CN108163213A - A kind of multi-stage booster Bladeless formula air propulsion method and propulsion device - Google Patents
A kind of multi-stage booster Bladeless formula air propulsion method and propulsion device Download PDFInfo
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- CN108163213A CN108163213A CN201810120186.2A CN201810120186A CN108163213A CN 108163213 A CN108163213 A CN 108163213A CN 201810120186 A CN201810120186 A CN 201810120186A CN 108163213 A CN108163213 A CN 108163213A
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- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000007789 sealing Methods 0.000 claims abstract description 20
- 239000012636 effector Substances 0.000 claims description 31
- 235000014653 Carica parviflora Nutrition 0.000 claims description 18
- 241000243321 Cnidaria Species 0.000 claims description 17
- 238000006243 chemical reaction Methods 0.000 claims description 13
- 230000007246 mechanism Effects 0.000 claims description 10
- 238000001914 filtration Methods 0.000 claims description 5
- 230000030279 gene silencing Effects 0.000 claims description 5
- 238000004458 analytical method Methods 0.000 claims description 3
- 230000008569 process Effects 0.000 claims description 3
- 244000132059 Carica parviflora Species 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 6
- 239000003570 air Substances 0.000 description 193
- 230000006872 improvement Effects 0.000 description 5
- 230000001133 acceleration Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 230000001276 controlling effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000001141 propulsive effect Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000013019 agitation Methods 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000010358 mechanical oscillation Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60V—AIR-CUSHION VEHICLES
- B60V1/00—Air-cushion
- B60V1/14—Propulsion; Control thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/36—Arrangement of jet reaction apparatus for propulsion or directional control
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a kind of multi-stage booster Bladeless formula air propulsion methods and propulsion device, propulsion method to include：Several sections of air ducts are connected and form closed air duct,Each section different air pressure pumps is set step by step in closed air duct,And it is capable of the propulsion device of the outside output gas of uniform vertical in the setting of sealing air flue end,Introduce a gas into closed air duct,Gas passes through the pressurization step by step of several air pressure pump in sealing air flue,So that gas pressure increases step by step,Gas after supercharged forms high-speed flow,High-speed flow is exported outward by the propulsion device uniform vertical of sealing air flue end,And the air-flow on propulsion device exhaust outlet periphery is driven to form powerful back pressure,It is of the invention compared with existing propeller,Push wind-force big,Mechanical structure Fatigue Vibration is small,The air-flow of generation is uniform,And add sensor,Various complex situations can be coped with to make adjustment,Stablize controlled,In addition design need not be cylindrical again,And original paper is pushed to disperse,Easy space layout.
Description
Technical field
The present invention relates to a kind of propulsion device, in particular to a kind of multi-stage booster Bladeless formula air propulsion method and propulsions
Device.
Background technology
Propeller is the device that any type of energy is converted into mechanical energy, is produced by rotating vane or jet (water)
Raw thrust, it can be used for driving the vehicles to advance or the power resources as other devices such as generator；Existing market
Upper various aircraft, unmanned plane or hovercraft etc. are substantially as the fan blade type of thrust power in a manner of fan blade agitation air
Propeller, blade high speed rotation, which is easily swept, when fan blade type propeller operates hinders periphery, and be vulnerable to foreign object strike fan blade and generate thing
Therefore safety is low, effect is promoted to be influenced by fan blade quality big, the aerodynamic energy pushed divides in Sine distribution rather than uniformly
Cloth, stability are poor；Existing fan blade type propeller often due to rotary shaft there are certain mechanical eccentric away from, generation largely make an uproar
Sound, and with mechanical oscillation fatigue damage；Fan blade type propeller is due to the limitation of fan blade length and blade shaft powering device size
So that its space hold is big, shape is because blade rotation must be cylinder, and structural compactness is poor, and most fan blade type propellers are past
Front and rear single-stage air is pushed to accelerate toward due to only existing fan blade, once there is fan blade rotate too fast or excessively slow situation, it can be right
Propeller overall performance and safety cause extreme influence.Therefore, design it is a kind of it is safe and stable, noise is small, motive force is big pushes away
It is various equivalent modifications urgent problem into device.
Invention content
In order to solve the above technical problems, it is pressurized and matches corresponding the purpose of the present invention is to provide a kind of use multi-level gas
Hierarchical detection, the method for the actuator structure for controlling and using Bladeless instead meet Powered Propulsion in safety, stability etc.
The scheme of the demand of aspect：
A kind of multi-stage booster Bladeless formula air propulsion method, including following process：Several sections of air ducts are connected and formed close
Close air duct, different air pressure pumps be set step by step each section of closed air duct, and the setting of sealing air flue end can uniform vertical to
The propulsion device of outer output gas；
Closed air duct is introduced a gas into, gas passes through the pressurization step by step of several air pressure pump in sealing air flue so that gas pressure
Power increases step by step, and gas after supercharged forms high-speed flow, and high-speed flow is uniformly hung down by the propulsion device of sealing air flue end
Straight output, and the air-flow on propulsion device exhaust outlet periphery has been driven to form powerful back pressure outward.
As an improvement, each section of the sealing air flue sets sensor respectively, lead between the sealing air flue and propulsion device
The connection of variable ratio frequency changer air pressure pump is crossed, the propulsion device air outlet is equipped with servo-steering mechanism, the sensor, variable ratio frequency changer pneumatics
The controlled chip controls processed of pump, air pressure pump, servo-steering mechanism are to realize the adjusting of itself.
The present invention also provides a kind of propulsion devices based on multi-stage booster Bladeless formula air propulsion method, are set including interior
Have main air duct, secondary air duct fuselage, described main air duct one end connect by secondary air duct with end effector, and other end both sides are symmetrical
Equipped with the identical inlet air air duct group of structure, the air outlet of inlet air air duct group is connected with main air duct；
The end effector includes the end effector one, the end effector two that are symmetrically set in fuselage both sides, the end
It holds actuator one identical with two structure of end effector but adjustable power levels, the end effector one is included outside actuator
Shell, lattice coral air duct, the lattice coral air duct genesis analysis between both ends on the inside of actuator shell, cut open by the transverse direction in the lattice coral air duct
Face is with a narrow upper and lower width streamlined, makes the air gap approximation between the lattice coral air duct trapezoidal, the lattice coral air duct, which is arranged in parallel, to be made
The outlet air surface of the air-gap ends air outlet is arranged in parallel；
According to mass conservation law, section becomes smaller, and speed air flow is accelerated so that end effector outlet air surface surrounding shape
Into uniform pusher high-speed flow, these air-flows will drive between grid air duct gas and the sky on end effector periphery in air gap
Gas quickly flows backward, since reaction force principle peripheral gas can give end effector larger propulsive force.
Inlet air air duct group includes several inlet air wind channel tubes, and small silent pneumatics is respectively equipped on the inlet air wind channel tube
Pump, the air inlet of the inlet air wind channel tube are connect with filtering silencing means；
Described main air duct one end is connected by main air compressor machine with secondary air duct, and the other end is connected with inlet air air duct group, the master
Air duct is additionally provided with sensor one close to one end of inlet air air duct group；
The pair air duct is equipped with adjustable frequency conversion type air compressor machine and sensor two, the pair air duct end and end effector
Junction be equipped with gas pressure sensor three, the main air compressor machine, adjustable frequency conversion type air compressor machine, small silent air pressure pump, pass
Sensor one, sensor two, sensor three connect with control system and are controlled by control system；
The main air duct is with secondary air duct, main air duct and inlet air air duct group, secondary air duct and the junction of end propeller
It is tightly connected.
As an improvement, the pair air duct includes the secondary air duct one with main air duct vertical connection, one both ends of the pair air duct lead to
It crosses adjustable frequency conversion type air compressor machine to be divided into several secondary air ducts two and connect with end effector, the sensor two is set on secondary air duct one
On.
As an improvement, it is additionally provided with servo steering mechanism on the pair air duct one.
As an improvement, the gap between the inlet air wind channel tube is gradually increased by one end close to main air duct to the other end.
As an improvement, the control chip of the control system includes microcontroller or PLC.
After more than structure, the invention has the advantages that：
After present invention energy supply operating, grid air duct narrow end air outlet can be uniform and stable output high speed gas parallel backward
Stream, and the high-speed flow of grid wind passage mouth output can give full play between grid and device ambient air forms interflow, institute's shape
Into interflow will give device with more powerful propulsive force；Device is concentrated controlled by control unit in itself, according to installation
Sensor signal can carry out self-test and system monitoring, and due to using freq uency conversion supercharging equipment and automatically controlled steering servo etc. in real time
Execution unit, device can realize a kind of tune of self-stability according to the variation of the variation of external environment or itself functional requirement
Section, for example cope with unexpected high wind convection current or need this operating mode of emergency stop racing；Device parts itself are smaller and disperse,
And propulsion device appearance and size and profile can carry out integrated planning according to the product general shape that the device is installed, convenient for total
Body designs, and variability is strong；The scattered and vibration frequency of supercharging equipment distribution of device is small and inconsistent, is not likely to produce mechanical fatigue damage
Wound, and noise is reduced, improve safety and comfort.
It is of the invention compared with existing propeller, security risk can be generated by foreign object strike to avoid fan blade type propeller
The shortcomings that, and noise of the present invention is small, and propulsion wind-force is big, and mechanical structure Fatigue Vibration is small, and the air-flow of generation is uniform, and air-flow gas
Pressure adds in sensor-based system, can cope with various complex situations and make adjustment, and stablizes controlled, and turbulence ability is strong, in addition designs not
Must be cylindrical again, design breaks original design limitations, and original paper is promoted to disperse, easy space layout.
Description of the drawings
Fig. 1 is a kind of multi-stage booster Bladeless formula air propulsion method of the present invention and the structure diagram of propulsion device.
Fig. 2 is the section signal of lattice coral in a kind of multi-stage booster Bladeless formula air propulsion method of the present invention and propulsion device
Figure.
Fig. 3 is the gas flow in a kind of multi-stage booster Bladeless formula air propulsion method of the present invention and propulsion device lattice coral
Schematic diagram.
Fig. 4 is the control system topology of a kind of multi-stage booster Bladeless formula air propulsion method of the present invention and propulsion device
Figure.
As shown in the figure：1st, fuselage, 2, main air duct, 3, secondary air duct, 301, secondary air duct one, 302, secondary air duct two, 4, end holds
Row device, 401, end effector one, 401a, actuator shell, 401b, lattice coral air duct, 401c, air gap, 402, end effector
Two, 5, inlet air air duct group, 501, inlet air wind channel tube, 502, small silent air pressure pump, 503, filtering silencing means, 6, main pneumatics
Machine, 7, sensor one, 8, adjustable frequency conversion type air compressor machine, 9, sensor two, 10, sensor three.
Specific embodiment
With reference to attached drawing 1-4, a kind of multi-stage booster Bladeless formula air propulsion method, including following process：By several sections of air ducts
It connects and forms closed air duct, each section different air pressure pumps is set step by step, and energy is set in sealing air flue end in closed air duct
The propulsion device of the outside output gas of enough uniform verticals；
Closed air duct is introduced a gas into, gas passes through the pressurization step by step of several air pressure pump in sealing air flue so that gas pressure
Power increases step by step, and gas after supercharged forms high-speed flow, and high-speed flow is uniformly hung down by the propulsion device of sealing air flue end
Straight output, and the air-flow on propulsion device exhaust outlet periphery has been driven to form powerful back pressure outward.
As the present embodiment preferred embodiment, each section of the sealing air flue sets sensor, the sealing respectively
It is connected between air duct and propulsion device by variable ratio frequency changer air pressure pump, the propulsion device air outlet is equipped with servo-steering mechanism, institute
The controlled chip controls processed of sensor, variable ratio frequency changer air pressure pump, air pressure pump, servo-steering mechanism are stated to realize the adjusting of itself.
The present invention also provides a kind of propulsion devices based on multi-stage booster Bladeless formula air propulsion method, are set including interior
Have main air duct 2, secondary air duct 3 fuselage 1, described 2 one end of main air duct connect by secondary air duct 3 with end effector 4, the other end two
Side is arranged with the identical inlet air air duct group 5 of structure, and the air outlet of inlet air air duct group 5 is connected with main air duct 2；
The end effector 4 includes the end effector 1, the end effector two that are symmetrically set in 1 both sides of fuselage
402, the end effector 1 is identical with 2 402 structure of end effector but adjustable power levels, the end effector
One 401 include actuator shell 401a, lattice coral air duct 401b, and the lattice coral air duct 401b genesis analysis is in actuator shell 401a
Between the both ends of inside, the horizontal section of the lattice coral air duct 401b is with a narrow upper and lower width streamlined, makes the lattice coral air duct 401b
Between air gap 401c approximations it is trapezoidal, the outlet air for making the air gap 401c ends air outlet is arranged in parallel in the lattice coral air duct 401b
Face is arranged in parallel；
Inlet air air duct group 5 includes several inlet air wind channel tubes 501, is respectively equipped on the inlet air wind channel tube 501 small-sized
Mute air pressure pump 502, the air inlet of the inlet air wind channel tube 501 are connect with filtering silencing means 503；
Described 2 one end of main air duct is connected by main air compressor machine 6 with secondary air duct 3, and the other end is connected with inlet air air duct group 5, institute
It states main air duct 2 and is additionally provided with sensor 1 close to one end of inlet air air duct group 5；
The pair air duct 3 is equipped with adjustable frequency conversion type air compressor machine 8 and sensor 29, and 3 end of the pair air duct is held with end
The junction of row device 4 is equipped with gas pressure sensor 3 10, the main air compressor machine 6, adjustable frequency conversion type air compressor machine 8, small silent
Air pressure pump 502, sensor 1, sensor 29, sensor 3 10 connect with control system and are controlled by control system；
The main air duct 2 and secondary air duct 3, main air duct 2 and inlet air air duct group 5, secondary air duct 3 and the connection of end propeller 4
Place is to be tightly connected.
As the present embodiment preferred embodiment, the pair air duct 3 includes the secondary air duct with main air duct vertical connection
One 301, pair one 301 both ends of air duct are divided for several secondary air ducts 2 302 by adjustable frequency conversion type air compressor machine 8 and are performed with end
Device 4 connects, and the sensor 29 is set on secondary air duct 1.
As the present embodiment preferred embodiment, servo steering mechanism is additionally provided on the pair air duct 1.
As the present embodiment preferred embodiment, the gap between the inlet air wind channel tube 501 is by close to main air duct 2
One end gradually increase to the other end.
As the present embodiment preferred embodiment, the control chip of the control system includes microcontroller or PLC.
The present invention is segmented installation small silent sky using more 5 structures of inlet air air duct group in outer end, and in inlet air wind channel tube 501
Press pump 502 and filtering silencing apparatus 503, after introducing a gas into main air duct 3, then are divided by main air compressor machine 6 and adjustable frequency conversion air compressor 8
It is other to realize that two level increases acceleration and three-level and increases acceleration to gas, gas pressure is made to increase step by step, the gas after acceleration is in end
Controllable high-speed flow is formed at the grid air duct 401b of actuator 4, peripheral gas flow fluid is driven to form thrust, and pass through biography
Sensing system and each section of control system unit regulating air duct pressure and end wind-force can be realized adaptively according to different operating modes
Adjusting acts.
The lattice air duct grid 401b by the arrangement of certain numerical value spacing, the end of grid air duct 401b are equipped in end effector 4
The outlet air surface of air outlet is in parallel distribution, and the section of grid air duct 401b is wide at the top and narrow at the bottom streamlined, is determined according to the conservation of mass
Rule, section become smaller, and gas flow rates are accelerated so that and 4 end surrounding of end effector forms uniform pusher high-speed flow, then
By the way that gas and the gas on device periphery quickly flow backward in air gap 401c between these air-flows drive grid air duct 401b, formed
Powerful propulsion capability.
Apparatus of the present invention material therefor is the material of lightweight high rigidity, main air duct 2 and secondary air duct 3 meet certain pressure-bearing and
Load bearing demand；Main air duct 2 is protected with secondary air duct 3, main air duct 2 and inlet air air duct group 5, secondary air duct 3 and the interface of end effector 4
Demonstrate,prove good sealing technology, main air duct 2, secondary air duct 3 leave for everywhere sensing element and executive component interface should also be as performing it is close
Envelope technique；The control chip of control system of the present invention is not limited to, using PLC and microcontroller, to use high performance embedded
Chip unit, the database algorithms for introducing higher precision complete integrally controlling for task or directly by networked remote control and cloud
Calculation is realized；The database algorithms of control system of the present invention can be obtained according to a series of performance test of apparatus of the present invention
It arrives, such as installs apparatus of the present invention into an aircraft, increase the sensor of wind direction in aircraft exterior, test in difference
Under conditions of ambient windstream, when aircraft holding holds position, the change of boost horsepower at left and right sides of propulsion device of the present invention is recorded
The angle change value of change value and servo steering mechanism, in addition we, which can also record and use, copes with emergency stop racing even more pole
The emergent variation that propulsion device needs are made during the operating mode at end；The shape of apparatus of the present invention can be done accordingly according to specific actual conditions
Adjustment.
The present invention and embodiments thereof are described above, this description is no restricted, attached shown in figure
Only one of embodiments of the present invention, practical structure are not limited thereto.All in all if the ordinary skill of this field
Personnel are enlightened by it, without departing from the spirit of the invention, are not inventively designed and the technical solution phase
As frame mode and embodiment, be within the scope of protection of the invention.
Claims (7)
1. a kind of multi-stage booster Bladeless formula air propulsion method, which is characterized in that including following process：Several sections of air ducts are connected
And closed air duct is formed, different air pressure pumps is set step by step, and setting can be equal in sealing air flue end each section in closed air duct
The propulsion device of even vertical output gas outward；
Introduce a gas into closed air duct, gas by several air pressure pump in sealing air flue pressurization step by step so that gas pressure by
Grade increase, gas after supercharged form high-speed flow, high-speed flow by the propulsion device uniform vertical of sealing air flue end to
Outer output, and the air-flow on propulsion device exhaust outlet periphery has been driven to form powerful back pressure.
2. a kind of multi-stage booster Bladeless formula air propulsion method according to claim 1, it is characterised in that：The sealing
Each section of air duct sets sensor respectively, is connected between the sealing air flue and propulsion device by variable ratio frequency changer air pressure pump, described to push away
Into device air outlet be equipped with servo-steering mechanism, the sensor, variable ratio frequency changer air pressure pump, air pressure pump, servo-steering mechanism by
Chip controls is controlled to realize the adjusting of itself.
3. a kind of propulsion device based on multi-stage booster Bladeless formula air propulsion method, it is characterised in that：Master is equipped with including interior
Air duct, the fuselage in secondary air duct, described main air duct one end are connect by secondary air duct with end effector, and other end both sides are arranged with
The identical inlet air air duct group of structure, the air outlet of inlet air air duct group are connected with main air duct；
The end effector includes the end effector one, the end effector two that are symmetrically set in fuselage both sides, and the end is held
Row device one is identical with two structure of end effector but adjustable power levels, the end effector one include actuator shell, lattice
Coral air duct, between both ends on the inside of actuator shell, the horizontal section in the lattice coral air duct is in the lattice coral air duct genesis analysis
Wide at the top and narrow at the bottom is streamlined, makes the air gap approximation between the lattice coral air duct trapezoidal, the lattice coral air duct be arranged in parallel make it is described
The outlet air surface of air-gap ends air outlet is arranged in parallel；
Inlet air air duct group includes several inlet air wind channel tubes, and small silent air pressure pump is respectively equipped on the inlet air wind channel tube,
The air inlet of the inlet air wind channel tube is connect with filtering silencing means；
Described main air duct one end is connected by main air compressor machine with secondary air duct, and the other end is connected with inlet air air duct group, the main air duct
Sensor one is additionally provided with close to one end of inlet air air duct group；
The pair air duct is equipped with the company of adjustable frequency conversion type air compressor machine and sensor two, the pair air duct end and end effector
It meets place and is equipped with gas pressure sensor three, the main air compressor machine, adjustable frequency conversion type air compressor machine, small silent air pressure pump, sensor
First, sensor two, sensor three connect with control system and are controlled by control system；
The junction of the main air duct and secondary air duct, main air duct and inlet air air duct group, secondary air duct and end propeller is sealing
Connection.
4. a kind of propulsion device based on multi-stage booster Bladeless formula air propulsion method according to claim 3, special
Sign is：The pair air duct includes the secondary air duct one with main air duct vertical connection, and one both ends of the pair air duct pass through adjustable frequency conversion
Formula air compressor machine is divided into several secondary air ducts two and is connect with end effector, and the sensor two is set on secondary air duct one.
5. a kind of propulsion device based on multi-stage booster Bladeless formula air propulsion method according to claim 4, special
Sign is：Servo steering mechanism is additionally provided on the pair air duct one.
6. a kind of propulsion device based on multi-stage booster Bladeless formula air propulsion method according to claim 3, special
Sign is：Gap between the inlet air wind channel tube is gradually increased by one end close to main air duct to the other end.
7. a kind of propulsion device based on multi-stage booster Bladeless formula air propulsion method according to claim 3, special
Sign is：The control chip of the control system includes microcontroller or PLC.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810120186.2A CN108163213B (en) | 2018-02-07 | 2018-02-07 | Multistage supercharging fan-blade-free air propulsion method and propulsion device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810120186.2A CN108163213B (en) | 2018-02-07 | 2018-02-07 | Multistage supercharging fan-blade-free air propulsion method and propulsion device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108163213A true CN108163213A (en) | 2018-06-15 |
| CN108163213B CN108163213B (en) | 2024-02-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810120186.2A Active CN108163213B (en) | 2018-02-07 | 2018-02-07 | Multistage supercharging fan-blade-free air propulsion method and propulsion device |
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| CN (1) | CN108163213B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111319774A (en) * | 2018-12-13 | 2020-06-23 | 研能科技股份有限公司 | Power driver of unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20070018034A1 (en) * | 2005-07-12 | 2007-01-25 | Dickau John E | Thrust vectoring |
| CN103612751A (en) * | 2013-11-18 | 2014-03-05 | 岑溪市东正新泵业贸易有限公司 | Air amplification type aircraft propulsion device |
| CN204916161U (en) * | 2015-08-19 | 2015-12-30 | 杨海涛 | No rotorcraft multiaxis aircraft |
| CN106958464A (en) * | 2017-05-09 | 2017-07-18 | 黄革远 | Multistage turbine propeller |
| CN207826571U (en) * | 2018-02-07 | 2018-09-07 | 屈楠 | A kind of multi-stage booster Bladeless formula air propulsion device |
-
2018
- 2018-02-07 CN CN201810120186.2A patent/CN108163213B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070018034A1 (en) * | 2005-07-12 | 2007-01-25 | Dickau John E | Thrust vectoring |
| CN103612751A (en) * | 2013-11-18 | 2014-03-05 | 岑溪市东正新泵业贸易有限公司 | Air amplification type aircraft propulsion device |
| CN204916161U (en) * | 2015-08-19 | 2015-12-30 | 杨海涛 | No rotorcraft multiaxis aircraft |
| CN106958464A (en) * | 2017-05-09 | 2017-07-18 | 黄革远 | Multistage turbine propeller |
| CN207826571U (en) * | 2018-02-07 | 2018-09-07 | 屈楠 | A kind of multi-stage booster Bladeless formula air propulsion device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111319774A (en) * | 2018-12-13 | 2020-06-23 | 研能科技股份有限公司 | Power driver of unmanned aerial vehicle |
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| Publication number | Publication date |
|---|---|
| CN108163213B (en) | 2024-02-06 |
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