CN107719629A - Displacement multi-rotor unmanned aerial vehicle based on duct - Google Patents
Displacement multi-rotor unmanned aerial vehicle based on duct Download PDFInfo
- Publication number
- CN107719629A CN107719629A CN201710992953.4A CN201710992953A CN107719629A CN 107719629 A CN107719629 A CN 107719629A CN 201710992953 A CN201710992953 A CN 201710992953A CN 107719629 A CN107719629 A CN 107719629A
- Authority
- CN
- China
- Prior art keywords
- rotor
- duct
- shell
- transmission device
- aerial vehicle
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/16—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like specially adapted for mounting power plant
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/32—Blade pitch-changing mechanisms mechanical
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- 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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
Abstract
The invention provides a kind of displacement multi-rotor unmanned aerial vehicle based on duct, including shell and frame, described frame is that surface is rectangular configuration, frame central is disposed with flight control computer, flight control computer both sides have been sequentially distributed fuel tank, aero-engine and transmission device along frame respectively, and each transmission device is connected to a pair of rotors；It is load zones in the middle part of described shell, shell both ends have figure of eight duct, fourth officer rotor is arranged in the duct at shell both ends for a pair two-by-two, with the rotor partial intersection of one end two, ensures that its rotating speed is always consistent so as to will not be collided between rotor by transmission device.The present invention can avoid the adverse effect of rotor down-wash flow, can increase substantially rotor efficiency, increase full machine payload, while improve security.
Description
Technical field
The present invention relates to multi-rotor unmanned aerial vehicle field, specifically a kind of displacement multi-rotor unmanned aerial vehicle based on duct.
Background technology
Multi-rotor unmanned aerial vehicle, it is a kind of special unmanned vehicle with three and above rotor.Existing more rotors
Unmanned plane, by the motor rotation on each axle, rotor is driven, so as to produce a liter thrust.By changing between different rotors
Relative rotation speed, thus it is possible to vary the size of single shaft propulsive force, so as to carry out flight control.Have the following disadvantages：1）It is limited by electricity
Machine, it is difficult to which maximization development, payload is low, and cruising time is short；2）Classical square rotor-hub configuration causes payload only
It can be distributed in below rotor, and the high speed purling of rotor can have a negative impact；3）Rotor rotates at a high speed, and it is hidden to there is safety
Suffer from, while its mobility deficiency is controlled by changing rotating speed.With the growth requirement of every profession and trade, have to the demand of unmanned plane
Large increase, traditional electronic four rotor wing unmanned aerial vehicle can not meet the market demand, particularly short distance air transportation and disappear
The special industries such as anti-rescue are, it is necessary to a kind of heavy－duty and safe and reliable unmanned plane.
The content of the invention
The present invention is in order to solve problem of the prior art, there is provided a kind of displacement multi-rotor unmanned aerial vehicle based on duct, energy
The adverse effect of rotor down-wash flow is enough avoided, rotor efficiency can be increased substantially, increases full machine payload, while improve safety
Property.
The present invention includes shell and frame, and described frame is that surface is rectangular configuration, and frame central, which is disposed with, flies control meter
Calculation machine, flight control computer both sides have been sequentially distributed fuel tank, aero-engine and transmission device, each transmission device along frame respectively
It is connected to a pair of rotors；It is load zones in the middle part of described shell, shell both ends have figure of eight duct, fourth officer rotation
The wing is arranged in the duct at shell both ends for a pair two-by-two, with the rotor partial intersection of one end two, ensures its rotating speed by transmission device
It is always consistent so as to will not collide between rotor.
Further improve, described each rotor is connected by rotor wing rotation axle with transmission device, and rotor wing rotation axle connects
It is connected to pitch control mechanism, pitch control mechanism includes distance-variable rocker arm, pitch-change-link, rotating ring, determines ring, antitorque arm, steering wheel rocking arm
And steering wheel, it is cased with oar folder, rotating ring wherein on rotor wing rotation axle circumference successively from top to bottom and determines ring, rotor is fixed on oar folder,
Oar folder is connected to rotating ring by passing sequentially through distance-variable rocker arm and pitch-change-link；Determine ring to be connected with transmission device by antitorque arm, it is fixed
Ring is connected with steering wheel by steering wheel rocking arm.
Further improve, described load zones are provided with one kind or several in infrared detector, stretcher, fire-extinguishing shell launcher
Kind.
Further improve, described bottom of the frame is provided with undercarriage.
Beneficial effect of the present invention is：Using aero-engine as power set, large-sized displacement rotor is therewith
Match somebody with somebody, more traditional electronic four rotor of payload greatly improves；Unconventional rotor-hub configuration, payload area between rotor,
Avoid the adverse effect of rotor down-wash flow；Rotor intersects ensures that its appearance and size obtains while rotor diameter is further increased
To reduce, convenience in transport；Duct is designed as ' 8 ' fonts and with rotor intersected to match, and can increase substantially rotor efficiency, and increase is complete
Machine payload, while improve security.
Brief description of the drawings
Fig. 1 is duct displacement multi-rotor unmanned aerial vehicle total arrangement schematic diagram.
Fig. 2 is duct displacement multi-rotor unmanned aerial vehicle rack construction schematic diagram.
Fig. 3 is duct displacement multi-rotor unmanned aerial vehicle gesture stability schematic diagram.
Fig. 4 is duct rotor diagrammatic cross-section.
Fig. 5 is intersection rotor and figure of eight duct schematic diagram.
Fig. 6 is pitch control structural scheme of mechanism.
Embodiment
The invention will be further described below in conjunction with the accompanying drawings.
As depicted in figs. 1 and 2, including shell 1 and frame 8, the bottom of frame 8 are provided with undercarriage 7 to structure of the present invention.Frame
8 be that surface is rectangular configuration, and the center arrangement of frame 8 has flight control computer 11, and the both sides of flight control computer 11 are distinguished successively along frame 8
Fuel tank 10, aero-engine 9 and transmission device 12 is distributed with, each transmission device 12 is connected to a pair of rotors 6；Described
The middle part of shell 1 is load zones 2, and the both ends of shell 1 have figure of eight duct 19（As shown in Figure 5）, a pair two-by-two of fourth officer rotor
It is arranged in the duct 19 at the both ends of shell 1, with the partial intersection of rotor 6 of one end two, is formed and intersect rotor disk overlay region 18, by
Transmission device ensures that its rotating speed is always consistent so as to will not collide between rotor.
Duct displacement multi-rotor unmanned aerial vehicle gesture stability schematic diagram is as shown in figure 3, two engines pass through transmission device point
Two variable-distance rotor rotationals of same one end are not driven, while the rotating speed of two engines is always consistent, A rotors and C
Number rotor rotates clockwise, and B rotors and D rotors rotate counterclockwise.During hovering, 2 engines reach rated speed, and 4 is secondary
Rotor always away from being consistent；Forward fly when, C rotors and D rotors increase always away from；To the left during rolling, B rotors and C
The increase of number rotor always away from；To during left drift, B rotors and the increase of D rotors always away from;Other gesture stability modes with it is such
Seemingly.
As shown in figure 4, rotor rotates around rotor wing rotation axis 17, there are gap 15, duct lip between duct inwall and rotor
Mouth 14 and expansion segment 16 cause duct to have lift-rising effect.
Described each rotor 6 is connected by rotor wing rotation axle 24 with transmission device 12, and rotor wing rotation axle 24 is connected with
Pitch control mechanism（As shown in Figure 6）, pitch control mechanism include distance-variable rocker arm 21, pitch-change-link 22, rotating ring 23, determine ring 25,
Antitorque arm 26, steering wheel rocking arm 27 and steering wheel 28, wherein it is cased with oar folder 20 on the circumference of rotor wing rotation axle 24 successively from top to bottom, moves
Ring 23 is fixed on oar folder 21 with ring 25, rotor 6 is determined, and oar folder 20 is connected by passing sequentially through distance-variable rocker arm 21 and pitch-change-link 22
To rotating ring 23；Determine ring 25 to be connected with transmission device 12 by antitorque arm 26, determine ring 25 and steering wheel 28 is connected with by steering wheel rocking arm 27.
Described load zones 2 can be used for placing payload, be provided with infrared detector 3, stretcher 4, fire extinguisher bomb transmitting
One or more in device 5.For short distance air transportation, payload can be seasonal vegetable or Cold Chain Logistics product；With
In fire-fighting and rescue, payload can be relief goods, can also place stretcher and transport the wounded.It can increase for fire-fighting and rescue
Accessory infrared detector and fire extinguisher bomb emitter, preferably aid in fire-fighting search-and-rescue work.
Concrete application approach of the present invention is a lot, and described above is only the preferred embodiment of the present invention, it is noted that for
For those skilled in the art, under the premise without departing from the principles of the invention, some improvement can also be made, this
A little improve also should be regarded as protection scope of the present invention.
Claims (4)
1. a kind of displacement multi-rotor unmanned aerial vehicle based on duct, including shell（1）And frame（8）, it is characterised in that：Described machine
Frame（8）It is rectangular configuration for surface, frame（8）Center arrangement has flight control computer（11）, flight control computer（11）Both sides are along machine
Frame（8）Fuel tank has been sequentially distributed respectively（10）, aero-engine（9）And transmission device（12）, each transmission device（12）Respectively
It is connected with a pair of rotors（6）；Described shell（1）Middle part is load zones（2）, shell（1）Both ends have figure of eight duct
（19）, fourth officer rotor is arranged in shell a pair two-by-two（1）The duct at both ends（19）It is interior, with the rotor of one end two（6）Partial intersection.
2. the displacement multi-rotor unmanned aerial vehicle according to claim 1 based on duct, it is characterised in that：Described each rotor
（6）Pass through rotor wing rotation axle（24）With transmission device（12）Connection, rotor wing rotation axle（24）Pitch control mechanism is connected with, is become
Include distance-variable rocker arm away from operating mechanism（21）, pitch-change-link（22）, rotating ring（23）, determine ring（25）, antitorque arm（26）, steering wheel rocking arm
（27）And steering wheel（28）, wherein rotor wing rotation axle（24）It is cased with oar folder on circumference successively from top to bottom（20）, rotating ring（23）With it is fixed
Ring（25）, rotor（6）It is fixed on oar folder（21）On, oar folder（20）By passing sequentially through distance-variable rocker arm（21）And pitch-change-link（22）
It is connected to rotating ring（23）；Determine ring（25）Pass through antitorque arm（26）With transmission device（12）Connection, determines ring（25）Pass through steering wheel rocking arm
（27）It is connected with steering wheel（28）.
3. the displacement multi-rotor unmanned aerial vehicle according to claim 1 or 2 based on duct, it is characterised in that：Described load
Area（2）Infrared detector is installed（3）, stretcher（4）, fire-extinguishing shell launcher（5）In one or more.
4. the displacement multi-rotor unmanned aerial vehicle according to claim 1 or 2 based on duct, it is characterised in that：Described frame
（8）Bottom is provided with undercarriage（7）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710992953.4A CN107719629A (en) | 2017-10-23 | 2017-10-23 | Displacement multi-rotor unmanned aerial vehicle based on duct |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710992953.4A CN107719629A (en) | 2017-10-23 | 2017-10-23 | Displacement multi-rotor unmanned aerial vehicle based on duct |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107719629A true CN107719629A (en) | 2018-02-23 |
Family
ID=61213132
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710992953.4A Pending CN107719629A (en) | 2017-10-23 | 2017-10-23 | Displacement multi-rotor unmanned aerial vehicle based on duct |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107719629A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108341054A (en) * | 2018-04-27 | 2018-07-31 | 安徽工程大学 | A kind of unmanned plane rotor cutting angle regulating mechanism |
| CN108357676A (en) * | 2018-04-09 | 2018-08-03 | 重庆国飞通用航空设备制造有限公司 | A kind of multifunction emergency rescue multi-rotor unmanned aerial vehicle system |
| CN108860590A (en) * | 2018-08-30 | 2018-11-23 | 天津曙光天成科技有限公司 | A kind of multi-rotor unmanned aerial vehicle |
| CN109131857A (en) * | 2018-05-04 | 2019-01-04 | 江国春 | Petrol engine drives more rotor fire extinguishment rescue manned vehicles |
Citations (5)
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|---|---|---|---|---|
| CN104816823A (en) * | 2015-04-21 | 2015-08-05 | 南京航空航天大学 | Duct rotary wing aircraft |
| CN105644283A (en) * | 2016-03-24 | 2016-06-08 | 航沃科技（上海）有限公司 | Vertical take-off and landing hovercar |
| CN205523490U (en) * | 2016-03-24 | 2016-08-31 | 南京航空航天大学 | Four rotor VTOL hovercar |
| CN206277908U (en) * | 2016-12-01 | 2017-06-27 | 吉林大学 | A kind of electric automobile wheel position conversion device and land and air double-used electric automobile |
| CN207956029U (en) * | 2017-10-23 | 2018-10-12 | 南京航空航天大学 | Displacement multi-rotor unmanned aerial vehicle based on duct |
-
2017
- 2017-10-23 CN CN201710992953.4A patent/CN107719629A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104816823A (en) * | 2015-04-21 | 2015-08-05 | 南京航空航天大学 | Duct rotary wing aircraft |
| CN105644283A (en) * | 2016-03-24 | 2016-06-08 | 航沃科技（上海）有限公司 | Vertical take-off and landing hovercar |
| CN205523490U (en) * | 2016-03-24 | 2016-08-31 | 南京航空航天大学 | Four rotor VTOL hovercar |
| CN206277908U (en) * | 2016-12-01 | 2017-06-27 | 吉林大学 | A kind of electric automobile wheel position conversion device and land and air double-used electric automobile |
| CN207956029U (en) * | 2017-10-23 | 2018-10-12 | 南京航空航天大学 | Displacement multi-rotor unmanned aerial vehicle based on duct |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108357676A (en) * | 2018-04-09 | 2018-08-03 | 重庆国飞通用航空设备制造有限公司 | A kind of multifunction emergency rescue multi-rotor unmanned aerial vehicle system |
| CN108341054A (en) * | 2018-04-27 | 2018-07-31 | 安徽工程大学 | A kind of unmanned plane rotor cutting angle regulating mechanism |
| CN108341054B (en) * | 2018-04-27 | 2023-05-02 | 安徽工程大学 | Unmanned aerial vehicle rotor cutting angle adjustment mechanism |
| CN109131857A (en) * | 2018-05-04 | 2019-01-04 | 江国春 | Petrol engine drives more rotor fire extinguishment rescue manned vehicles |
| CN108860590A (en) * | 2018-08-30 | 2018-11-23 | 天津曙光天成科技有限公司 | A kind of multi-rotor unmanned aerial vehicle |
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