CN106347655A - Duct power device and aircraft - Google Patents
Duct power device and aircraft Download PDFInfo
- Publication number
- CN106347655A CN106347655A CN201610882710.0A CN201610882710A CN106347655A CN 106347655 A CN106347655 A CN 106347655A CN 201610882710 A CN201610882710 A CN 201610882710A CN 106347655 A CN106347655 A CN 106347655A
- Authority
- CN
- China
- Prior art keywords
- duct
- power set
- guide shell
- cylinder
- duct power
- 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.)
- Granted
Links
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
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/001—Shrouded propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
-
- 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
Abstract
The invention discloses a duct power device and belongs to the field of power devices. The device comprises a duct barrel, a rotor wing, a driving device and an airflow turning device, wherein the inlet side of the duct barrel is provided with an arc-shaped lip opening extending outwards along a radial direction; the rotor wing is arranged in the duct barrel and is positioned at the lower side of the lip opening; the driving device drives the rotor wing; the airflow turning device comprises a guide cylinder and a helm gear for controlling the guide cylinder to incline around the radial direction; the guide cylinder is arranged in the duct barrel and is positioned at the lower side of the rotor wing; the inclination direction of the barrel wall of the guide cylinder along the radius direction is opposite to that of the rotor wing. The power device is relatively high in rectification efficiency, relatively light in weight and flexible in airflow turning.
Description
Technical field
The present invention relates to aircraft field, especially relate to a kind of duct power set for aircraft and there is this culvert
The aircraft of road power set.
Background technology
Multi-axis aircraft generally adopts fan-type duct power set, compared with the isolated fan of same diameter, fan-type
Duct compact conformation, the lift of generation is bigger, and safety is higher.Existing fan-type duct generally comprise duct cylinder, rotor with
And the driving means of driving rotor, duct cylinder upper end is the circular arc lip extending radially outward, and lip forms additional pulling force,
Increase the effect of duct cylinder entirety pulling force.Inside duct cylinder, the downside of rotor is provided with the flow deflector of inclination, incline direction with
Rotor incline direction is contrary, and flow deflector is used for revising air-flow rotation direction, prevents air-flow from rotating around the axis of duct cylinder, flow deflector is located
Position become middle position, when flow be located at tilts relative to middle position around radial direction when, air-flow from duct cylinder discharge after understand around duct
The axis rotation of cylinder.Driving means can be motor or the rotating shaft being driven by the motor outside duct or oil machine.
Chinese patent cn2753672u discloses a kind of vector thrust culvert pipe fan type single aircraft, and body afterbody is provided with balance tail
The wing, body left and right sides Parallel Symmetric is fixed with vectored thrust duct storehouse, and body front end position is also provided with vectored thrust duct
Storehouse, is provided with forward and backward two power set in vectored thrust duct storehouse, front power set and rear power set respectively with forward thrust
Fan is connected with back pressure fan, and vectored thrust duct storehouse rear portion is provided with horizontally arranged equidistant water conservancy diversion wind direction leaf, in arrow
Amount thrust duct storehouse rear end position has that water conservancy diversion Wind Direction Tablet is vertical with water conservancy diversion wind direction leaf to be connected.This aircraft needs the whole power that verts
Device could obtain horizontal component, and to adjust attitude, high to the intensity and loading demands of inclining rotary mechanism, reliability is low.China is specially
Sharp cn101353084a discloses a kind of light aerobat capable of landing or taking-off vertically, and its ducted fan propulsion system is included in duct
Fan, drive fan rotation electromotor and enging cabin, support duct duct pillar, wherein the rotary shaft of fan with drive
The longitudinal axis sailing cabin are parallel, and the attitude-adjusting system of this aircraft is predominantly arranged on the deflector of distant place below ducted fan,
It occupies larger space, and weight is larger, and regulated efficiency is relatively low, and steering flexibility is low.
Content of the invention
First goal of the invention of the present invention is: a kind of rectification efficiency of offer is higher, weight is lighter, air-flow steering is more flexible
Duct power set；
The second object of the present invention is to provide a kind of aircraft with this duct power set.
For achieving the above object: the duct power set that the present invention provides, comprising: duct cylinder, its entrance side is provided with along footpath
Lip to the arc stretching out；Rotor, is arranged in duct cylinder and is located at the downside of lip；Driving means, drive rotor；
Air-flow transfer, comprises guide shell and controls guide shell around the helm gear of radial skew；Guide shell is arranged in duct cylinder,
Downside positioned at rotor；
The barrel bending along radial direction of guide shell tilts, and this incline direction is contrary with the incline direction of rotor, bending recessed
Mouth direction is towards the outlet of duct cylinder..
As can be seen here, by arranging air-flow transfer in duct, substitute the frequent feed speed control of motor amplitude
Aircraft turns to, and indirectly improves the service life of motor；Duct is made integrally to incline with the steering wheel that verts of traditional dependence aircraft
Turn difference, control guide shell just to can control air flow deflector around radial skew using helm gear, realize the steering of aircraft, permissible
Reduce the power controlling helm gear, reduce weight, extend the flight time.Control guide shell and the monolithic flow deflector of air flow deflector
Compare, along the axis direction of duct, the conducting element of more low height size can be adopted, more effectively constrain air flow deflector, guide shell
Barrel incline direction radially is contrary with the incline direction of rotor, can reduce the windage of guide shell, improves air flow deflector effect
Rate.Additionally, guide shell is set directly in duct cylinder, closer to rotor, more effectively can capture air-flow, make high efficiency air flow
Deflection.
Further, guide shell is in up big and down small cone.Guide shell is conducive to making restrained in up big and down small cone
Deflection air-flow supercharging, formed higher pressure deflection jet-stream wind, improve duct power set steering flexibility.
Further, it is provided with the flow deflector extending along radius in guide shell, flow deflector is curved.Air-flow in duct is
Screw, in guide shell, the flow deflector further oar deflection air-flow of the arc of setting arranges smooth, raising deflection efficiency.
Further, flow deflector is located substantially at the middle part of guide shell circumference, and entrance is divided in flow deflector recess
The first entrance of side and the second entrance outside flow deflector recess, first entrance is less than second entrance.Guide shell is from middle position
Can ensure that guide shell obtains roughly the same deflection air-flow to both sides deflection, thus it is double to ensure that guide shell realizes reliable air-flow
Deflect to efficient.
Further, helm gear is arranged in duct cylinder, and on the downside of rotor, helm gear includes motor and reducing gear
Wheel group.Motor changes gear ratio by train of reduction gears, and gear-driven efficiency is higher, more stable reliability.Save space, is easy to contain
The installation of road power set, reduces the horizontal windage of the even whole aircraft of duct power set.
Further, air-flow transfer also includes position-limit mechanism, when described helm gear makes guide shell vert, makes to lead
The swing of flow cartridge；It is in minimum point when guide shell is located at middle position, when guide shell is swung sideward and turned, the entrance of guide shell more leans on
Nearly rotor.Further improve air-flow capture rate and the air-flow deflection efficiency of guide shell.
Further, position-limit mechanism includes fix bar and bent axle；Helm gear is fixed on duct cylinder by fix bar, leads
Flow cartridge is assemblied between duct cylinder and the shell of helm gear by bent axle, and bent axle one end is arranged in fix bar, and the other end leads to
Cross gear to engage with train of reduction gears, the pinion being engaged with gear teeth mouth is also equipped with bent axle.
This mechanism makes guide shell arrange near the outside of duct cylinder radial direction, and the air-flow of duct is concentrated mainly on culvert
Near the inwall of road cylinder, can be by less radial direction size, effectively utilizes air-flow, improves the utilization rate of air-flow, and carries
High steering efficiency.
Helm gear passes through internal motor and drives train of reduction gears rotation, because guide shell passes through bent axle and reduction gearing
Group engagement, therefore motor machine drives guide shell to rotate a certain angle indirectly；In order to improve the stability of guide shell rotation, in steering wheel
The shell of device offers gear teeth mouth, and the pinion that bent axle is installed is engaged with gear teeth mouth.In rotating shaft rotary course, bent axle leads to
Cross pinion to rotate around gear teeth mouth, further raising bent axle is around the stability of axial-rotation.Meanwhile, guide shell vert
During can lifting upwards, thus being increasingly closer to rotor bottom, thus obtaining larger spiral air flow, improve air-flow utilization
Rate and deflection efficiency.
Further, guide shell radially tilt angle in the range of positive and negative 35 °.Can be in relatively low wind in the range of being somebody's turn to do
Resistance is lower to realize stronger air flow deflector, air flow deflector ultrahigh in efficiency.
Further, in duct cylinder, coaxial line arranges driving means, rotor and air-flow transfer from top to bottom, drives dress
Put and be connected with duct cylinder by guide support, driving means are motor；By mounting disc and to be fitted around disk uniform for guide support
The deflector composition of distribution；Driving means are arranged on the upside of mounting disc, driving means output shaft stretch out from mounting disc through hole with
Rotor connects.
In the present invention, motor is directly installed in mounting disc, and deflector near mounting disc part vertically under
Fall, overall is in v shape, can install the motor of different model by this structure.In prior art, mounting disc has a support
Ring, the effect of support ring is to make its structure more firm, and motor will be enclosed within support ring could be affixed with mounting disc, directly limit electricity
The size of machine.Mounting disc is counter to be filled, and motor is directly installed in mounting disc, and support ring, in the opposite side of motor, can make structure steady
Gu again not limiting motor size.
Further, the outer wall of duct cylinder is provided with fender bracket, installation portion pass through bolt successively with fender bracket, duct cylinder and lead
Stream plate is affixed, and installation portion and mounting disc are in same level；Duct cylinder by upper under shrink axially inward；Deflector bottom
Offer wire casing.
In the present invention, offer wire casing in deflector centre position, the wire of controlled motor imports and motor from wire casing
Connect so as to more compact structure；The outside sheathed fender bracket of duct cylinder, makes culvert device be hardly damaged, and improves overall appearance simultaneously
Effect；Installation portion with mounting disc at grade, improves fixing rigidity.
Further, arc lip is circular arc lip, is provided with circumferential equally distributed guiding gutter.
In the present invention, on circular arc lip, increase the indent guiding gutter extending radially outward, strengthen duct lip position
The overall water conservancy diversion effect put, improves the suffered pulling force of duct cylinder.
For realizing another object, the invention provides aircraft, it includes fuselage and above-mentioned duct power set, duct
Power set are arranged on fuselage.Wherein aircraft can for two axle aircraft, three axle aircraft, four axles flight even six axles, eight
Axle aircraft.The rotor of aircraft is no longer necessary to frequently significantly acceleration and deceleration to control the flight attitude such as driftage and translation, saves energy
Amount, extends cruising time.
Further, duct power set have two, and two duct power set are symmetrically dispersed in institute by horn
State fuselage both sides..This aircraft passes through to adjust guide shell i.e. achievable fuselage pose adjustment, and whole power unit need not be driven to incline
Turn, lightweight, structure is reliable, and cruising time is long.
The invention has the benefit that controlling guide shell just to can control air flow deflector around radial skew using helm gear,
Realize the steering of aircraft, it is possible to reduce control the power of the helm gear that verts, reduce weight, extend the flight time, and rectification
In hgher efficiency, weight is lighter, air-flow turns to more flexible, cruising time length, is more easy to manipulate.
Brief description
Fig. 1 is the overall structure diagram of aircraft embodiment of the present invention；
Fig. 2 is the structural representation of duct power set embodiment of the present invention；
Fig. 3 is the structural decomposition diagram of Fig. 2；
Fig. 4 is the structural representation of air-flow transfer in duct power set embodiment of the present invention；
Fig. 5 is the structural representation of helm gear in duct power set embodiment of the present invention；
Fig. 6 is the internal structure schematic diagram of helm gear in duct power set embodiment of the present invention；
Fig. 7 is the structural representation of guide shell in duct power set embodiment of the present invention；
Fig. 8 is the structural representation of helm gear in duct power set embodiment of the present invention, illustrated therein is vertical state
Guide shell and the relative position of pinion；
Fig. 9 is the structural representation of helm gear in duct power set embodiment of the present invention, illustrated therein is left side and verts shape
The guide shell of state and the relative position of pinion；
Figure 10 is the structural representation of helm gear in duct power set embodiment of the present invention, illustrated therein is right side and verts shape
The guide shell of state and the relative position of pinion.
Specific embodiment
The present invention by specific embodiment and will be described with reference to the accompanying drawings.
Duct power set embodiment
As shown in figure 1, two axle aircraft include fuselage 7, and the duct power set 1 being arranged on fuselage 7 both sides.
As shown in Figures 2 and 3, duct power set 1 include duct cylinder 101, are arranged in duct cylinder 101 and are located at its lip
Rotor 4 on the downside of mouthful, the driving means 2 of driving rotor 4, and connect the guide support 3 of rotor 4 and driving means 2, wherein contain
The entrance of the arc lip 102 of road cylinder 101 extends radially outward, and arc lip 102 is uniformly laid with axial diversion groove
103；The cylinder outer wall of duct cylinder 101 is provided with fender bracket 104 and installation portion 105, and driving means 2, rotor 4 is gentle circulates to dress
Put 5 from top to bottom coaxial line arrangement.
Guide support 3 is by the mounting disc 301 being provided with central through hole, and is fitted around the equally distributed bottom of disk 301 and sets
Be made up of the deflector 302 of wire casing 303, the wire of controlled motor from wire casing 303 import with and be connected with controlled motor, thus tying
Structure is more compact, and driving means 2 are arranged on the top of mounting disc 301, and driving means 2 output shaft stretches out from mounting disc 301 through hole
It is connected with rotor 4.Installation portion 105 is connected with fender bracket 104, duct cylinder 101 and deflector 302 successively by bolt.
As shown in Figures 4 to 7, air-flow transfer 5 includes being arranged in duct cylinder 101 and is located at leading of rotor 4 downside
Flow cartridge 502, and control guide shell 502 around the helm gear 501 of radial skew, the barrel of guide shell 502 is around radial skew side
To contrary with the incline direction of rotor 4.
The position-limit mechanism 6 supporting guide shell 502 includes for air-flow transfer 5 being integrally attached to duct cylinder 101 tail end
γ type fix bar 601, by its by guide shell 502 be hinged on duct cylinder 101 and helm gear 501 cylinder shell outer wall it
Between bent axle 602, and be arranged on and engage with the gear teeth mouth 5011 in the middle part of the cylinder shell of helm gear 501 on bent axle 602
Pinion 603.Bent axle 602 input is engaged with the train of reduction gears 5013 of helm gear 501 by gear.
Helm gear 501 include cylinder shell, the motor 5012 being arranged in cylindrical shell body, and its input shaft with
The train of reduction gears 5013 of the output shaft engagement of motor 5012, the middle part circumference along cylinder shell symmetrically offers quantity at least
Gear teeth mouth 5011 for 2,
Guide shell 502 is up big and down small conical cylinder, and guide shell 502 is up big and down small cone, and the outer wall of guide shell 502 is in arc
Shape, has the flow deflector 5021 extending along radius in it, flow deflector 5021 is also curved.Flow deflector 5021 is located substantially at guide shell
The middle part of 502 circumferences, entrance is divided into the first entrance 5022 inside flow deflector 5021 recess and is located at flow deflector
Second entrance 5023 outside 5021 recesses, first entrance 5022 is less than second entrance 5023.
Guide shell 502 not around radial skew be tilt angle be 0 °, when being in vertical state, pinion 603 and gear teeth mouth
5011 engagement positions in the left side middle and lower part of gear teeth mouth 5011, as shown in Figure 8.
Helm gear 501 control guide shell 502 around footpath be tilted to the left maximum tilt angle be -35 ° when, pinion 603 and wheel
Tooth mouth 5011 engagement position in the right side middle and upper part of gear teeth mouth 5011, as shown in Figure 9.
Helm gear 501 control guide shell 502 around footpath be tilted to the right maximum tilt angle be+35 ° when, pinion 603 and wheel
Tooth mouth 5011 engagement position in the right side middle and lower part of gear teeth mouth 5011, as shown in Figure 10.
Aircraft embodiment
Aircraft includes fuselage and duct power set, and duct power set are arranged on fuselage, and duct power set can have
Two, fuselage both sides are arranged on by horn.
Above content is to further describe it is impossible to assert with reference to specific preferred implementation is made for the present invention
Being embodied as of the present invention is confined to these explanations.For general technical staff of the technical field of the invention,
Without departing from making some equivalent substitutes or obvious modification on the premise of present inventive concept, and performance or purposes are identical, all should
It is considered as belonging to the scope of patent protection that the present invention is determined by the claims submitted to.
Claims (13)
1. a kind of duct power set, comprising:
Duct cylinder, its entrance side is provided with the lip of the arc extending radially outward；
Rotor, is arranged in described duct cylinder and is located at the downside of described lip；
Driving means, drive described rotor；
It is characterized in that:
Air-flow transfer, the helm gear comprising guide shell and controlling described guide shell to vert around radial direction；
Described guide shell is arranged in described duct cylinder, positioned at the downside of described rotor；
The barrel bending along radial direction of described guide shell tilts, and this incline direction is contrary with the incline direction of described rotor,
The recess direction of described bending is towards the outlet of described duct cylinder.
2. duct power set as claimed in claim 1 it is characterised in that: described guide shell is in up big and down small cone.
3. duct power set as claimed in claim 2 it is characterised in that: be provided with described guide shell along radius extend
Flow deflector, described flow deflector is curved.
4. duct power set as claimed in claim 3, described flow deflector is located substantially at the middle part of described guide shell circumference, will
Entrance is divided into positioned at the first entrance inside described flow deflector recess and the second entrance outside described flow deflector recess,
Described first entrance is less than described second entrance.
5. the duct power set as described in any one of Claims 1-4 it is characterised in that: described helm gear is arranged on institute
State in duct cylinder, on the downside of described rotor, described helm gear includes motor and train of reduction gears.
6. duct power set as claimed in claim 5 it is characterised in that: described air-flow transfer also includes position restrainer
Structure, when described helm gear makes described guide shell vert, described position-limit mechanism controls described guide shell to swing；When described water conservancy diversion
Cylinder is in minimum point when being located at middle position, and when described guide shell is swung sideward and turned, the entrance of described guide shell is closer to described rotation
The wing.
7. duct power set as claimed in claim 6 it is characterised in that: described position-limit mechanism includes fix bar and bent axle；
Described helm gear is fixed on described duct cylinder by fix bar, and described guide shell is assemblied in described duct by described bent axle
Between cylinder and the shell of described helm gear, described bent axle one end is arranged in fix bar, and the other end passes through gear and reducing gear
Wheel group engages, and is also equipped with the pinion engaging with gear teeth mouth on described bent axle.
8. the duct power set as described in any one of Claims 1-4 it is characterised in that: described guide shell radially verts
Angle is in the range of positive and negative 35 °.
9. the duct power set as described in any one of Claims 1-4 it is characterised in that: described driving means, described rotor
Coaxially arrange from top to bottom in described duct cylinder with described air-flow transfer, described driving means pass through guide support
It is connected with described duct cylinder；
Described guide support forms by mounting disc and around the equally distributed deflector of described mounting disc；Described driving means peace
It is contained on the upside of described mounting disc, the output shaft of described driving means stretches out with described rotor even from the through hole of described mounting disc
Connect.
10. duct power set as claimed in claim 9 it is characterised in that: the outer wall of described duct cylinder is provided with fender bracket, peace
It is affixed with described fender bracket, described duct cylinder and described deflector successively that dress portion passes through bolt, described installation portion and described installation
Disk is in same level, and described deflector bottom offers wire casing.
A kind of 11. duct power set as described in any one of Claims 1-4 it is characterised in that: described arc lip is circle
Arc lip, offers thereon around axially equally distributed guiding gutter.
12. aircraft, including fuselage and duct power set it is characterised in that:
Described duct power set are the duct power set any one of claim 1 to 11, described duct power dress
Put and be arranged on described fuselage.
13. aircraft as described in claim 11 or 12 it is characterised in that:
Described duct power set have two, and two duct power set are symmetrically dispersed in described fuselage two by horn
Side.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610816440 | 2016-09-11 | ||
| CN2016108164403 | 2016-09-11 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106347655A true CN106347655A (en) | 2017-01-25 |
| CN106347655B CN106347655B (en) | 2019-11-29 |
Family
ID=57865773
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610882710.0A Active CN106347655B (en) | 2016-09-11 | 2016-10-07 | A kind of duct power device and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106347655B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108955423A (en) * | 2018-06-27 | 2018-12-07 | 西安恒宇众科空间技术有限公司 | A kind of non-priming system guided missile with water conservancy diversion air intake structure |
| CN110816811A (en) * | 2019-11-26 | 2020-02-21 | 滨州学院 | Air jet type steering unmanned aerial vehicle |
| TWI742727B (en) * | 2020-06-17 | 2021-10-11 | 林瑤章 | Propulsion device with double layers of guiding assembly and flying vehicle thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5149014A (en) * | 1989-02-27 | 1992-09-22 | Alexander Faller Maschinenbau | Rotary wing aircraft |
| US5295643A (en) * | 1992-12-28 | 1994-03-22 | Hughes Missile Systems Company | Unmanned vertical take-off and landing, horizontal cruise, air vehicle |
| CN1699114A (en) * | 2005-03-15 | 2005-11-23 | 王忠信 | Unmanned aerobat with ring-like wing |
| CN103332293A (en) * | 2013-06-13 | 2013-10-02 | 上海大学 | Tilting double-duct subminiature unmanned plane |
| CN204236766U (en) * | 2014-11-27 | 2015-04-01 | 哈尔滨盛世特种飞行器有限公司 | The novel control vane of culvert type list rotor unmanned aircraft |
| CN104859851A (en) * | 2015-04-27 | 2015-08-26 | 刘朝阳 | Multi-rotor aircraft driven by duct lift fans with diversion helms |
| CN105000180A (en) * | 2015-06-28 | 2015-10-28 | 杨盛 | Aircraft aerodynamic configuration device |
-
2016
- 2016-10-07 CN CN201610882710.0A patent/CN106347655B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5149014A (en) * | 1989-02-27 | 1992-09-22 | Alexander Faller Maschinenbau | Rotary wing aircraft |
| US5295643A (en) * | 1992-12-28 | 1994-03-22 | Hughes Missile Systems Company | Unmanned vertical take-off and landing, horizontal cruise, air vehicle |
| CN1699114A (en) * | 2005-03-15 | 2005-11-23 | 王忠信 | Unmanned aerobat with ring-like wing |
| CN103332293A (en) * | 2013-06-13 | 2013-10-02 | 上海大学 | Tilting double-duct subminiature unmanned plane |
| CN204236766U (en) * | 2014-11-27 | 2015-04-01 | 哈尔滨盛世特种飞行器有限公司 | The novel control vane of culvert type list rotor unmanned aircraft |
| CN104859851A (en) * | 2015-04-27 | 2015-08-26 | 刘朝阳 | Multi-rotor aircraft driven by duct lift fans with diversion helms |
| CN105000180A (en) * | 2015-06-28 | 2015-10-28 | 杨盛 | Aircraft aerodynamic configuration device |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108955423A (en) * | 2018-06-27 | 2018-12-07 | 西安恒宇众科空间技术有限公司 | A kind of non-priming system guided missile with water conservancy diversion air intake structure |
| CN110816811A (en) * | 2019-11-26 | 2020-02-21 | 滨州学院 | Air jet type steering unmanned aerial vehicle |
| TWI742727B (en) * | 2020-06-17 | 2021-10-11 | 林瑤章 | Propulsion device with double layers of guiding assembly and flying vehicle thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106347655B (en) | 2019-11-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106347655A (en) | Duct power device and aircraft | |
| CN103693194A (en) | Tilting four-rotor-wing aircraft | |
| CN206502014U (en) | A kind of single duct engine | |
| CN203638093U (en) | Tiltable four-rotor aircraft | |
| CN109533320A (en) | A kind of helicopter bevel-type main rotor parallel drive unit | |
| CN218479877U (en) | Horizontal shaft wind driven generator | |
| US6837457B2 (en) | Aircraft rotor and aircraft | |
| CN106379534B (en) | The control system that spins and aircraft | |
| CN205524972U (en) | High -efficient duct power device and use its aircraft | |
| CN108479241A (en) | A kind of novel drop haze dust removal machine | |
| CN206087305U (en) | Spin control system and aircraft | |
| CN106364665B (en) | Flying power system and aircraft | |
| CN205022860U (en) | Coaxial pair changes duct aircraft | |
| CN101092167A (en) | Dished aircraft | |
| CN207728490U (en) | A kind of wind power generating set | |
| CN206218208U (en) | Flying power system and aircraft | |
| CN106904270A (en) | A kind of high stability six rotorcraft | |
| CN109606167A (en) | Charging pile system of electric automobile | |
| CN106542094A (en) | Coaxially to turning duct aircraft | |
| CN109808866B (en) | Tumbler aircraft | |
| CN207644646U (en) | Unmanned plane tossed device | |
| CN206511120U (en) | Dalta wing is coaxial to turning duct aircraft | |
| CN207315573U (en) | Low pressure drainage type wind-driven generator | |
| CN206900670U (en) | A kind of transmission mechanism of multi-rotor aerocraft | |
| CN206871351U (en) | A kind of compound unmanned vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |