CN107128489A - A kind of VTOL fixed wing aircraft of oil electricity mixing - Google Patents
A kind of VTOL fixed wing aircraft of oil electricity mixing Download PDFInfo
- Publication number
- CN107128489A CN107128489A CN201710324498.0A CN201710324498A CN107128489A CN 107128489 A CN107128489 A CN 107128489A CN 201710324498 A CN201710324498 A CN 201710324498A CN 107128489 A CN107128489 A CN 107128489A
- Authority
- CN
- China
- Prior art keywords
- rotor
- wing
- rotor unit
- wing aircraft
- unit
- 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
Links
- 230000005611 electricity Effects 0.000 title claims abstract description 22
- 230000000712 assembly Effects 0.000 claims abstract description 51
- 238000000429 assembly Methods 0.000 claims abstract description 51
- 230000015572 biosynthetic process Effects 0.000 claims abstract description 10
- 238000005516 engineering process Methods 0.000 claims abstract description 7
- 239000000463 material Substances 0.000 claims description 12
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 240000007182 Ochroma pyramidale Species 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000002131 composite material Substances 0.000 claims description 3
- 150000001875 compounds Chemical class 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 239000003365 glass fiber Substances 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 230000005669 field effect Effects 0.000 claims description 2
- 241000196324 Embryophyta Species 0.000 claims 1
- 238000005183 dynamical system Methods 0.000 abstract description 2
- 238000005457 optimization Methods 0.000 abstract 1
- 239000000446 fuel Substances 0.000 description 16
- 239000003921 oil Substances 0.000 description 7
- 230000004044 response Effects 0.000 description 6
- 230000008859 change Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- 230000008450 motivation Effects 0.000 description 3
- 230000006872 improvement Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 241000566150 Pandion haliaetus Species 0.000 description 1
- 230000002929 anti-fatigue Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000010297 mechanical methods and process Methods 0.000 description 1
- 238000004886 process control Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
-
- B64D27/026—
Abstract
The invention discloses a kind of VTOL fixed wing aircraft of oil electricity mixing, including fuselage, it is symmetricly set on the wing of the fuselage both sides and is arranged on the empennage of the fuselage tail end, also include at least two rotor units being arranged on the wing, at least two described rotor units include at least one first rotor unit and at least one second rotor unit, the first rotor unit is included on symmetrically arranged a pair of first rotor assemblies of the fuselage axis, the second rotor unit is included on symmetrically arranged a pair of second rotor assemblies of the fuselage axis, first rotor assemblies and second rotor assemblies are separately positioned on the wing end, first rotor assemblies and second rotor assemblies are using asymmetrical control technology set-up mode one three fulcrum of formation or the inertia geometrical plane of four fulcrums.The present invention at least has the advantage that：Structure optimization, dynamical system utilization rate is high, stationarity is good, endurance is strong.
Description
Technical field
The present invention relates to vehicle technology field, more particularly to a kind of VTOL fixed wing aircraft of oil electricity mixing.
Background technology
Current tilt rotor aircraft has many types, wherein main using fuel engines or motor as driving power
Based on." osprey " in the current U.S. uses complete mechanical method, and all rotors are all used as driving using fuel engines.Due to
Fuel engines response speed is too slow, aircraft balanced can not be met required for the quick lift regulation of rotor, therefore employ change
Away from technology, by the quick displacement of the angle for adjusting rotor blade to realize the quick regulation of lift, but this kind of technology causes machine
Tool complicatedization, cost are high, difficult in maintenance, reliability is low.For electric tilting rotor wing aircraft developed in recent years, institute
Some rotors are used as driving using motor.Powered by battery, using the characteristic of motor fast response time, by changing electricity
The lift of each rotor of motivation rotational speed regulation, is adjusted with the quick lift for meeting the rotor needed for aircraft balanced.This system knot
Structure is simple, safe and reliable, but is due to the limitation of current battery energy storage, and the time of this flight and flight is all very
Short, practical value is very low.
In the market have also been devised a kind of combine many rotors and fixed wing aircraft, by fuel electric generator and motor
The aircraft combined.This kind of aircraft is in VTOL, and all rotors all rotate produces lift vertically upward upwards, profit
Kept balancing with motor quick regulation characteristic, fuel engines rotor produces lift, and rotor system is simple in construction.But this kind of aircraft
It is not thoroughly tilt rotor aircraft, it is when VTOL or hovering, and all rotors all work, but flies aircraft is flat
When only some rotor wing rotation direction provide power for aircraft.Obviously this kind of aircraft is redundant system, power utilization
Rate is low, during horizontal flight, and part rotor does not provide the power of flight, while adding flight resistance, increasing aircraft
Load.
The content of the invention
In order to solve the above technical problems, flying present invention aims at a kind of VTOL fixed-wing of oil electricity mixing is provided
Machine, to solve the problem of complicated, dynamical system utilization rate of the prior art is low, stationarity is poor, endurance is low.
A kind of VTOL fixed wing aircraft of oil electricity mixing of the present invention, including fuselage, it is symmetricly set on the fuselage
The wing of both sides and the empennage for being arranged on the fuselage tail end, in addition at least two rotor lists being arranged on the wing
Member, at least two described rotor units include at least one first rotor unit and at least one second rotor unit, described
First rotor unit is included on symmetrically arranged a pair of first rotor assemblies of the fuselage axis, the second rotor unit bag
Include on symmetrically arranged a pair of second rotor assemblies of the fuselage axis, it is adjustable that first rotor assemblies include rotary speed
The motor of section and the first rotor for being driven by it rotation, second rotor assemblies include starting using fixed rotary speed
Machine and the second rotor for being driven by it rotation, first rotor assemblies and second rotor assemblies are separately positioned on the machine
Tip extension, first rotor assemblies and second rotor assemblies are using asymmetrical control technology set-up mode formation one three
The inertia geometrical plane of fulcrum or four fulcrums.
Further, the thrust of each motor is adjusted respectively, to form multiple variable thrust fulcrums, each described
Engine is using fixed thrust, with the equivalent quantitative thrust fulcrum of formation single-point.
Further, the fixed wing aircraft also includes the power for being used to monitor the motor and engine operating
Control circuit, the power control circuit includes microprocessor, each motor for being coupled with the microprocessor and described
The power unit of engine, to set up the logical relation mathematical modeling between each motor and the rotating speed of the engine.
Further, first rotor assemblies and the second rotor assemblies in the plane parallel to the fuselage axis
Rotate, its rotational angle is 0-90 °.
Further, the fixed wing aircraft includes being provided with one on two rotor units, one of them described wing
The second rotor unit is provided with the first rotor unit, another described wing.
Further, the fixed wing aircraft includes being provided with one on three rotor units, one of them described wing
Above and below the first rotor unit and the second rotor unit, the first rotor unit and the second rotor unit
It is arranged in parallel, the first rotor unit or the second rotor unit is provided with another described wing.
Further, the fixed wing aircraft includes four rotor units, is respectively respectively arranged with one described in two on wing
Above and below the first rotor unit and the second rotor unit, the first rotor unit and the second rotor unit
It is arranged in parallel.
Further, the tune for detecting the motor speed is provided between the motor and the microprocessor
Fast device, the speed regulator includes FET.
Further, the ratio between the diameter of first rotor and described wing length are 0.1-0.6, second rotor with
The ratio between described wing length is 0.1-0.6.
Further, the material of the fuselage and wing is glass fiber compound material, carbon fibre composite, metal plate material
One or more combinations in material, balsa wood material.
By such scheme, the present invention at least has advantages below：
1st, by being provided with the first rotor assemblies and the second rotor assemblies, including motor and fuel engines, fuel oil hair
Motivation is using fixed rotating speed, in VTOL, mainly the pushing away with rotor generation by high-power fuel engines and its institute
Power provides lift, balance control is realized by adjusting motor speed Fast transforms thrust, in flat winged state, mainly by big
Power fuel engines and its provide aircraft speed forward with the thrust that rotor is produced, it is quick by adjusting motor speed
Conversion thrust realizes the overall gesture stability of aircraft；
2nd, asymmetrical set-up mode is used by the first rotor and second rotor, forms three fulcrums or four
The inertia geometrical plane of point, it is ensured that the stability contorting of aircraft；
3rd, by way of oily electricity mixing, fuel engines and motor is organically used cooperatively, electricity is on the one hand utilized
Motivation response range is big, overcomes landing process to the flat adjustment for flying over journey thrust wide variation, on the other hand utilizes
The characteristics of motor response range is greatly and power dynamic range is big realizes the stability contorting of aircraft, strong using fuel engines power
Strength, long-endurance feature realizes that aircraft length is continued a journey.
Described above is only the general introduction of technical solution of the present invention, in order to better understand the technological means of the present invention,
And can be practiced according to the content of specification, below with presently preferred embodiments of the present invention and coordinate accompanying drawing describe in detail as after.
Brief description of the drawings
Fig. 1 is the structural representation of the present invention；
Fig. 2 is Fig. 1 of the present invention mechanic equivalent schematic diagram；
Fig. 3 is another structural representation of the present invention；
Fig. 4 is Fig. 3 of the present invention mechanic equivalent schematic diagram；
Fig. 5 is another structural representation of the present invention.
In the figures above：1st, fuselage；2nd, wing；3rd, empennage；4th, the first rotor assemblies；5th, the second rotor assemblies.
Embodiment
With reference to the accompanying drawings and examples, the embodiment to the present invention is described in further detail.Implement below
Example is used to illustrate the present invention, but is not limited to the scope of the present invention.
With reference to shown in Fig. 1 to Fig. 5, the invention discloses a kind of VTOL fixed wing aircraft of oil electricity mixing, including machine
Body 1, the wing 2 for being symmetricly set on the both sides of fuselage 1 and the empennage 3 for being arranged on the tail end of fuselage 1.The fuselage 1 and machine
The material of the wing 2 is one or more groups in glass fiber compound material, carbon fibre composite, Metal plate, balsa wood material
Close, can preferably mitigate weight using these materials, the oil consumption and discharge greatly reduced reduces operation cost, and have
Extremely strong antifatigue and resistance to corrosion, increases the service life.
The VTOL fixed wing aircraft of the oil electricity mixing also includes at least two rotors being arranged on the wing 2
Unit, at least two described rotor units include at least one first rotor unit and at least one second rotor unit.Institute
State a pair of first rotor assemblies 4 that the first rotor unit includes setting on the axisymmetrical of fuselage 1, the second rotor list
Member includes a pair of second rotor assemblies 5 set on the axisymmetrical of fuselage 1.First rotor assemblies 4 include rotation
The adjustable motor of speed and the first rotor for being driven by it rotation, the thrust of each motor are adjusted respectively, with shape
Into multiple variable thrust fulcrums.Second rotor assemblies 5 include using the engine for fixing rotary speed and are driven by it turning
The second dynamic rotor, each engine is fuel engines, and it includes fuel oil engine, using fixed thrust, with equivalent shape
Into the quantitative thrust fulcrum of single-point.By way of oily electricity mixing, fuel engines and motor are organically used cooperatively, a side
Face is big using motor response range, overcomes landing process to the flat adjustment for flying over journey thrust wide variation, another
Aspect is started using motor response range is big and the stability contorting of aircraft is realized the characteristics of big power dynamic range using fuel oil
Mechanomotive force is powerful, and long-endurance feature realizes that aircraft length is continued a journey.First rotor assemblies 4 and second rotor assemblies
5 are separately positioned on the end of wing 2, when aircraft vertical takes off, first rotor assemblies 4 and the second rotor assemblies 5
In the rotation with surface parallel to the axis of fuselage 1, taking off vertically to flat fly, the first rotor assemblies 4 and second
The angle that rotor assemblies 5 are turned over is 90 °.The diameter of first rotor is 0.1-0.6 with the length ratio of wing 2, described
Second rotor is 0.1-0.6 with the length ratio of wing 2.By being provided with the first rotor assemblies 4 and the second rotor assemblies 5,
Including motor and fuel engines, fuel engines is mainly electronic by adjusting in flat winged state using fixed rotating speed
Machine rotating speed Fast transforms thrust realizes the overall balance control of aircraft, in VTOL, is mainly produced by fuel engines
High-power thrust stabilized flight.
With reference to shown in Fig. 1, the fixed wing aircraft includes being provided with two rotor units, one of them described wing 2
The second rotor unit is provided with one the first rotor unit, another described wing 2.First rotor
The two variable thrust fulcrums of equivalent formation of the first rotor assemblies 4 of unit, second rotor assemblies 5 of the second rotor unit etc.
Effect forms a quantitative thrust fulcrum.A plane can be determined in geometrically three thrust fulcrums, when a branch of this plane
Point is fixed, can arbitrarily adjust the normal vector of the plane by two other fulcrum to realize the balance control of aircraft.Specifically
Mode is：Two fuel engines of the second rotor unit are using fixed rotary speed, two motor of the first rotor unit
Rotating speed can be needed to adjust according to flight respectively to change thrust size, to adjust the pitching of aircraft, on two axial directions of level
Balance, realizes that balance of the aircraft in take-off process controls, ensures that aircraft steadily takes off or landed.With reference to shown in Fig. 2, Fig. 2 is
Fig. 1 mechanic equivalent schematic diagram.
With reference to shown in Fig. 3, the fixed wing aircraft includes being provided with three rotor units, one of them described wing 2
One the first rotor unit and the second rotor unit, the first rotor assemblies 4 and second of the first rotor unit
Second rotor assemblies 5 of rotor unit are combined, two variable thrust fulcrums of equivalent formation.The first rotor unit and described
Be arranged in parallel (the plane and the second of the second rotor unit that the first rotor of the first rotor unit is turned over above and below second rotor unit
The plane that rotor is turned over is relative to the diameter parallel of fuselage 1), the first rotor list is provided with another described wing 2
Member, the first rotor assemblies 4 two variable thrust fulcrums of formation of the first rotor unit.Because each rotor assemblies are relative to fuselage 1
Axisymmetrical is set, and the straight line of each equivalent formation of rotor unit on two wings 2 is parallel to each other, four variable thrust fulcrum shapes
The inertia geometrical plane of Cheng Yisi fulcrums.Four motor can need to adjust rotating speed respectively to change thrust size according to flight,
For adjusting course, pitching and rolling on three axis of movements of aircraft.With reference to shown in Fig. 4, Fig. 4 shows for Fig. 3 mechanic equivalent
It is intended to.
With reference to shown in Fig. 5, the fixed wing aircraft includes four rotor units, is respectively respectively arranged with wing 2 described in two
One the first rotor unit and the second rotor unit, the first rotor unit and the second rotor unit
Be arrangeding in parallel up and down, (it is flat that the plane and the second rotor of the second rotor unit that the first rotor of the first rotor unit is turned over are turned over
Face is relative to the diameter parallel of fuselage 1).First rotor assemblies 4 of the first rotor unit on two wings 2 and the second rotor unit
Second rotor assemblies 5 are combined respectively, four variable thrust fulcrums of equivalent formation.Because each rotor assemblies are relative to the axle of fuselage 1
Line is symmetrical arranged, and the straight line of each equivalent formation of rotor unit on two wings 2 is parallel to each other, and four variable thrust fulcrums are formed
The inertia geometrical plane of one or four fulcrums.
The fixed wing aircraft also includes the power control circuit for being used to monitor the motor and engine operating,
The power control circuit includes the dynamic of microprocessor, each motor coupled with the microprocessor and the engine
Power unit, to set up the logical relation mathematical modeling between each motor and the rotating speed of the engine.The motor
The speed regulator for detecting the motor speed is provided between the microprocessor, the speed regulator includes field-effect
Pipe.
Described above is only the preferred embodiment of the present invention, is not intended to limit the invention, it is noted that for this skill
For the those of ordinary skill in art field, without departing from the technical principles of the invention, can also make it is some improvement and
Modification, these improvement and modification also should be regarded as protection scope of the present invention.
Claims (10)
1. a kind of VTOL fixed wing aircraft of oil electricity mixing, including fuselage, the wing for being symmetricly set on the fuselage both sides
With the empennage for being arranged on the fuselage tail end, it is characterised in that：Also include at least two rotor lists being arranged on the wing
Member, at least two described rotor units include at least one first rotor unit and at least one second rotor unit, described
First rotor unit is included on symmetrically arranged a pair of first rotor assemblies of the fuselage axis, the second rotor unit bag
Include on symmetrically arranged a pair of second rotor assemblies of the fuselage axis, it is adjustable that first rotor assemblies include rotary speed
The motor of section and the first rotor for being driven by it rotation, second rotor assemblies include starting using fixed rotary speed
Machine and the second rotor for being driven by it rotation, first rotor assemblies and second rotor assemblies are separately positioned on the machine
Tip extension, first rotor assemblies and second rotor assemblies are using asymmetrical control technology set-up mode formation one three
The inertia geometrical plane of fulcrum or four fulcrums.
2. a kind of VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：It is each described
The thrust of motor is adjusted respectively, to form multiple variable thrust fulcrums, and each engine is using fixed thrust, with equivalent
Form the quantitative thrust fulcrum of single-point.
3. a kind of VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：The fixation
Wing aircraft also includes the power control circuit for being used to monitor the motor and engine operating, the power control circuit
Each motor and the power unit of the engine coupled including microprocessor, with the microprocessor, it is each to set up
Logical relation mathematical modeling between the rotating speed of the motor and the engine.
4. a kind of VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：Described first
Rotor assemblies and the second rotor assemblies of institute are in the rotation with surface parallel to the fuselage axis, and its rotational angle is 0-90 °.
5. a kind of VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：The fixation
Wing aircraft includes being provided with the first rotor unit, another institute on two rotor units, one of them described wing
State and the second rotor unit is provided with wing.
6. a kind of VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：The fixation
Wing aircraft includes being provided with described in the first rotor unit and one on three rotor units, one of them described wing
It is be arranged in parallel above and below second rotor unit, the first rotor unit and the second rotor unit, on another described wing
It is provided with the first rotor unit or the second rotor unit.
7. a kind of VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：The fixation
Wing aircraft includes four rotor units, is respectively respectively arranged with described in the first rotor unit and one on wing described in two
It is be arranged in parallel above and below second rotor unit, the first rotor unit and the second rotor unit.
8. a kind of VTOL fixed wing aircraft of oil electricity mixing according to claim 3, it is characterised in that：It is described electronic
The speed regulator for detecting the motor speed is provided between machine and the microprocessor, the speed regulator includes field-effect
Pipe.
9. a kind of VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：Described first
The ratio between the diameter of rotor and the wing length are 0.1-0.6, and the ratio between second rotor and the wing length are 0.1-
0.6。
10. a kind of VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：The machine
The material of body and wing is one kind or many in glass fiber compound material, carbon fibre composite, Metal plate, balsa wood material
Plant combination.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710324498.0A CN107128489A (en) | 2017-05-10 | 2017-05-10 | A kind of VTOL fixed wing aircraft of oil electricity mixing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710324498.0A CN107128489A (en) | 2017-05-10 | 2017-05-10 | A kind of VTOL fixed wing aircraft of oil electricity mixing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107128489A true CN107128489A (en) | 2017-09-05 |
Family
ID=59732714
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710324498.0A Pending CN107128489A (en) | 2017-05-10 | 2017-05-10 | A kind of VTOL fixed wing aircraft of oil electricity mixing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107128489A (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110303795A1 (en) * | 2009-10-09 | 2011-12-15 | Richard David Oliver | Three-wing, six tilt-propulsion unit, vtol aircraft |
| CN102897315A (en) * | 2011-07-29 | 2013-01-30 | 奥格斯塔韦斯兰股份公司 | Convertiplane |
| RU2550909C1 (en) * | 2014-03-26 | 2015-05-20 | Дмитрий Сергеевич Дуров | Multirotor convertible pilotless helicopter |
| DE102014000509A1 (en) * | 2014-01-16 | 2015-07-16 | Emt Ingenieurgesellschaft Dipl.-Ing. Hartmut Euer Mbh | Fixed-wing aircraft |
| CN205034338U (en) * | 2015-09-06 | 2016-02-17 | 湖北航天飞行器研究所 | Tilted four -rotor aircraft |
| CN205239908U (en) * | 2015-12-22 | 2016-05-18 | 江苏数字鹰科技发展有限公司 | Fixed tilt angle rotor craft |
| CN105711827A (en) * | 2016-03-23 | 2016-06-29 | 刘海涛 | Oil and electricity hybrid power multi-rotor aircraft |
| CN105730692A (en) * | 2016-04-19 | 2016-07-06 | 北京航空航天大学 | Tilting quad-rotor long-endurance composite aircraft |
| EP3056425A1 (en) * | 2015-02-13 | 2016-08-17 | Airbus Defence and Space GmbH | Aircraft which can launch vertically |
| WO2017016096A1 (en) * | 2015-07-27 | 2017-02-02 | 江阴市翔诺电子科技有限公司 | Novel vertical take-off and landing aircraft and control method therefor |
| CN106477033A (en) * | 2016-04-13 | 2017-03-08 | 北京天宇新超航空科技有限公司 | High speed hybrid multi-rotor aerocraft |
| CN207000818U (en) * | 2017-05-10 | 2018-02-13 | 优飞科技（苏州）有限公司 | A kind of VTOL fixed wing aircraft of oil electricity mixing |
-
2017
- 2017-05-10 CN CN201710324498.0A patent/CN107128489A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110303795A1 (en) * | 2009-10-09 | 2011-12-15 | Richard David Oliver | Three-wing, six tilt-propulsion unit, vtol aircraft |
| CN102897315A (en) * | 2011-07-29 | 2013-01-30 | 奥格斯塔韦斯兰股份公司 | Convertiplane |
| DE102014000509A1 (en) * | 2014-01-16 | 2015-07-16 | Emt Ingenieurgesellschaft Dipl.-Ing. Hartmut Euer Mbh | Fixed-wing aircraft |
| RU2550909C1 (en) * | 2014-03-26 | 2015-05-20 | Дмитрий Сергеевич Дуров | Multirotor convertible pilotless helicopter |
| EP3056425A1 (en) * | 2015-02-13 | 2016-08-17 | Airbus Defence and Space GmbH | Aircraft which can launch vertically |
| WO2017016096A1 (en) * | 2015-07-27 | 2017-02-02 | 江阴市翔诺电子科技有限公司 | Novel vertical take-off and landing aircraft and control method therefor |
| CN205034338U (en) * | 2015-09-06 | 2016-02-17 | 湖北航天飞行器研究所 | Tilted four -rotor aircraft |
| CN205239908U (en) * | 2015-12-22 | 2016-05-18 | 江苏数字鹰科技发展有限公司 | Fixed tilt angle rotor craft |
| CN105711827A (en) * | 2016-03-23 | 2016-06-29 | 刘海涛 | Oil and electricity hybrid power multi-rotor aircraft |
| CN106477033A (en) * | 2016-04-13 | 2017-03-08 | 北京天宇新超航空科技有限公司 | High speed hybrid multi-rotor aerocraft |
| CN105730692A (en) * | 2016-04-19 | 2016-07-06 | 北京航空航天大学 | Tilting quad-rotor long-endurance composite aircraft |
| CN207000818U (en) * | 2017-05-10 | 2018-02-13 | 优飞科技（苏州）有限公司 | A kind of VTOL fixed wing aircraft of oil electricity mixing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107042884A (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| US20160010627A1 (en) | Auto-gyro rotor flying electric generator (feg) with wing lift augmentation | |
| CN104743107B (en) | Multi-rotor aerocraft | |
| CN105620743A (en) | Tilting mechanism for tilting three-rotor aircraft | |
| CN204660023U (en) | Aircraft | |
| CN104859853A (en) | Six-rotor hybrid aircraft | |
| CN104176247A (en) | Four-rotor unmanned aerial vehicle with engine for directly driving rotor | |
| CN107089328A (en) | Hybrid power tail sitting posture VTOL long endurance unmanned aircraft and its flight control method | |
| CN201712787U (en) | Electric tilt rotor unmanned aircraft | |
| CN205022861U (en) | VTOL fixed wing aircraft | |
| CN103057702B (en) | Jet-propelled type helicopter with rotating wings | |
| CN105966609B (en) | A kind of heavy autogyro hybrid power richochet system with variable-distance teetering rotor head | |
| CN103832583A (en) | Airplane with lift force balance fans and tiltable rotor wings | |
| CN107244415A (en) | The composite power rotor wing unmanned aerial vehicle that a kind of fuselage can vert | |
| CN102417034A (en) | Transverse rigid rotor blade helicopter | |
| CN105270614A (en) | Symmetric eight-axle aircraft | |
| CN204776020U (en) | Unmanned vehicles with many rotors of major -minor structure | |
| CN108238247A (en) | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer | |
| CN104973241A (en) | Unmanned aerial vehicle with main and auxiliary multi-rotor structure | |
| CN207000818U (en) | A kind of VTOL fixed wing aircraft of oil electricity mixing | |
| CN206434864U (en) | A kind of aircraft of VTOL | |
| WO2019212744A1 (en) | Aircraft | |
| CN206552261U (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN208007286U (en) | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer | |
| CN208715474U (en) | A kind of multi-rotor unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20211111 Address after: Room 102, No. 10, Lane 2500, xiupu Road, Pudong New Area, Shanghai 200120 Applicant after: SHANGHAI YOUQIAN INTELLIGENT TECHNOLOGY Co.,Ltd. Address before: 215000 Room 401, building 9, Northwest District, Suzhou nano City, No. 99, Jinjihu Avenue, Suzhou Industrial Park, Jiangsu Province Applicant before: YOUFEI TECHNOLOGY (SUZHOU) CO.,LTD. |
|
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170905 |