CN106986005A - A kind of structure of verting of the dynamic tilt rotor aircraft of oil - Google Patents
A kind of structure of verting of the dynamic tilt rotor aircraft of oil Download PDFInfo
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- CN106986005A CN106986005A CN201710198177.0A CN201710198177A CN106986005A CN 106986005 A CN106986005 A CN 106986005A CN 201710198177 A CN201710198177 A CN 201710198177A CN 106986005 A CN106986005 A CN 106986005A
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- verting
- type commutator
- oil
- drive
- drive shaft
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- 230000005540 biological transmission Effects 0.000 claims description 9
- 230000008878 coupling Effects 0.000 claims description 9
- 238000010168 coupling process Methods 0.000 claims description 9
- 238000005859 coupling reaction Methods 0.000 claims description 9
- 238000002627 tracheal intubation Methods 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims 1
- 230000007246 mechanism Effects 0.000 abstract description 17
- 238000010276 construction Methods 0.000 abstract description 3
- 239000011295 pitch Substances 0.000 description 8
- 230000009471 action Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 241000272184 Falconiformes Species 0.000 description 3
- 241000566150 Pandion haliaetus Species 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000012856 packing Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- 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
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
- B64C13/504—Transmitting means with power amplification using electrical energy using electro-hydrostatic actuators [EHA's]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Automation & Control Theory (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- General Details Of Gearings (AREA)
Abstract
The present invention relates to spacecraft field of power machinery, there is provided a kind of structure of verting of the dynamic tilt rotor aircraft of oil, including drive shaft system, L-type commutator, drive bearing group, bearing group of verting, electric pushrod；Drive shaft system is arranged in wing, for transmitting power；L-type commutator includes drive bevel gear, driven wheel of differential, and drive shaft system output end is connected with the drive bevel gear, and drive bevel gear is engaged with driven wheel of differential；Driven wheel of differential is connected with Propeller variable pitch structure；Drive bearing group supports drive bevel gear high-speed rotation in mounting flange；Bearing group of verting support L-type commutator verts around the cylindrical of mounting flange under the driving of the electric pushrod；Drive shaft system and the pivot of L-type commutator are coaxial.The present invention solves the problems, such as the big voyage endurance of the heavy－duty of electric propeller aircraft, is adapted to the inclining rotary mechanism of small and medium size unmanned aerial vehicles, and lightweight, simple in construction, modularized design, assembling is simple, easy disassembling.
Description
Technical field
The present invention relates to spacecraft field of power machinery, the structure of verting of more particularly to a kind of dynamic tilt rotor aircraft of oil.
Background technology
Tilting rotor：A kind of aircraft form, aircraft can produce the rotation that lift makees similar helicopter upwards by propeller
The wing flies；Propeller can also be verted to horizontal level and make fixed-wing flight.
In terms of inclining rotary mechanism, the V22 ospreys in the U.S. as active service tilt rotor aircraft, it is similar on mechanism action,
But its engine follows propeller to vert, though transmission is simple, structure of verting is excessively complicated.V22 is because engine follows spiral
Oar is verted, and causes wing tip load excessive, and very high request, thus security performance summary are all proposed to engine performance and pilot operator
Difference；V280 is expected to alleviate V22 technical problem, but can not thoroughly solve, and is limited by current structure, it is difficult to transplant for space
In the weight all small and medium size unmanned aerial vehicles of sensitivity, also flying quality can not be improved by further increasing aspect ratio.
U.S.'s future V280 schemes, its huge structure, it is adaptable to large transport airplane is not suitable for all quick to weight and size
The small and medium size unmanned aerial vehicles of sense, and can not increase outside inclining rotary mechanism contribute to improve aeroplane performance the winglet that verts.
Existing electric tilting rotor wing aircraft is limited by battery in load-carrying and voyage endurance, obtains great prominent in battery energy storage
Before broken, these shortcomings in a short time just can not to thoroughly solution.
Although the scheme model machine that row industry has propeller and winglet synchronously to vert in the country is put on display, belong to small-sized electronic
Unmanned plane, is limited by battery, and the same type aircraft that load-carrying can not all drive with voyage endurance with oil machine is compared.
The present invention is driven problem and passes through increase based on the problem of verting for solving the dynamic tilt rotor aircraft of middle-size and small-size oil
Winglet improves flying quality.
The content of the invention
The purpose of the present invention is exactly to overcome the defect of prior art there is provided a kind of knot that verts of the dynamic tilt rotor aircraft of oil
Structure, present invention mainly solves three Practical Project problems：
1st, the controllable tilting problem of propeller.Propeller needs to pause and drive in vertically and horizontally two position long periods；
Different from light-weight electric tilt rotor aircraft, electric propeller has very strong explosive force, can with switching state in the short time, with
The control of explosive force and autopilot by means of electric propeller, overcomes rapidly airplane inertial, is switched to from a kind of state of flight another
Plant state of flight.The dynamic tilt rotor aircraft of oil can generally do large aircraft, it is necessary between the two positions slowly with accurate
Linear speed is verted and hung down action, to avoid stall.What the present invention was primarily solved is exactly elemental motion problem of verting.
2nd, transmission problem of the propeller in inclining rotary mechanism.The large-scale tilting rotor transporter of active service and on sale electronic small
Type tilting rotor wing unmanned aerial vehicle, its engine or motor are at propeller, and drive mechanism is simple.Small-sized electric tilting rotor nobody
Machine there's almost no design shortcoming with this scheme, and only electronic unmanned plane is unable to big load, it is impossible to which the long endurance of voyage is intrinsic greatly
Defect.The dynamic tilt rotor aircraft of oil as similar osprey, the scheme that engine is placed under the propeller of two ends, though simplify
Transmission, but the overall rotary inertia of aircraft is added, belong to the position of aircraft roll stability worst, this is to the whole of engine
Body performance and the operative skill of driver are proposed challenge.The present invention need not follow propeller to incline by a kind of engine is provided
Turn, must even not be fixed on the solution near propeller.
3rd, the relevant issues of winglet can be expanded outside inclining rotary mechanism.Tilt rotor aircraft is fixed wing aircraft and helicopter aircraft
The set of advantage, is also spliting the difference for the two design shortcoming.It is limited by the position of inclining rotary mechanism and engine, the following U.S.
Though the aspect ratio of V280 tilt rotor aircrafts increased than V22 osprey, it can not still increase winglet to increase aspect ratio.This
To the ultimate run endurance of aircraft, stalling speed, safety and reliability have all been limited.The present invention carries for tilting rotor wing unmanned aerial vehicle
For the technical scheme of plug-in winglet, so that overall improve flying quality.
A kind of structure of verting of the dynamic tilt rotor aircraft of oil of the present invention, including drive shaft system, L-type commutator, drive bearing
Group, bearing group of verting, mounting flange, electric pushrod；
The drive shaft system is arranged in wing, for transmitting power；The drive shaft system output end and the L-type commutator are defeated
Enter end connection；The L-type commutator output end is connected with Propeller variable pitch structure；
The mounting flange is fixedly connected with fuselage or wing；The mounting flange aixs cylinder is cylindrical to be provided with bearing group of verting, institute
State and the L-type commutator is installed in bearing group of verting, the L-type commutator is under electric pushrod driving by the tiliting axis
Hold group supporting and surround the cylindrical low speed rotation of the mounting flange by the direction of rotation of bearing；The mounting flange endoporus is provided with
The drive bearing group, the drive shaft system and is existed by the constraint and supporting of the drive bearing group by the direction of rotation of bearing
Rotated at a high speed in the mounting flange；
The drive shaft system and the pivot of the L-type commutator are coaxial.
Further, the L-type commutator include drive bevel gear, driven wheel of differential, the drive shaft system output end with
The drive bevel gear connection, the drive bevel gear is engaged with driven wheel of differential；The driven wheel of differential and Propeller variable pitch
Structure is connected.
Further, the L-type commutator is the three section steering gears that two shaft couplings are constituted.
Further, the L-type commutator is flexible clutch.
Further, L-type commutator side corresponding with the winglet that verts is provided with tubulose push-pull structure, it is described vert it is small
Intubation is correspondingly arranged on the wing, after the L-type commutator and the winglet that verts are patched, is locked with anticreep pin.
Further, the Interface Shape of the tubulose push-pull structure is circular, ellipse or polygon.
Further, the quantity of the tubulose push-pull structure is 2 or multiple.
Further, the electric pushrod is that hydraulic-driven or steering wheel connecting rod drive.
Beneficial effects of the present invention are：
1st, it is adapted to the inclining rotary mechanism of small and medium size unmanned aerial vehicles, lightweight, simple in construction, modularized design, assembling is simple, and dismounting is held
Easily, transport motor-driven after being adapted to packing；
2nd, suitable for the tilt rotor aircraft of oil machine, the big voyage endurance of heavy－duty of electric propeller aircraft is solved the problems, such as；
3rd, the winglet interface that verts of the invention, can avoid similar V22 ospreys and the such wings of V280 big face when verting
Product stops propeller downwash flow, verts and the lift of High Angle of Attack is provided during switching to flat fly, and puts down and provides big during flying
The pressure difference lift of aspect ratio.
Brief description of the drawings
Fig. 1 show a kind of structure of the structure vertical landing state of verting of the dynamic tilt rotor aircraft of oil of the embodiment of the present invention
Schematic diagram.
Fig. 2 show a kind of structure of verting of the dynamic tilt rotor aircraft of oil of the embodiment of the present invention in the flat winged state of fixed-wing
Structural representation.
Fig. 3 show a kind of overall structure diagram of the structure of verting of the dynamic tilt rotor aircraft of oil of the embodiment of the present invention.
Fig. 4 show tubulose push-pull structure schematic diagram.
Fig. 5 show the three section steering gear schematic diagrames that two shaft couplings are constituted.
In figure：1- wings, 2- vert winglet, 3- electric pushrods, 4-L types commutator, 5- Propeller variable pitches structural assembly, 6-
Vert bearing group, 7- drive bearings group, 8- drive bevel gears, 9- driven wheels of differential, 10- drive shaft systems, 11- mounting flanges, 12-
Anticreep pin.
Embodiment
The specific embodiment of the invention is described in detail below in conjunction with specific accompanying drawing.It should be noted that in following embodiments
The combination of the technical characteristic or technical characteristic of description is not construed as isolated, and they can be mutually combined so as to reaching
To superior technique effect.In the accompanying drawing of following embodiments, the identical label that each accompanying drawing occurs represent identical feature or
Person's part, can be applied in not be the same as Example.
As Figure 1-4, a kind of structure of verting of the dynamic tilt rotor aircraft of oil of the embodiment of the present invention, including drive shaft system
10th, L-type commutator 4, drive bearing group 7, bearing group of verting 6, mounting flange 11, electric pushrod 3；
The drive shaft system 10 is arranged in wing 1, for transmitting power；The output end of drive shaft system 10 is changed with the L-type
Connected to the input of device 4；The output end of L-type commutator 4 is connected with Propeller variable pitch structure 5；
The mounting flange 11 is fixedly connected with fuselage or wing 1；The aixs cylinder of mounting flange 11 is cylindrical to be provided with the bearing that verts
Group 6, installs the L-type commutator 4 in the bearing group 6 of verting, the L-type commutator 4 under the electric pushrod 3 driving by
The bearing group 6 of verting supports and surrounds the cylindrical low speed rotation of the mounting flange 11 by the direction of rotation of bearing；The fixation
The endoporus of flange 11 is provided with the drive bearing group 7, the drive shaft system 10 by the drive bearing group 7 constraint and supporting,
And rotated at a high speed in the mounting flange 11 by the direction of rotation of bearing；
The drive shaft system 10 and the pivot of the L-type commutator 4 are coaxial.
The L-type commutator 4 can use drive bevel gear-driven wheel of differential structure, the output end of drive shaft system 10
It is connected with the drive bevel gear 8, the drive bevel gear 8 is engaged with driven wheel of differential 9；The driven wheel of differential 9 and spiral
Oar distance changing mechanism 5 is connected.
The three section steering gears that the L-type commutator 4 can also be constituted from two shaft couplings, replace bevel gear pair
The kind of drive.The L-type commutator 4 can also be flexible clutch.
It is right on tubulose push-pull structure, the winglet 2 that verts that the L-type commutator 4 is provided with the corresponding side of winglet 2 of verting
Intubation should be provided with, after the L-type commutator 4 and the winglet 2 that verts are patched, is locked with anticreep pin 12.The tubulose plug machine
The Interface Shape of structure is circular, ellipse or polygon.The quantity of the tubulose push-pull structure can be 2, or 2
More than.
The electric pushrod 3 is that hydraulic-driven or steering wheel connecting rod drive.
In actual applications, as shown in Figure 1-2, Propeller variable pitch structural assembly 5 is arranged on a L-type commutator 4, L
Type commutator 4 rotates under the driving of electric pushrod 3 along axis, so as to realize VTOL and the switching put down and flown of verting.It is electronic
The geometrical extension of push rod 3 can according to design requirement carry out high-precision servo control so that fit aircraft from VTOL to
The propeller pose adjustment curve of fixed-wing horizontal flight.
Inclining rotary mechanism drives propeller pitch motion, realizes the conversion in airscrew thrust direction, the power of propeller, then by
Line shaft inside wing 1 is passed over.Such as Fig. 3, power is transmitted by drive shaft system 10, by the initiative taper in L-type commutator 4
Gear 8 is delivered to driven wheel of differential 9, and driven wheel of differential 9 directly delivers power to Propeller variable pitch structural assembly 5.Wherein pass
Dynamic bearing group 7 supports the high-speed rotation in mounting flange 11 of bevel gear 8, to transmit the rotary power needed for propeller；Tiliting axis
Holding group 6 supports L-type commutator 4 to be verted around the cylindrical low speed under the driving of electric pushrod 3 of mounting flange 11.Wherein power transmission shaft
Rotating speed of the rotating speed when verting action executing for being 10 is 4000rpm, and action of verting was by 15 seconds complete tropometers in 90 °, and rotating speed is
1rpm.The latter is only the former 1/4000, and the transport motion influence produced by verting can be ignored.
Can be with the tubulose push-pull structure of fast insert-pull containing 2 on L-type commutator 4, such as Fig. 4, correspondence position on the winglet 2 that verts
Installed intubation, the two is patched finish after, locked with anticreep pin 12, prevent in flight course vibration to come off.
The present invention has following features：
1st, the design feature of L-type commutator 4 and inclining rotary mechanism.The key point of the design is the input shaft of L-type commutator 4 and verted
The pivot of mechanism is coaxial, and vertical 90 ° of output end is then realized under the promotion of electric pushrod 3 verts.According to existing structure,
Hydraulic push rod driving can be derived to vert, the driving of steering wheel connecting rod is verted, or even servomotor drives L-type commutator by gear
4 realize the scheme verted, and these schemes belong to the simple modification based on L-type commutator 4 and inclining rotary mechanism design feature；
2nd, the inside and outside concentric drive mechanism of mounting flange 11, L-type commutator 4 is done by bearing group 6 of verting around mounting flange 11
Pitch motion, coaxial drive bevel gear 8 is then supported by the drive bearing group 7 inside mounting flange 11, internally transmits dynamic
Power.The key point of this structure is inside and outside two sets of structure of bearings of mounting flange 11, and this structure belongs to the protection of the present invention
Point.The modulus of gear is changed in such as designing, pressure angle, helical angle belongs to the simple modification to the present invention；In this mounting flange
Under 11 inside and outside bearing arrangement support, internal drive can also be changed to the steering transmission of several Hooks coupling universal couplings, and such as Fig. 5 bores tooth
Wheel transmission could alternatively be the three section steering gears that two shaft couplings are constituted；The steering that two or more shaft couplings are constituted
Transmission mechanism can also be replaced realizing by single flexible shaft coupling turns to transmission；
3rd, the fixed character of winglet 2 of verting on L-type commutator 4, is the protection point of the present invention.Therebetween connecting-disconnecting interface, can
To be circular, ellipse, rectangle or even polygon, interface length can have length thickness because of the difference of load, even
The quantity increase of interface is two or more, and these belong to simple change；Other latch structure can be derived by cotter pin
Variously-shaped radome fairing is added in the pin of other shapes, or outside, and these fall within simple change, as long as being changed based on L-type
To the outside of device 4, add and the winglet 2 that verts fixation interface, belong to the row of the protection of the present invention.
Beneficial effects of the present invention are：
1st, it is adapted to the inclining rotary mechanism of small and medium size unmanned aerial vehicles, lightweight, simple in construction, modularized design, assembling is simple, and dismounting is held
Easily, transport motor-driven after being adapted to packing；
2nd, suitable for the tilt rotor aircraft of oil machine, the big voyage endurance of heavy－duty of electric propeller aircraft is solved the problems, such as；
3rd, the winglet interface that verts of the invention, can avoid similar V22 ospreys and the such wings of V280 big face when verting
Product stops propeller downwash flow, verts and the lift of High Angle of Attack is provided during switching to flat fly, and puts down and provides big during flying
The pressure difference lift of aspect ratio.
Although having been presented for several embodiments of the present invention herein, it will be appreciated by those of skill in the art that
Without departing from the spirit of the invention, the embodiments herein can be changed.Above-described embodiment be it is exemplary, no
The restriction of interest field of the present invention should be used as using the embodiments herein.
Claims (8)
1. a kind of structure of verting of the dynamic tilt rotor aircraft of oil, it is characterised in that including drive shaft system, L-type commutator, power transmission shaft
Hold group, bearing group of verting, mounting flange, electric pushrod；
The drive shaft system is arranged in wing, for transmitting power；The drive shaft system output end and the L-type commutator are defeated
Enter end connection；The L-type commutator output end is connected with Propeller variable pitch structure；
The mounting flange is fixedly connected with fuselage or wing；The mounting flange aixs cylinder is cylindrical to be provided with bearing group of verting, institute
State and the L-type commutator is installed in bearing group of verting, the L-type commutator is under electric pushrod driving by the tiliting axis
Hold group supporting and surround the cylindrical low speed rotation of the mounting flange by the direction of rotation of bearing；The mounting flange endoporus is provided with
The drive bearing group, the drive shaft system and is existed by the constraint and supporting of the drive bearing group by the direction of rotation of bearing
Rotated at a high speed in the mounting flange；
The drive shaft system and the pivot of the L-type commutator are coaxial.
2. the structure of verting of the dynamic tilt rotor aircraft of oil as claimed in claim 1, it is characterised in that the L-type commutator bag
Drive bevel gear, driven wheel of differential are included, the drive shaft system output end is connected with the drive bevel gear, the drive bevel gear
Engaged with driven wheel of differential；The driven wheel of differential is connected with Propeller variable pitch structure.
3. the structure of verting of the dynamic tilt rotor aircraft of oil as claimed in claim 1, it is characterised in that the L-type commutator is
The three section steering gears that two shaft couplings are constituted.
4. the structure of verting of the dynamic tilt rotor aircraft of oil as claimed in claim 1, it is characterised in that the L-type commutator is
Flexible clutch.
5. the structure of verting of the dynamic tilt rotor aircraft of oil as claimed in claim 1, it is characterised in that the L-type commutator with
The winglet that verts correspondence side, which is provided with tubulose push-pull structure, the winglet that verts, is correspondingly arranged on intubation, the L-type commutator
After being patched with the winglet that verts, locked with anticreep pin.
6. the structure of verting of the dynamic tilt rotor aircraft of oil as claimed in claim 5, it is characterised in that the tubulose push-pull structure
Interface Shape be circular, ellipse or polygon.
7. the structure of verting of the dynamic tilt rotor aircraft of oil as claimed in claim 5, it is characterised in that the tubulose push-pull structure
Quantity be 2 or multiple.
8. the structure of verting of the dynamic tilt rotor aircraft of oil as claimed in claim 1, it is characterised in that the electric pushrod is liquid
Pressure driving or the driving of steering wheel connecting rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710198177.0A CN106986005B (en) | 2017-03-29 | 2017-03-29 | Tilting structure of oil-driven tilting rotary wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710198177.0A CN106986005B (en) | 2017-03-29 | 2017-03-29 | Tilting structure of oil-driven tilting rotary wing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106986005A true CN106986005A (en) | 2017-07-28 |
| CN106986005B CN106986005B (en) | 2024-02-13 |
Family
ID=59413422
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710198177.0A Active CN106986005B (en) | 2017-03-29 | 2017-03-29 | Tilting structure of oil-driven tilting rotary wing aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN106986005B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109911179A (en) * | 2019-03-13 | 2019-06-21 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of pusher rotary-wing aircraft and its control method of VTOL and high-speed flight |
| CN109911178A (en) * | 2019-03-13 | 2019-06-21 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of tail-rotor for rotary-wing aircraft and propulsion sharing system and control method |
| WO2020151608A1 (en) * | 2019-01-25 | 2020-07-30 | 深圳市旗客智能技术有限公司 | Rotary-wing unmanned aerial vehicle |
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| CN203332392U (en) * | 2013-03-27 | 2013-12-11 | 南京傲翼伟滕自动化科技有限公司 | Tiltable-rotation type fixed-wing unmanned aerial vehicle |
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| US20060239824A1 (en) * | 2003-01-23 | 2006-10-26 | Robertson Daniel B | Proprotor blade with leading edge slot |
| CN1458030A (en) * | 2003-05-26 | 2003-11-26 | 韩培洲 | Horizontal and vertical take-off and landing plane with tilted front rotary wing |
| US20100193644A1 (en) * | 2008-04-25 | 2010-08-05 | Abe Karem | Aircraft with Integrated Lift and Propulsion System |
| CN101314409A (en) * | 2008-07-10 | 2008-12-03 | 周武双 | Swallow type inclined rotation rotorcraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2020151608A1 (en) * | 2019-01-25 | 2020-07-30 | 深圳市旗客智能技术有限公司 | Rotary-wing unmanned aerial vehicle |
| CN109911179A (en) * | 2019-03-13 | 2019-06-21 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of pusher rotary-wing aircraft and its control method of VTOL and high-speed flight |
| CN109911178A (en) * | 2019-03-13 | 2019-06-21 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of tail-rotor for rotary-wing aircraft and propulsion sharing system and control method |
| CN109911179B (en) * | 2019-03-13 | 2022-11-04 | 南京灵龙旋翼无人机系统研究院有限公司 | Propulsion type rotary wing aircraft capable of vertically taking off and landing and flying at high speed and control method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106986005B (en) | 2024-02-13 |
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