CN106882371A - A kind of hybrid tilting rotor wing unmanned aerial vehicle - Google Patents
A kind of hybrid tilting rotor wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106882371A CN106882371A CN201710132598.3A CN201710132598A CN106882371A CN 106882371 A CN106882371 A CN 106882371A CN 201710132598 A CN201710132598 A CN 201710132598A CN 106882371 A CN106882371 A CN 106882371A
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- CN
- China
- Prior art keywords
- wing
- piggyback pod
- unmanned plane
- propeller
- piggyback
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- 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.)
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Classifications
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
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- 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
- B64U50/11—Propulsion using internal combustion piston engines
-
- 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
Abstract
A kind of hybrid tilting rotor wing unmanned aerial vehicle, including body, dynamical system, control system and inclining rotary mechanism.Body is made up of fuselage, wing and empennage；Dynamical system is made up of the propeller piggyback pod and afterbody duct piggyback pod at wing two ends, and each piggyback pod can be carried out wide-angle and vert；Control system flat to aircraft can fly and winged state of hanging down carries out stabilization and gesture stability；Inclining rotary mechanism is responsible for changing three piggyback pod tilt angles.When unmanned plane is in many rotor modes, can be with VTOL and hovering；When unmanned plane is in fixed-wing pattern, flying speed is very fast, and efficiency is higher.The present invention has merged the advantage of many rotors and fixed-wing, has broad application prospects.
Description
Technical field
The invention belongs to aviation aircraft design field, more particularly to a kind of tilting rotor wing unmanned aerial vehicle.
Background technology
For a long time, people are seeking to have the aircraft of many gyroplanes and fixed-wing aircraft advantage concurrently always.By visiting for many years
Rope and practice, the V-22 " osprey " for occur in that such as U.S.'s first generation tilting rotor prototype verification machine XV-15, being on active service vert
Gyroplane, " hawkeye " tilting rotor wing unmanned aerial vehicle etc., have played important function, before wide development in dual-use field
Scape.Tilting rotor wing unmanned aerial vehicle not only has the advantages that multi-rotor unmanned aerial vehicle VTOL, hovering, while also having and fixation
The suitable flying speed of wing aircraft, voyage and load-carrying ability.But due to the tiltrotor that osprey is double dynamical cabin, flight control
System is complex, hang down fly and vert hang down fly it is flat fly over the state of flight crossed when, have that longitudinal stability is poor, operation is stranded
Difficult the problems such as, for osprey in longitudinally operation and deficiency present on stable type, with three new rotations of verting of piggyback pod
Wing scheme is suggested.
The A of China Patent Publication No. CN 102632994 propose a kind of tilting rotor scheme, in the program, in every section of wing
A propeller piggyback pod that can be verted respectively is installed in portion, and afterbody installs a fixed propeller piggyback pod, propeller rotation
Axis is vertical with fuselage axis.
The tilting rotor scheme that the A of China Patent Publication No. CN 106143895 are proposed is similar to the above, and difference is
The piggyback pod of afterbody can be realized verting.
The A schemes of China Patent Publication No. CN 105775122 use Flying-wing, two preceding piggyback pods pair that can be verted
Claim at head, connected by a connecting rod, afterbody is made up of a fixed rear piggyback pod.On each piggyback pod, all by one
To propeller generation thrust coaxial but that steering is opposite.
On the whole, the tilting rotor scheme with three piggyback pods exists compared to the tiltrotor in double dynamical cabin
The stability of longitudinal direction, is greatly improved in maneuverability, but is needed as can be seen that still there are many deficiencies from above scheme
Improve.On the one hand, in the design of afterbody power end, mostly using propeller propulsion, in flat flying, if afterbody is not provided
Power output, will produce larger resistance, the flat winged performance of influence aircraft.On the other hand, two preceding piggyback pods are arranged on the wing wing
In, this can make aircraft when hanging down winged, and the purling major part that propeller is produced is blocked by aerofoil, and power loss is more serious, shadow
Ring winged performance of hanging down.In the scheme of the A of patent publication No. CN 105775122, although two preceding piggyback pods are not blocked by wing,
But the flight resistance when construction weight peace that the presence of connecting rod increased aircraft flies.
The content of the invention
The purpose of the present invention is directed to the deficiency that above-mentioned prior art is present, and designs a kind of flight control system simply, stability
By force, reliability is high, is easy to the new tilting rotor wing unmanned aerial vehicle of operation.
The purpose of the present invention is realized by following any technical scheme.
A kind of hybrid tilting rotor wing unmanned aerial vehicle, including body, dynamical system, control system and inclining rotary mechanism.Body by
Fuselage, wing and empennage are constituted；Dynamical system is made up of the propeller piggyback pod and afterbody duct piggyback pod at wing two ends, each dynamic
Power cabin can carry out wide-angle and vert；Control system flat to aircraft can fly and winged state of hanging down carries out stabilization and gesture stability；
Inclining rotary mechanism is responsible for changing three piggyback pod tilt angles.
According to the unmanned plane of any of the above-described technical scheme, it is characterised in that it is described can tilted propeller piggyback pod be located at machine
Wing two ends.
According to the unmanned plane of any of the above-described technical scheme, it is characterised in that it is described two can tilted propeller piggyback pod
Propeller direction of rotation is opposite.
According to the unmanned plane of any of the above-described technical scheme, it is characterised in that the inclining rotary mechanism acts only on each piggyback pod,
Setting angle without changing wing and empennage.
According to the unmanned plane of any of the above-described technical scheme, it is characterised in that the power type of three piggyback pods is electricity
Dynamic, oil is moved or oil electricity mixing.
According to the unmanned plane of any of the above-described technical scheme, it is characterised in that the unmanned aerial vehicle control system includes that flight is controlled
System processed, attitude measurement system and optional IMAQ and Transmission system.
In one more specifically technical scheme, the present invention provides a kind of hybrid tilting rotor wing unmanned aerial vehicle, including machine
Body, dynamical system, control system and inclining rotary mechanism, body are made up of fuselage, wing, empennage.Compared to the double dynamical cabin with osprey
Layout, dynamical system of the present invention is made up of two, wing two ends propeller piggyback pod and the part of afterbody duct piggyback pod three, in etc.
Lumbar triangle shape is distributed, and each piggyback pod can carry out wide-angle and vert, and realizes many rotors and fixed-wing both of which
Conversion；By flight control system, the system composition such as attitude measurement system, the winged state that flat to aircraft can fly to hang down is carried out control system
Stabilization and gesture stability；Inclining rotary mechanism is made up of actuation mechanism and connecting rod, is responsible for changing three piggyback pod tilt angles.Work as wing
Two ends piggyback pod verts upwards, and when duct piggyback pod verts downwards, unmanned plane is in many rotor modes, can be with VTOL and sky
Middle hovering；When wing two ends, propeller piggyback pod is tilted forward, and when duct motor verts backward, unmanned plane is in fixed-wing mould
Formula, flying speed is very fast, and efficiency is higher.Additionally, the layout type of three piggyback pods improves aircraft and hangs down flying and transition stage
Stability and mobility, have broad application prospects.
The duct piggyback pod that the unmanned plane use can vert is moved as the power output of afterbody compared to using propeller
There is larger advantage in power cabin as the unmanned plane of afterbody power output.On the one hand, when aircraft hangs down winged, duct internal fan rotating speed
Height, can produce larger thrust.And because ducted fan oar footpath is smaller, the extra yawing of generation is also smaller, because
This, afterbody employs duct piggyback pod and avoids the need for two rotational speed differences of propeller piggyback pod to offset extra moment of torsion, this
Balance control when sample is conducive to aircraft to hang down winged；On the other hand, because duct internal fan internal diameter is smaller, and fan has outside duct
Parcel, when aircraft is flat winged, the front face area of afterbody duct piggyback pod is smaller, and duct surface and the round and smooth mistake in aft fuselage surface
Cross, the resistance produced when flat winged is smaller, is conducive to the high-speed flight of aircraft.Additionally, duct piggyback pod compact conformation, relative to one
As propeller piggyback pod quality it is smaller, reduce the take-off weight of aircraft.
In a specific technical scheme, two piggyback pods are arranged on wing two ends, had relative in the wing
There is following benefit：First, slightly to locate wing chord length smaller for the wing, and when aircraft is in hangs down winged state, propeller is washed under producing
Stream only about 15% is blocked by a bit of wing that the wing is slightly located, and most of air-flow can pass through wing, if piggyback pod is pacified
Mounted in wing middle part, then at least 50% downwash flow is blocked by wing, has seriously undermined the thrust of propeller；Secondly, piggyback pod
Slightly locate installed in the wing wing, the inclining rotary mechanism of piggyback pod can be allowed to have bigger design space, the steady of inclining rotary mechanism can be increased
Qualitative and reliability；Again, center of gravity of the piggyback pod slightly located installed in the wing wing away from whole machine farther out, can make aircraft hang down fly when
Fly control moment with bigger side, improve mobility when aircraft hangs down winged.
Beneficial effects of the present invention are：
The present invention is a kind of new tilting rotor being made up of three piggyback pods (each one of wing two ends, empennage one)
Aircraft, has many rotors and fixed-wing both of which concurrently.VTOL and hovering can be carried out under many rotor modes, makes it
Can be taken off landing without runway or other devices, the flight of high speed can be carried out under fixed-wing pattern, flight efficiency is higher.
The tilting rotor scheme has the advantage that compared to other schemes：Three piggyback pods are compared to two tiltrotors of piggyback pod
(such as osprey) has more a duct piggyback pod in afterbody, and when hanging down winged, aircraft increased the power that pitching can be controlled to operate
Square, this causes aircraft, and longitudinally operation is upper simpler, and stability is stronger, and reliability is higher；Afterbody is duct piggyback pod, when hanging down winged
Extra yawing is nearly free from, the resistance when design of culvert type can greatly reduce flight again in flat flying；Two
Preceding piggyback pod design is slightly located in the wing wing, reduces influence of the aerofoil to purling when flying of hanging down, and increased the design of inclining rotary mechanism
Space, also improves the mobility hung down when flying.
Brief description of the drawings
Fig. 1 is overall pattern of the unmanned plane of the present invention under fixed-wing pattern；
Fig. 2 is overall pattern of the unmanned plane of the present invention under many rotor modes；
Fig. 3 is that unmanned drive end unit of the invention is vertical flies flat winged detail view；
1 fuselage in figure, 2 wings, 3 empennages, 4 wing propeller piggyback pods, 5 propellers, 6 duct piggyback pods, 7 aileron rudders
Face, 8 empennage rudder faces, 9 drivers, 10 power fans
Specific embodiment
In order that technical problem solved by the invention, technical scheme and beneficial effect become more apparent, below in conjunction with
Drawings and Examples, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein is only used to
The present invention is explained, is not intended to limit the present invention.
Wing piggyback pod 4 Y1 can rotate around the shaft, and duct piggyback pod 6 can be in the perpendicular where aircraft axis
Inside Y2 rotations around the shaft, by inclining rotary mechanism control, realize the switching between rotor mode and fixed-wing pattern.
When unmanned plane is in many rotor modes, wing propeller piggyback pod 4 verts to vertical with the axis of fuselage 1 upwards, contains
Road piggyback pod 6 is dipped down and goes to vertical with the axis of fuselage 1, all produces downward thrust, and the steady of aircraft is kept by control system
It is qualitative.During aircraft forward-reverse, wing two ends propellers piggyback pod 4 and the Differential Control of duct piggyback pod 6；It is left when aircraft side flies
The Differential Control of starboard wing propeller piggyback pod 4；During yawed flight, the wing of termination two is adjusted by the inclining rotary mechanism of wing or so
The tilt angle of piggyback pod 4 is controlled.To sum up, unmanned plane hang down fly when, can realize VTOL, hovering, it is preceding it is winged, after
Fly, side fly etc. action.
When unmanned plane is in fixed-wing pattern, wing two ends propeller piggyback pod is tilted forward, and duct piggyback pod retreats
Turn, rolling movement is controlled by aileron rudder face 7, pitching and driftage operation are carried out by empennage rudder face 8, the common fixed-wing of operation format
Aircraft is consistent.Under fixed-wing pattern, the speed of aircraft horizontal movement gets a promotion, and realizes high-speed maneuver.
Claims (6)
1. a kind of hybrid tilting rotor wing unmanned aerial vehicle, including body, dynamical system, control system and inclining rotary mechanism.Body is by machine
Body, wing and empennage are constituted；Dynamical system is made up of the propeller piggyback pod and afterbody duct piggyback pod at wing two ends, each power
Cabin can carry out wide-angle and vert；Control system flat to aircraft can fly and winged state of hanging down carries out stabilization and gesture stability；Incline
Rotation mechanism is responsible for changing three piggyback pod tilt angles.
2. unmanned plane according to claim 1, it is characterised in that it is described can tilted propeller piggyback pod be located at the two of wing
End.
3. unmanned plane according to claim 1, it is characterised in that it is described two can tilted propeller piggyback pod propeller
Direction of rotation is opposite.
4. unmanned plane according to claim 1, it is characterised in that the inclining rotary mechanism acts only on each piggyback pod, without
Change the setting angle of wing and empennage.
5. unmanned plane according to claim 1, it is characterised in that the power type of three piggyback pods is electronic, oil
Dynamic or oil electricity mixing.
6. unmanned plane according to claim 1, it is characterised in that the unmanned aerial vehicle control system includes flight control system
System, attitude measurement system and optional IMAQ and Transmission system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710132598.3A CN106882371A (en) | 2017-03-07 | 2017-03-07 | A kind of hybrid tilting rotor wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710132598.3A CN106882371A (en) | 2017-03-07 | 2017-03-07 | A kind of hybrid tilting rotor wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106882371A true CN106882371A (en) | 2017-06-23 |
Family
ID=59180235
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710132598.3A Pending CN106882371A (en) | 2017-03-07 | 2017-03-07 | A kind of hybrid tilting rotor wing unmanned aerial vehicle |
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| CN (1) | CN106882371A (en) |
Cited By (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107458579A (en) * | 2017-08-01 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of unmanned plane device |
| CN107585305A (en) * | 2017-10-10 | 2018-01-16 | 王根英 | A kind of light and handy unmanned plane |
| CN107639984A (en) * | 2017-10-23 | 2018-01-30 | 大连理工大学 | It is a kind of can the aeroamphibious latent four of VTOL dwell three rotor wing unmanned aerial vehicles that vert |
| CN107738748A (en) * | 2017-10-16 | 2018-02-27 | 成都军融项目管理有限公司 | A kind of multipurpose Dual module combined type hybrid power unmanned plane |
| CN107933909A (en) * | 2017-12-17 | 2018-04-20 | 北京天宇新超航空科技有限公司 | A kind of high-speed and high-efficiency tilting wing unmanned vehicle |
| CN108382579A (en) * | 2018-05-06 | 2018-08-10 | 北京天宇新超航空科技有限公司 | A kind of new and effective tilting rotor unmanned vehicle |
| CN108639334A (en) * | 2018-07-17 | 2018-10-12 | 张家淦 | A kind of interurban logistics transportation system based on tilting rotor shipping unmanned plane |
| CN108725773A (en) * | 2018-08-06 | 2018-11-02 | 云呈通信息科技（上海）有限公司 | A kind of unmanned transporter |
| CN108791874A (en) * | 2018-06-21 | 2018-11-13 | 南京航空航天大学 | A kind of tilting duct power unmanned vehicle |
| CN109407692A (en) * | 2017-08-17 | 2019-03-01 | 西安羚控电子科技有限公司 | Vert Yaw control method under VTOL fixed-wing unmanned plane rotor mode |
| WO2019079930A1 (en) * | 2017-10-23 | 2019-05-02 | 大连理工大学 | Sea-air-land-dive four-environment tilting three-rotor unmanned aerial vehicle capable of vertical take-off and landing |
| CN110155317A (en) * | 2019-05-13 | 2019-08-23 | 中国人民解放军国防科技大学 | Oil-electricity hybrid vertical take-off and landing fixed-wing aircraft |
| CN110723284A (en) * | 2018-07-17 | 2020-01-24 | 刘建国 | Vertical lifting fixed wing aircraft with tiltable ducted fan |
| CN110949654A (en) * | 2019-12-25 | 2020-04-03 | 彭振根 | Aircraft |
| CN111268089A (en) * | 2019-11-22 | 2020-06-12 | 湖北航天飞行器研究所 | Double-fuselage vertical take-off and landing fixed wing unmanned aerial vehicle structure |
| CN111332465A (en) * | 2019-12-09 | 2020-06-26 | 湖北航天飞行器研究所 | Propeller and ducted fan combined type tilt rotor unmanned aerial vehicle and flight mode |
| CN112224400A (en) * | 2020-10-19 | 2021-01-15 | 南京航空航天大学 | Novel tilt rotor aircraft and working method thereof |
| CN112947528A (en) * | 2021-03-24 | 2021-06-11 | 南京航空航天大学 | Tilt-rotor aircraft flight control method and system oriented to high-low undulating terrain environment |
| CN112937851A (en) * | 2021-02-01 | 2021-06-11 | 河北利翔航空科技有限公司 | Vertical take-off and landing fixed wing aircraft using coanda effect for increasing lift |
| CN113260566A (en) * | 2018-12-28 | 2021-08-13 | 列奥纳多股份公司 | Thrust reverser aircraft and associated control method |
| CN113460300A (en) * | 2021-08-16 | 2021-10-01 | 江西洪都航空工业股份有限公司 | Carrying equipment suitable for single flight |
| CN113697097A (en) * | 2021-09-01 | 2021-11-26 | 中国航空研究院 | Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary wings |
| CN114056557A (en) * | 2020-07-29 | 2022-02-18 | 中国科学院沈阳自动化研究所 | Hybrid power tilt rotor unmanned aerial vehicle |
| CN115123535A (en) * | 2022-08-11 | 2022-09-30 | 北京北航天宇长鹰无人机科技有限公司 | Tilt wing unmanned aerial vehicle |
| CN115157944A (en) * | 2022-06-30 | 2022-10-11 | 中国航天空气动力技术研究院 | Solar energy range-extending electric aerocar |
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Cited By (32)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107458579A (en) * | 2017-08-01 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of unmanned plane device |
| CN109407692A (en) * | 2017-08-17 | 2019-03-01 | 西安羚控电子科技有限公司 | Vert Yaw control method under VTOL fixed-wing unmanned plane rotor mode |
| CN107585305A (en) * | 2017-10-10 | 2018-01-16 | 王根英 | A kind of light and handy unmanned plane |
| CN107738748A (en) * | 2017-10-16 | 2018-02-27 | 成都军融项目管理有限公司 | A kind of multipurpose Dual module combined type hybrid power unmanned plane |
| CN107639984A (en) * | 2017-10-23 | 2018-01-30 | 大连理工大学 | It is a kind of can the aeroamphibious latent four of VTOL dwell three rotor wing unmanned aerial vehicles that vert |
| US11305873B2 (en) | 2017-10-23 | 2022-04-19 | Dalian University Of Technology | Air, sea and underwater tilt tri-rotor UAV capable of performing vertical take-off and landing |
| CN107639984B (en) * | 2017-10-23 | 2023-07-18 | 大连理工大学 | Sea, land, air and water amphibious four-purpose tilting three-rotor unmanned aerial vehicle capable of taking off and landing vertically |
| WO2019079930A1 (en) * | 2017-10-23 | 2019-05-02 | 大连理工大学 | Sea-air-land-dive four-environment tilting three-rotor unmanned aerial vehicle capable of vertical take-off and landing |
| CN107933909A (en) * | 2017-12-17 | 2018-04-20 | 北京天宇新超航空科技有限公司 | A kind of high-speed and high-efficiency tilting wing unmanned vehicle |
| CN108382579A (en) * | 2018-05-06 | 2018-08-10 | 北京天宇新超航空科技有限公司 | A kind of new and effective tilting rotor unmanned vehicle |
| CN108791874A (en) * | 2018-06-21 | 2018-11-13 | 南京航空航天大学 | A kind of tilting duct power unmanned vehicle |
| CN110723284A (en) * | 2018-07-17 | 2020-01-24 | 刘建国 | Vertical lifting fixed wing aircraft with tiltable ducted fan |
| CN108639334A (en) * | 2018-07-17 | 2018-10-12 | 张家淦 | A kind of interurban logistics transportation system based on tilting rotor shipping unmanned plane |
| CN108725773A (en) * | 2018-08-06 | 2018-11-02 | 云呈通信息科技（上海）有限公司 | A kind of unmanned transporter |
| CN113260566A (en) * | 2018-12-28 | 2021-08-13 | 列奥纳多股份公司 | Thrust reverser aircraft and associated control method |
| CN110155317A (en) * | 2019-05-13 | 2019-08-23 | 中国人民解放军国防科技大学 | Oil-electricity hybrid vertical take-off and landing fixed-wing aircraft |
| CN111268089A (en) * | 2019-11-22 | 2020-06-12 | 湖北航天飞行器研究所 | Double-fuselage vertical take-off and landing fixed wing unmanned aerial vehicle structure |
| CN111268089B (en) * | 2019-11-22 | 2021-12-07 | 湖北航天飞行器研究所 | Double-fuselage vertical take-off and landing fixed wing unmanned aerial vehicle structure |
| CN111332465A (en) * | 2019-12-09 | 2020-06-26 | 湖北航天飞行器研究所 | Propeller and ducted fan combined type tilt rotor unmanned aerial vehicle and flight mode |
| CN111332465B (en) * | 2019-12-09 | 2022-01-21 | 湖北航天飞行器研究所 | Propeller and ducted fan combined type tilt rotor unmanned aerial vehicle and flight mode |
| CN110949654A (en) * | 2019-12-25 | 2020-04-03 | 彭振根 | Aircraft |
| CN114056557A (en) * | 2020-07-29 | 2022-02-18 | 中国科学院沈阳自动化研究所 | Hybrid power tilt rotor unmanned aerial vehicle |
| CN112224400A (en) * | 2020-10-19 | 2021-01-15 | 南京航空航天大学 | Novel tilt rotor aircraft and working method thereof |
| CN112937851A (en) * | 2021-02-01 | 2021-06-11 | 河北利翔航空科技有限公司 | Vertical take-off and landing fixed wing aircraft using coanda effect for increasing lift |
| CN112937851B (en) * | 2021-02-01 | 2022-10-18 | 河北利翔航空科技有限公司 | Vertical take-off and landing fixed-wing aircraft using coanda effect to increase lift |
| CN112947528B (en) * | 2021-03-24 | 2022-04-08 | 南京航空航天大学 | Tilt-rotor aircraft flight control method and system oriented to high-low undulating terrain environment |
| CN112947528A (en) * | 2021-03-24 | 2021-06-11 | 南京航空航天大学 | Tilt-rotor aircraft flight control method and system oriented to high-low undulating terrain environment |
| CN113460300A (en) * | 2021-08-16 | 2021-10-01 | 江西洪都航空工业股份有限公司 | Carrying equipment suitable for single flight |
| CN113697097A (en) * | 2021-09-01 | 2021-11-26 | 中国航空研究院 | Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary wings |
| CN113697097B (en) * | 2021-09-01 | 2024-01-02 | 中国航空研究院 | Fixed wing aircraft overall aerodynamic layout with tiltable outer wings and rotor wings |
| CN115157944A (en) * | 2022-06-30 | 2022-10-11 | 中国航天空气动力技术研究院 | Solar energy range-extending electric aerocar |
| CN115123535A (en) * | 2022-08-11 | 2022-09-30 | 北京北航天宇长鹰无人机科技有限公司 | Tilt wing unmanned aerial vehicle |
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