CN107697281A - A kind of culvert vertical take-off and landing unmanned aerial vehicle - Google Patents
A kind of culvert vertical take-off and landing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN107697281A CN107697281A CN201710853290.8A CN201710853290A CN107697281A CN 107697281 A CN107697281 A CN 107697281A CN 201710853290 A CN201710853290 A CN 201710853290A CN 107697281 A CN107697281 A CN 107697281A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- steering wheel
- culvert
- duct
- swing arm
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The present invention relates to unmanned vehicle technical field, more particularly to a kind of culvert vertical take-off and landing unmanned aerial vehicle, main technical schemes include structural body, including aircraft body, and described aircraft body includes aircraft head, horn, aircraft tail, vector duct spout；Described aircraft head, aircraft tail are equipped with aircraft tire；Described aircraft tail is provided with aircraft empennage；Setting activity culvert device on described horn.This aircraft of unmanned vehicle provided by the invention not only possesses multifunctionality, is also equipped with higher security performance.Movable culvert device designs adds one of shield frame to the moving vane of high speed rotation, reduces the area that moving vane contacts with foreign object, improves security performance and antijamming capability.
Description
Technical field
The present invention relates to a kind of unmanned vehicle, more particularly, to a kind of culvert vertical take-off and landing unmanned aerial vehicle.
Background technology
In the modern times, unmanned plane has gradually been come among the life of most people, and either group activity is also
People lives, and we can see the figure of unmanned plane everywhere, and unmanned plane also increases some interests while life is convenient for people to
Taste, particularly depopulated helicopter, it is still the selection of most people the characteristics of its VTOL.Current most depopulated helicopters are all adopted
With rotor design, the rotor rotated at a high speed can give helicopter to provide climbing power, be the major impetus source of aircraft, but revolve at a high speed
The rotor turned has certain danger, so most of depopulated helicopters need to keep certain when flight with barrier and human body
Distance.
Unmanned plane of the prior art is divided into two kinds mostly, and one kind is fixed-wing unmanned plane, and another kind is that unmanned rotary wing is straight
The machine of liter, both unmanned planes respectively have excellent lack.For example fixed-wing unmanned plane has the characteristics of flying speed is fast, but landing condition is high；Nothing
Though people's heligyro speed is slower than fixed-wing, it has the characteristics of VTOL.So with the development of technology, Ren Menyue
More to wish a kind of aircraft that can be provided simultaneously with said two devices common feature.
The content of the invention
To make up the deficiencies in the prior art, the present invention provides a kind of culvert vertical take-off and landing unmanned aerial vehicle, takes movable culvert
Road design is used conveniently and safely and multi-functional feature so as to have.
Technical scheme is as follows：A kind of culvert vertical take-off and landing unmanned aerial vehicle, including aircraft body, it is described
Aircraft body includes aircraft head, horn, aircraft tail, vector duct spout；Described aircraft head, aircraft
Tail is equipped with aircraft tire；Described aircraft tail is provided with aircraft empennage；Setting activity duct on described horn
Device；
Described movable culvert device includes steering wheel I, power transmission shaft, steering wheel fixed frame, pull bar I, bearing and brushless duct electricity
Machine I, described steering wheel I are fixed on horn by steering wheel fixed frame, and steering wheel swing arm I is provided with steering wheel I, and steering wheel swing arm I is logical
Pull bar I is crossed to be connected with power transmission shaft swing arm；Power transmission shaft is fixed on horn by bearing, and brushless duct motor I is fixed by motor
Frame is connected with power transmission shaft swing arm；
Described vector duct spout is fixed on aircraft tail, and described vector duct spout includes steering wheel II, pull bar
IIth, loose-leaf, model plane rudder angle, moving vane, brushless duct motor II, gas channel, described steering wheel II, brushless duct motor II
It is fixed in gas channel, described steering wheel II is provided with steering wheel swing arm II, and described gas channel afterbody is connected by loose-leaf and lived
Movable vane piece, described moving vane are connected by model plane rudder angle, pull bar II with steering wheel swing arm II；Described vector duct spout is
Two, it is symmetrically distributed in aircraft body both sides；Described movable culvert device is two, is symmetrically distributed in aircraft body two
Side；Described aircraft empennage is double vertical tails.
Further, battery, electricity tune, signal receiver and model plane gyroscope are additionally provided with described aircraft body.
Further, in addition to it is used cooperatively model airplane remote controller.
Beneficial effects of the present invention are as follows：
(1) present invention is designed with movable culvert device, the direction of verting of brushless duct motor can be controlled, by brushless culvert
The direction of verting of road motor, this aircraft can select VTOL offline mode or horizontal direction offline mode, thus this hair
Bright to possess multifunctionality, user can select offline mode according to the hobby of oneself.Due to being set using movable culvert device
Meter, this aircraft not only possess multifunctionality, are also equipped with very high security.Movable culvert device designs the work to high speed rotation
Movable vane piece adds one of shield frame, reduces the area that rotary moveable blade contacts with foreign object, improves security performance and resists dry
Disturb ability.
(2) body both sides of the invention are also devised with vector duct spout, brushless duct motor, the brushless duct electricity of both sides
Machine can not only lift the power of aircraft, and vector duct spout can also increase the mobility of aircraft.
(3) present invention possesses the characteristics of Fixed Wing AirVehicle flying speed is fast, and vertically taking off and landing flyer VTOL
The characteristics of.
Brief description of the drawings
Fig. 1 is aircraft top view of the present invention；
Fig. 2 is aircraft right view of the present invention；
Fig. 3 is aircraft front view of the present invention；
Fig. 4 is movable culvert device top view；
Fig. 5 is movable culvert device right view；
Fig. 6 is movable culvert device front view；
Fig. 7 is vector duct spout top view；
Fig. 8 is vector duct spout right view；
Fig. 9 is vector duct spout front view；
Wherein：1st, aircraft body, 2, aircraft head, 3, aircraft tire, 4, horn, 5, movable culvert device, 6,
Brushless duct motor I, 7, aircraft tail, 8, aircraft empennage, 9, vector duct spout, 5A, steering wheel I, 5B, power transmission shaft, 5C,
Steering wheel fixed frame, 5D, steering wheel swing arm I, 5E, pull bar I, 5F, bearing, 5G, power transmission shaft swing arm, 5H, motor fixing frame, 9A, steering wheel
II, 9B, steering wheel swing arm II, 9C, pull bar II, 9D, loose-leaf, 9E, model plane rudder angle, 9F, moving vane, 9G, brushless duct motor II,
9H, gas channel.
Embodiment
1-9 is further explained explanation to the present invention below in conjunction with the accompanying drawings：
A kind of culvert vertical take-off and landing unmanned aerial vehicle, including aircraft body 1, described aircraft body 1 include flight
Device head 2, horn 4, aircraft tail 7, vector duct spout 9；Described aircraft head 2, aircraft tail 7 are equipped with winged
Row device wheel tire 3；Described aircraft tail 7 is provided with aircraft empennage 8；Setting activity culvert device 5 on described horn 4；Institute
The movable culvert device 5 stated includes the 5A of steering wheel I, power transmission shaft 5B, steering wheel fixed frame 5C, the 5E of pull bar I, bearing 5F and brushless duct electricity
Machine I 6, the described 5A of steering wheel I are fixed on horn 4 by steering wheel fixed frame 5C, and the 5D of steering wheel swing arm I, rudder are provided with the 5A of steering wheel I
The 5D of machine swing arm I is connected by the 5E of pull bar I with power transmission shaft swing arm 5G；Power transmission shaft 5B is fixed on horn 4 by bearing 5F, brushless culvert
Road motor I 6 is connected by motor fixing frame 5H and power transmission shaft swing arm 5G；Described vector duct spout 9 is fixed on flight
Device tail 7, described vector duct spout 9 include the 9A of steering wheel II, the 9C of pull bar II, loose-leaf 9D, model plane rudder angle 9E, moving vane
9F, the brushless 9G of duct motor II, gas channel 9H, the described 9A of steering wheel II, the brushless 9G of duct motor II are fixed on gas channel
In 9H, the described 9A of steering wheel II is provided with the 9B of steering wheel swing arm II, and described gas channel 9H afterbodys pass through loose-leaf 9D connection activity leaves
Piece 9F, described moving vane 9F are connected by model plane rudder angle 9E, the 9C of pull bar II with the 9B of steering wheel swing arm II.Described vector duct
Spout 9 is two, is symmetrically distributed in the both sides of aircraft body 1.Described movable culvert device 5 is two, is symmetrically distributed in winged
The both sides of row device body 1.Battery, electricity tune, signal receiver and model plane gyroscope are additionally provided with described aircraft body 1.It is described
Aircraft empennage 8 be double vertical tails.Also include being used cooperatively model airplane remote controller.
Aircraft body 1 of the present invention uses plastic material, and is filled with foamed material, can use injection molding and cut
The method cut processes to obtain, and gas channel 9H outlets are rectangle, and the moving vane 9F of setting has three, one steering wheel of every correspondence
Ⅱ9A.When brushless II 9G rotor high-speed rotations of duct motor, the air-flow rearwardly sprayed is formed in gas channel 9H, is being sprayed
Three moving vane 9F, one 9A of steering wheel II of every moving vane 9F connection are provided with mouthful, can be by controlling moving vane 9F
To change the direction for spraying air-flow.That is the moving vane 9F of spout can be rotated to different directions to produce the acceleration of different directions
Degree.
The present invention is movable duct aircraft, as user in use, can be controlled by remote control carry-on
Movable culvert device 5 and vector duct spout 9.When movable culvert device 5 works, brushless duct motor I 6 can tilt forward and
Vert backward, when tilting forward the brushless power direction of duct motor I 6 forward, the brushless power side of duct motor I 6 when verting backward
To backward, brushless duct motor I 6 vertically upward when power direction vertically upward.Vector duct spout 9 is arranged on aircraft body
Both sides, the moving vane 9F of spout can be rotated to different directions to produce the acceleration of different directions during its work.When upper and lower
Two panels moving vane 9F simultaneously upper deflecting when aircraft tail 7 produce downward acceleration, while aircraft machine when deflecting down
Tail 7 produces upward acceleration, when left and right two panels moving vane 9F is deflected to the left simultaneously aircraft tail 7 produce to the right plus
Speed, while aircraft tail 7 produces acceleration to the left during deflection to the right.When aircraft needs hovering, work can be controlled
The brushless duct motor I 6 of dynamic culvert device 5, which retreats to transfer, offsets the brushless 9G of duct motor II from vector duct spout 9
Thrust.
Claims (3)
- A kind of 1. culvert vertical take-off and landing unmanned aerial vehicle, it is characterised in that including aircraft body (1), described aircraft sheet Body (1) includes aircraft head (2), horn (4), aircraft tail (7), vector duct spout (9)；Described aircraft head (2), aircraft tail (7) is equipped with aircraft tire (3)；Described aircraft tail (7) is provided with aircraft empennage (8)；Institute Setting activity culvert device (5) on the horn (4) stated；Described movable culvert device (5) includes steering wheel I (5A), power transmission shaft (5B), steering wheel fixed frame (5C), pull bar I (5E), axle (5F) and brushless duct motor I (6) are held, described steering wheel I (5A) is fixed on horn (4) by steering wheel fixed frame (5C), rudder Steering wheel swing arm I (5D) is provided with machine I (5A), steering wheel swing arm I (5D) is connected by pull bar I (5E) with power transmission shaft swing arm (5G)； Power transmission shaft (5B) is fixed on horn (4) by bearing (5F), and brushless duct motor I (6) is by motor fixing frame (5H) with passing Moving axis swing arm (5G) is connected；Described vector duct spout (9) is fixed on aircraft tail (7), and described vector duct spout (9) includes steering wheel II (9A), pull bar II (9C), loose-leaf (9D), model plane rudder angle (9E), moving vane (9F), brushless duct motor II (9G), air-flow lead to Road (9H), described steering wheel II (9A), brushless duct motor II (9G) are fixed in gas channel (9H), described steering wheel II (9A) is provided with steering wheel swing arm II (9B), and described gas channel (9H) afterbody connects moving vane (9F), institute by loose-leaf (9D) The moving vane (9F) stated is connected by model plane rudder angle (9E), pull bar II (9C) with steering wheel swing arm II (9B)；Described vector is contained Road spout (9) is two, is symmetrically distributed in aircraft body (1) both sides；Described movable culvert device (5) is two, symmetrically It is distributed in aircraft body (1) both sides；Described aircraft empennage (8) is double vertical tails.
- 2. culvert vertical take-off and landing unmanned aerial vehicle as claimed in claim 1, it is characterised in that described aircraft body (1) Inside it is additionally provided with battery, electricity tune, signal receiver and model plane gyroscope.
- 3. culvert vertical take-off and landing unmanned aerial vehicle as claimed in claim 1, it is characterised in that also include distant with the use of model plane Control device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710853290.8A CN107697281A (en) | 2017-09-20 | 2017-09-20 | A kind of culvert vertical take-off and landing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710853290.8A CN107697281A (en) | 2017-09-20 | 2017-09-20 | A kind of culvert vertical take-off and landing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107697281A true CN107697281A (en) | 2018-02-16 |
Family
ID=61173037
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710853290.8A Pending CN107697281A (en) | 2017-09-20 | 2017-09-20 | A kind of culvert vertical take-off and landing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107697281A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110550208A (en) * | 2019-10-15 | 2019-12-10 | 中国计量大学 | Blade opening and closing mechanism based on rotary flapping wing vertical take-off and landing power device |
| WO2022067492A1 (en) * | 2020-09-29 | 2022-04-07 | 瑞鉴航太科技股份有限公司 | Aerial vehicle |
Citations (7)
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|---|---|---|---|---|
| KR20030049796A (en) * | 2001-12-17 | 2003-06-25 | 한국항공우주연구원 | Three-Fan Lifted Vertical Take-off and Landing Aircraft |
| CN103144769A (en) * | 2013-03-05 | 2013-06-12 | 西北工业大学 | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct |
| CN104369863A (en) * | 2014-10-31 | 2015-02-25 | 吴建伟 | Composite vertical take-off/landing aircraft |
| CN105151292A (en) * | 2015-05-25 | 2015-12-16 | 郝思阳 | Distributive vectored thrust system |
| CN105292444A (en) * | 2014-07-08 | 2016-02-03 | 吴建伟 | Vertical take-off and landing aircraft |
| CN105947192A (en) * | 2016-06-01 | 2016-09-21 | 中国航空工业集团公司西安飞机设计研究所 | Tilting double-duct unmanned aerial vehicle |
| CN106516100A (en) * | 2016-09-11 | 2017-03-22 | 珠海市磐石电子科技有限公司 | Vertical takeoff and landing aircraft |
-
2017
- 2017-09-20 CN CN201710853290.8A patent/CN107697281A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20030049796A (en) * | 2001-12-17 | 2003-06-25 | 한국항공우주연구원 | Three-Fan Lifted Vertical Take-off and Landing Aircraft |
| CN103144769A (en) * | 2013-03-05 | 2013-06-12 | 西北工业大学 | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct |
| CN105292444A (en) * | 2014-07-08 | 2016-02-03 | 吴建伟 | Vertical take-off and landing aircraft |
| CN104369863A (en) * | 2014-10-31 | 2015-02-25 | 吴建伟 | Composite vertical take-off/landing aircraft |
| CN105151292A (en) * | 2015-05-25 | 2015-12-16 | 郝思阳 | Distributive vectored thrust system |
| CN105947192A (en) * | 2016-06-01 | 2016-09-21 | 中国航空工业集团公司西安飞机设计研究所 | Tilting double-duct unmanned aerial vehicle |
| CN106516100A (en) * | 2016-09-11 | 2017-03-22 | 珠海市磐石电子科技有限公司 | Vertical takeoff and landing aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110550208A (en) * | 2019-10-15 | 2019-12-10 | 中国计量大学 | Blade opening and closing mechanism based on rotary flapping wing vertical take-off and landing power device |
| WO2022067492A1 (en) * | 2020-09-29 | 2022-04-07 | 瑞鉴航太科技股份有限公司 | Aerial vehicle |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180216 |