preceding rotor motor, rear rotor electricity
Machine, navigation module, rotor wings frame and preceding rotor inclining rotary mechanism；
The two horizontally disposed pusher side fixed-wings are symmetrically fixed at unmanned aerial vehicle body both sides；Two tails are solid
Determine the tail both sides that the wing is symmetrically fixed at unmanned aerial vehicle body；Two rotor wings frames are symmetricly set on two pusher sides and fix
Underwing, two rotor wings frames are parallel to each other, and rotor wings frame length direction is parallel with unmanned aerial vehicle body front-rear direction, the rotor
The leading portion of frame is stretched out in pusher side fixed-wing front, and the back segment of the rotor wings frame stretches out at pusher side fixed-wing rear portion；The two rear rotations
Wing motor is vertically provided at the back segment of rotor wings frame, and rear rotor motor is located on the downside of the back segment end of rotor wings frame；The two rear rotations
After the wing is horizontally set on two respectively below rotor motor, and rear rotor motor is drivingly connected with rear rotor；The two preceding rotors and
Preceding rotor motor is arranged by preceding rotor inclining rotary mechanism in the leading portion end of rotor wings frame；The navigation module is arranged in unmanned plane machine
The tail top of body.
Further, the preceding rotor inclining rotary mechanism includes motor U-shaped frame and U-shaped stand；
The U-shaped stand is fixed at the leading portion end of rotor wings frame, and the motor U-shaped frame is rotatably provided in U-shaped frame
On seat, motor in the U-shaped stand can lateral shaft of the driving motor U-shaped frame on U-shaped stand vert, the preceding rotor electricity
Machine is fixed in motor U-shaped frame.
Further, further include landing cushion pad, the two landing cushion pads are symmetricly set on the head of unmanned aerial vehicle body
Two bottom sides.
Further, further include head lamp, wing lamp and tail light；The head lamp, wing lamp and tail light are separately positioned on
Head front end, pusher side fix underwing and tail tail portion.
Further, the outer profile of the unmanned aerial vehicle body is at the thin streamlined drops of the thick tail of head.
Further, further include infrared ray range sensor, the infrared ray range sensor setting is held before the handpiece, and two
Described infrared ray range sensor or so is set up in parallel.
Further, two alar parts of the two tail fixed-wings open above tail at inverted "eight" shape, two machines
The "eight" shape opening angle of tail fixed-wing is 120 degree.
Further, the rotor wings frame is the rhs-structure of boring, and battle array along its length on the inside of the pipe of rotor wings frame
Several reinforcing props are arranged, the upper and lower side of the reinforcing prop is separately connected in the pipe of rotor wings frame inner wall up and down.
Further, the rotor wings frame is carbon fibre materials.
Further, the extension wing end of the pusher side fixed-wing is in raise shape upwards.
Advantageous effect：The utility model has the advantages of simple structure, reduces rotor quantity, is realized for preceding rotor design inclining rotary mechanism
It takes off vertically to flat winged peace and flies to the instant switching of landing, optimize aerodynamic configuration, reduce flight resistance, promote flight
Can, extend the flight time；Hollow rhs-structure is incorporated in reinforcing prop in the case of not reducing rotor wings frame intensity, is reduced whole
The weight of machine further improves the flight resistance of unmanned plane；The form of the composite wing compensates for fixed-wing unmanned plane simultaneously
Specific runway is needed to slide the deficiency for landing of taking off.
Description of the drawings
Attached drawing 1 is the whole axonometric drawing of the utility model；
Attached drawing 2 is the whole first view of the utility model；
Attached drawing 3 is whole second view of the utility model；
Attached drawing 4 is the whole third view of the utility model；
Attached drawing 5 is whole 4th view of the utility model；
Attached drawing 6 is preceding rotor inclining rotary mechanism partial structural diagram；
Attached drawing 7 is reinforcing prop structural schematic diagram inside rotor wings frame.
Specific implementation mode
The utility model is further described below in conjunction with the accompanying drawings.
As shown in attached drawing 1 to 7, a kind of VTOL composite wing unmanned plane that rotor can vert, including unmanned aerial vehicle body 5,
Pusher side fixed-wing 12, tail fixed-wing 10, preceding rotor 1, rear rotor 7, preceding rotor motor 2, rear rotor motor 8, navigation module 9,
Rotor wings frame 18 and preceding rotor inclining rotary mechanism 23；
The two horizontally disposed pusher side fixed-wings 12 are symmetrically fixed at 5 both sides of unmanned aerial vehicle body；Two machines
Tail fixed-wing 10 is symmetrically fixed at 27 both sides of tail of unmanned aerial vehicle body 5；Two rotor wings frames 18 are symmetricly set on two
12 lower part of pusher side fixed-wing, two rotor wings frames 18 are parallel to each other, and before 18 length direction of rotor wings frame and unmanned aerial vehicle body 5
Rear direction is parallel, and the leading portion 4 of the rotor wings frame 18 is stretched out in 12 front of pusher side fixed-wing, and the back segment 6 of the rotor wings frame 18 is in machine
Fixed-wing 12 rear portion in side is stretched out；The two rear rotor motors 8 are vertically provided at the back segment 6 of rotor wings frame 18, and rear rotor motor 8
On the downside of 6 end of back segment of rotor wings frame 18；8 lower section of rotor motor after the two rear rotors 7 are horizontally set on two respectively, and after
Rotor motor 8 is drivingly connected with rear rotor 7；The two preceding rotors 1 and preceding rotor motor 2 are set by preceding rotor inclining rotary mechanism 23
It sets in 4 end of leading portion of rotor wings frame 18；The navigation module 9 is arranged on 27 top of tail of unmanned aerial vehicle body 5.
The preceding rotor inclining rotary mechanism 23 includes motor U-shaped frame 3 and U-shaped stand 20；The U-shaped stand 20 is fixed at
4 end of leading portion of rotor wings frame 18, the motor U-shaped frame 3 are rotatably provided on U-shaped stand 20, the electricity in the U-shaped stand 20
Machine can lateral shaft of the driving motor U-shaped frame 3 on U-shaped stand 20 vert, the preceding rotor motor 2 is fixed at motor U
On shape frame 3, rotor motor 2 is verted the thrust direction of the changeable two preceding rotors 1, and then preceding rotor before motor U-shaped frame 3 drives
Inclining rotary mechanism, which realizes, to take off vertically to flat winged switching.
Further include landing cushion pad 19, the two landing cushion pads 19 are symmetricly set on 15 bottom of head of unmanned aerial vehicle body 5
Portion both sides, airplane nose down formula, which lands, can play cushioning effect.
Further include head lamp 13, wing lamp 17 and tail light 16；The head lamp 13, wing lamp 17 and tail light 16 are respectively set
In 27 tail portion of 15 front end of head, 12 lower part of pusher side fixed-wing and tail.
The outer profile of the unmanned aerial vehicle body 5 reduces flight resistance, reduces dynamic at the thin streamlined drops of the thick tail of head
The burden of power apparatus improves flight continuation of the journey and accelerating ability.
Further include infrared ray range sensor 14, the infrared ray range sensor 14 is arranged in 15 front end of head, two institutes
It states infrared ray range sensor 14 or so to be set up in parallel, can identify front obstacle, conducive to giving warning in advance or avoiding.
Two alar parts of the two tail fixed-wings 10 open above tail at inverted "eight" shape, the two tail fixed-wings
10 "eight" shape opening angle is 120 degree, and angle setting makes the having a smooth flight property of unmanned plane reach optimum state.
The rotor wings frame 18 is the rhs-structure of boring, and array is several along its length on the inside of the pipe of rotor wings frame 18
Reinforcing prop 22, the upper and lower side of the reinforcing prop 22 are separately connected in the pipe of rotor wings frame 18 inner wall up and down, hollow rhs-structure with
Reinforcing prop is incorporated in the case of not reducing by 18 intensity of rotor wings frame, reduces the weight of complete machine.
The rotor wings frame 18 is carbon fibre materials, further increases intensity rotor wings frame 18, while reducing weight, is improved
Flying quality.
The extension wing end 25 of the pusher side fixed-wing 12 reduces shadow of the convection gas to unmanned plane in shape is raised upwards
It rings, keeps unmanned plane operation more steady.
The above is only the preferred embodiment of the utility model, it should be pointed out that：For the common skill of the art
For art personnel, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications
Also it should be regarded as the scope of protection of the utility model.
Claims (10)
1. the VTOL composite wing unmanned plane that a kind of rotor can vert, it is characterised in that：Including unmanned aerial vehicle body (5), pusher side
Fixed-wing (12), preceding rotor (1), rear rotor (7), preceding rotor motor (2), rear rotor motor (8), is led at tail fixed-wing (10)
Model plane block (9), rotor wings frame (18) and preceding rotor inclining rotary mechanism (23)；
The two horizontally disposed pusher side fixed-wings (12) are symmetrically fixed at unmanned aerial vehicle body (5) both sides；Two machines
Tail fixed-wing (10) is symmetrically fixed at tail (27) both sides of unmanned aerial vehicle body (5)；Two rotor wings frames (18) are symmetrical
It is arranged in two pusher side fixed-wing (12) lower parts, two rotor wings frames (18) are parallel to each other, and rotor wings frame (18) length direction
Parallel with unmanned aerial vehicle body (5) front-rear direction, the leading portion (4) of the rotor wings frame (18) is stretched out in pusher side fixed-wing (12) front,
The back segment (6) of the rotor wings frame (18) stretches out at pusher side fixed-wing (12) rear portion；The two rear rotor motors (8) are vertically provided at
The back segment (6) of rotor wings frame (18), and rear rotor motor (8) is located on the downside of back segment (6) end of rotor wings frame (18)；The two rear rotations
After the wing (7) is horizontally set on two respectively below rotor motor (8), and rear rotor motor (8) is drivingly connected with rear rotor (7)；Two
The preceding rotor (1) and preceding rotor motor (2) are arranged by preceding rotor inclining rotary mechanism (23) at leading portion (4) end of rotor wings frame (18)
End；Tail (27) top of navigation module (9) setting in unmanned aerial vehicle body (5).
2. the VTOL composite wing unmanned plane that a kind of rotor according to claim 1 can vert, it is characterised in that：It is described
Preceding rotor inclining rotary mechanism (23) includes motor U-shaped frame (3) and U-shaped stand (20)；
The U-shaped stand (20) is fixed at leading portion (4) end of rotor wings frame (18), and the motor U-shaped frame (3) rotatably sets
Set on U-shaped stand (20), the motor in the U-shaped stand (20) can driving motor U-shaped frame (3) along U-shaped stand (20)
Lateral shaft is verted, and the preceding rotor motor (2) is fixed in motor U-shaped frame (3).
3. the VTOL composite wing unmanned plane that a kind of rotor according to claim 1 can vert, it is characterised in that：Also wrap
Landing cushion pad (19) is included, the two landing cushion pads (19) are symmetricly set on head (15) bottom two of unmanned aerial vehicle body (5)
Side.
4. the VTOL composite wing unmanned plane that a kind of rotor according to claim 1 can vert, it is characterised in that：Also wrap
Include head lamp (13), wing lamp (17) and tail light (16)；The head lamp (13), wing lamp (17) and tail light (16) are respectively set
In head (15) front end, pusher side fixed-wing (12) lower part and tail (27) tail portion.
5. the VTOL composite wing unmanned plane that a kind of rotor according to claim 1 can vert, it is characterised in that：It is described
The outer profile of unmanned aerial vehicle body (5) is at the thin streamlined drops of the thick tail of head.
6. the VTOL composite wing unmanned plane that a kind of rotor according to claim 1 can vert, it is characterised in that：Also wrap
Infrared ray range sensor (14) is included, the infrared ray range sensor (14) is arranged in head (15) front end, and two is described infrared
Linear distance sensor (14) left and right is set up in parallel.
7. the VTOL composite wing unmanned plane that a kind of rotor according to claim 1 can vert, it is characterised in that：Two institutes
Two alar parts for stating tail fixed-wing (10) open above tail at inverted "eight" shape, " eight " of the two tail fixed-wings (10)
Font opening angle is 120 degree.
8. the VTOL composite wing unmanned plane that a kind of rotor according to claim 1 can vert, it is characterised in that：It is described
Rotor wings frame (18) is the rhs-structure of boring, and several reinforcing props of array along its length on the inside of the pipe of rotor wings frame (18)
(22), the upper and lower side of the reinforcing prop (22) is separately connected in the pipe of rotor wings frame (18) inner wall up and down.
9. the VTOL composite wing unmanned plane that a kind of rotor according to claim 1 can vert, it is characterised in that：It is described
Rotor wings frame (18) is carbon fibre materials.
10. the VTOL composite wing unmanned plane that a kind of rotor according to claim 1 can vert, it is characterised in that：Institute
The extension wing end (25) for stating pusher side fixed-wing (12) is in raise shape upwards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720968036.8U CN207631486U (en) | 2017-08-04 | 2017-08-04 | A kind of VTOL composite wing unmanned plane that rotor can vert |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720968036.8U CN207631486U (en) | 2017-08-04 | 2017-08-04 | A kind of VTOL composite wing unmanned plane that rotor can vert |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207631486U true CN207631486U (en) | 2018-07-20 |
Family
ID=62861772
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720968036.8U Active CN207631486U (en) | 2017-08-04 | 2017-08-04 | A kind of VTOL composite wing unmanned plane that rotor can vert |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207631486U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109720564A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | Fixed-wing unmanned plane and its control method with VTOL function |
| CN109969392A (en) * | 2019-03-13 | 2019-07-05 | 庆安集团有限公司 | A kind of vertically taking off and landing flyer converted using local dynamic effect |
| 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 |
| CN113050691A (en) * | 2021-03-25 | 2021-06-29 | 成都纵横自动化技术股份有限公司 | Unmanned aerial vehicle obstacle avoidance method, device, equipment and computer readable storage medium |
| 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 |
| CN116968919A (en) * | 2023-09-19 | 2023-10-31 | 上海柘飞航空科技有限公司 | Vertical take-off and landing aircraft with tilting power system and control method thereof |
-
2017
- 2017-08-04 CN CN201720968036.8U patent/CN207631486U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109720564A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | Fixed-wing unmanned plane and its control method with VTOL function |
| CN109969392A (en) * | 2019-03-13 | 2019-07-05 | 庆安集团有限公司 | A kind of vertically taking off and landing flyer converted using local dynamic effect |
| 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 |
| CN111532428B (en) * | 2020-04-28 | 2021-12-28 | 北京航空航天大学 | Tilting power micro fixed wing unmanned aerial vehicle capable of freely taking off and landing |
| CN113050691A (en) * | 2021-03-25 | 2021-06-29 | 成都纵横自动化技术股份有限公司 | Unmanned aerial vehicle obstacle avoidance method, device, equipment and computer readable storage medium |
| 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 |
| CN116968919A (en) * | 2023-09-19 | 2023-10-31 | 上海柘飞航空科技有限公司 | Vertical take-off and landing aircraft with tilting power system and control method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207631486U (en) | A kind of VTOL composite wing unmanned plane that rotor can vert | |
| CN106882371A (en) | A kind of hybrid tilting rotor wing unmanned aerial vehicle | |
| CN107933909A (en) | A kind of high-speed and high-efficiency tilting wing unmanned vehicle | |
| CN106882373A (en) | A kind of combined type tilt rotor helicopter | |
| CN106043696A (en) | Flying system for unmanned aerial vehicle | |
| CN207029551U (en) | A kind of combined type tilt rotor helicopter | |
| CN205998126U (en) | A kind of unmanned plane during flying system | |
| CN107963209A (en) | Tandem wing tilting rotor wing unmanned aerial vehicle | |
| CN107352029A (en) | A kind of electronic multiaxis tilting rotor wing unmanned aerial vehicle system | |
| CN105460215A (en) | Fixed-wing air vehicle achieving vertical or short-distance take-off and landing | |
| CN205469821U (en) | Perpendicular or short take off and landing fixed wing aircraft | |
| CN206187340U (en) | Aircraft | |
| CN208181416U (en) | Without rudder face VTOL fixed-wing unmanned plane | |
| CN211281472U (en) | Duct tail sitting posture VTOL unmanned aerial vehicle | |
| CN209176908U (en) | A kind of rotor fixed-wing unmanned plane of composite drive | |
| CN218537100U (en) | Single power driven unmanned aerial vehicle that verts | |
| CN207523932U (en) | Tandem wing tilting rotor wing unmanned aerial vehicle | |
| CN207607645U (en) | Compound rotor aircraft | |
| CN207917144U (en) | One kind is verted wing helicopter | |
| CN107284658B (en) | Composite vertical/short-distance take-off and landing aircraft | |
| CN206704538U (en) | The long continuation of the journey aerofoil multi-rotor unmanned aerial vehicle of one kind | |
| CN202481307U (en) | Four-propeller aircraft taking off and landing vertically | |
| CN205098475U (en) | Vertical take -off and landing aircraft | |
| CN109319106A (en) | A kind of high-speed rotor machine | |
| CN220404811U (en) | Model airplane with combination of fixed wings and rotary wings |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20181019 Address after: 100176 Beijing Daxing District Beijing economic and Technological Development Zone, Yongchang Road 4, building 4, three floor, 313A Patentee after: Beijing Ju Net Technology Co., Ltd. Address before: 100028 room 2312, Jingan center, 8 North Third Ring Road, Chaoyang District, Beijing. Patentee before: Beijing Cape InterSpace Technology Ltd |