CN108163213B - Multistage supercharging fan-blade-free air propulsion method and propulsion device - Google Patents
Multistage supercharging fan-blade-free air propulsion method and propulsion device Download PDFInfo
- Publication number
- CN108163213B CN108163213B CN201810120186.2A CN201810120186A CN108163213B CN 108163213 B CN108163213 B CN 108163213B CN 201810120186 A CN201810120186 A CN 201810120186A CN 108163213 B CN108163213 B CN 108163213B
- Authority
- CN
- China
- Prior art keywords
- air
- air duct
- duct
- auxiliary
- channel
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 21
- 241000167857 Bourreria Species 0.000 claims abstract description 4
- 239000012636 effector Substances 0.000 claims description 40
- 238000001914 filtration Methods 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 5
- 230000030279 gene silencing Effects 0.000 claims description 4
- 230000007246 mechanism Effects 0.000 claims description 4
- 230000033228 biological regulation Effects 0.000 claims description 2
- 230000008859 change Effects 0.000 description 6
- 230000006872 improvement Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000010485 coping Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000006855 networking Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a multistage supercharging fan-blade-free air propulsion method and a propulsion device, wherein the propulsion method comprises the following steps: the invention relates to a sealed air channel, which is characterized in that a plurality of sections of air channels are connected and form a sealed air channel, different air pressure pumps are arranged in each section of the sealed air channel step by step, a propelling device capable of uniformly and vertically outputting air is arranged at the tail end of the sealed air channel, the air is introduced into the sealed air channel, the air is pressurized step by a plurality of air pressure pumps in the sealed air channel, so that the air pressure is increased step by step, the pressurized air forms high-speed air flow, the high-speed air flow is uniformly and vertically output through the propelling device at the tail end of the sealed air channel, and the air flow at the periphery of an exhaust port of the propelling device is driven to form strong back thrust.
Description
Technical Field
The invention relates to a propulsion device, in particular to a multistage supercharging fan-blade-free air propulsion method and a propulsion device.
Background
A propeller is a device that converts any form of energy into mechanical energy, generates thrust by rotating blades or jet (water), and can be used to drive a vehicle forward, or as a source of power for other devices such as an electric generator; the existing aircrafts, unmanned aerial vehicles or air cushion boats and the like in the market are basically fan blade type propellers taking a fan blade stirring air mode as propulsion power, when the fan blade type propellers run, the fan blades rotate at a high speed and are easy to sweep the periphery, foreign objects are easy to strike the fan blades to generate accidents, the safety is low, the propulsion effect is greatly influenced by the quality of the fan blades, the propelled air kinetic energy is distributed in a sine mode instead of in a uniform mode, and the stability is poor; the existing fan blade type propeller often generates a great amount of noise due to a certain mechanical eccentricity of a rotating shaft and has mechanical vibration fatigue damage; the fan blade type propeller occupies a large space due to the limitation of the length of the fan blade and the size of the fan blade shaft energy supply equipment, the appearance is cylindrical due to the fact that the fan blade rotates, the structure is poor in compactness, most fan blade type propellers are often accelerated by single-stage air before and after the fan blade is pushed, and once the fan blade rotates too fast or too slow, the overall performance and the safety of the propeller are greatly influenced. Therefore, designing a safe, stable, low-noise, high-thrust propeller is an urgent problem for those skilled in the relevant arts.
Disclosure of Invention
In order to solve the technical problems, the invention aims to provide a scheme which adopts multistage gas pressurization and matches corresponding staged detection, control and change a method of using a blade-free actuator structure to meet requirements of power propulsion in the aspects of safety, stability and the like:
a multistage supercharging fan-blade-free air propulsion method comprises the following steps: connecting a plurality of sections of air channels to form a closed air channel, arranging different air pressure pumps step by step in each section of the closed air channel, and arranging a pushing device capable of uniformly and vertically outputting gas at the tail end of the closed air channel;
the air is introduced into the closed air duct, and is pressurized step by a plurality of air pressure pumps in the closed air duct, so that the pressure of the air is increased step by step, the pressurized air forms high-speed air flow, the high-speed air flow is uniformly and vertically output outwards through a propelling device at the tail end of the closed air duct, and the air flow around the exhaust port of the propelling device is driven to form strong back thrust.
As an improvement, each section of the sealed air duct is respectively provided with a sensor, the sealed air duct is connected with the propelling device through a variable-frequency air pressure pump, the air outlet of the propelling device is provided with a servo steering device, and the sensors, the variable-frequency air pressure pump, the air pressure pump and the servo steering device are controlled by a control chip to realize self adjustment.
The invention also provides a propelling device based on the multistage supercharging fan-blade-free air propelling method, which comprises a machine body provided with a main air duct and an auxiliary air duct, wherein one end of the main air duct is connected with an end effector through the auxiliary air duct, air inlet air duct groups with the same structure are symmetrically arranged on two sides of the other end of the main air duct, and air outlets of the air inlet air duct groups are communicated with the main air duct;
the end effector comprises a first end effector and a second end effector which are symmetrically arranged on two sides of the machine body, the first end effector has the same structure as the second end effector and respectively adjustable power, the first end effector comprises an effector shell and grid air channels, the grid air channels are longitudinally distributed between two ends of the inner side of the effector shell, the transverse section of each grid air channel is in a streamline shape with a wide upper part and a narrow lower part, so that an air gap between the grid air channels is approximately trapezoidal, and the grid air channels are arranged in parallel so that air outlet surfaces of air outlets at the tail ends of the air gaps are arranged in parallel;
according to the law of conservation of mass, the cross section becomes smaller, the air flow speed is increased, so that uniform backward pushing high-speed air flows are formed around the air outlet face of the end effector, and the air flows can drive air in an air gap between grid air channels and air around the end effector to flow backward and quickly, and the peripheral air can give larger propelling force to the end effector due to the reactive force principle.
The air inlet air duct group comprises a plurality of air inlet air duct pipes, the air inlet air duct pipes are respectively provided with a small mute air pressure pump, and an air inlet of each air inlet air duct pipe is connected with the filtering and silencing device;
one end of the main air channel is communicated with the auxiliary air channel through a main air compressor, the other end of the main air channel is communicated with the air inlet air channel group, and one end, close to the air inlet air channel group, of the main air channel is also provided with a first sensor;
the auxiliary air duct is provided with an adjustable variable-frequency air compressor and a sensor II, a gas pressure sensor III is arranged at the joint of the tail end of the auxiliary air duct and the tail end actuator, and the main air compressor, the adjustable variable-frequency air compressor, the small-sized mute air compressor, the sensor I, the sensor II and the sensor III are connected with a control system and controlled by the control system;
the joints of the main air duct and the auxiliary air duct, the main air duct and the air inlet air duct group and the auxiliary air duct and the tail end propeller are in sealing connection.
As an improvement, the auxiliary air duct comprises an auxiliary air duct I which is vertically communicated with the main air duct, two ends of the auxiliary air duct I are divided into a plurality of auxiliary air ducts II through an adjustable variable-frequency air compressor and are connected with an end effector, and the sensor II is arranged on the auxiliary air duct I.
As an improvement, a servo steering mechanism is further arranged on the first auxiliary air duct.
As an improvement, the gap between the air inlet duct pipes is gradually increased from one end close to the main duct to the other end.
As an improvement, the control chip of the control system comprises a singlechip or a PLC.
After adopting the structure, the invention has the following advantages:
after the air conditioner is powered to operate, the air outlet at the narrow end of the grid air duct can uniformly and stably output high-speed air in a backward parallel manner, and the high-speed air output by the air outlet of the grid air duct can fully mobilize air between grids and around the device to form confluence, so that the formed confluence can give stronger propelling force to the device; the device is controlled by a centralized control unit, can perform self-check and system monitoring in real time according to the installed sensor signals, and can realize self-stability adjustment according to the change of external environment or the change of self-function requirements by adopting a variable-frequency supercharging device, an electric control steering servo and other execution units, such as a working condition of coping with sudden strong wind convection or needing sudden stop and sudden rotation; the parts of the device are smaller and scattered, the overall dimension and the outline of the propulsion device can be integrally planned according to the overall appearance of a product installed by the device, the overall design is convenient, and the variability is strong; the supercharging equipment of the device has scattered distribution, small and inconsistent vibration frequency, is not easy to produce mechanical fatigue damage, reduces noise and improves safety and comfort.
Compared with the existing propeller, the invention can avoid the defect of potential safety hazard caused by the impact of foreign objects on the fan blade type propeller, has the advantages of low noise, large propelling wind power, small fatigue vibration of mechanical structure, uniform generated air flow, stable and controlled air pressure added into the sensing system, capability of adjusting various complex conditions, strong turbulence resistance, no need of cylindrical design, capability of breaking the original design limitation by design, and easy spatial arrangement.
Drawings
FIG. 1 is a schematic diagram of a multistage supercharging blade-free air propulsion method and a propulsion device according to the present invention.
FIG. 2 is a schematic cross-sectional view of a grid in a multi-stage supercharging vaneless air propulsion method and propulsion device of the present invention.
FIG. 3 is a schematic diagram of the flow of air in a multi-stage supercharging vaneless air propulsion method and propulsion device grid according to the present invention.
FIG. 4 is a topology diagram of a control system for a multi-stage supercharging bladeless air propulsion method and propulsion apparatus according to the present invention.
As shown in the figure: 1. fuselage, 2, main wind channel, 3, auxiliary wind channel, 301, auxiliary wind channel one, 302, auxiliary wind channel two, 4, end effector, 401, end effector one, 401a, actuator housing, 401b, grid wind channel, 401c, air gap, 402, end effector two, 5, into wind channel group, 501, into wind channel pipe, 502, small-size silence air pump, 503, filtering silencing device, 6, main air compressor, 7, sensor one, 8, adjustable variable frequency air compressor, 9, sensor two, 10, sensor three.
Detailed Description
1-4, a multistage supercharging fan-blade-free air propulsion method comprises the following steps: connecting a plurality of sections of air channels to form a closed air channel, arranging different air pressure pumps step by step in each section of the closed air channel, and arranging a pushing device capable of uniformly and vertically outputting gas at the tail end of the closed air channel;
the air is introduced into the closed air duct, and is pressurized step by a plurality of air pressure pumps in the closed air duct, so that the pressure of the air is increased step by step, the pressurized air forms high-speed air flow, the high-speed air flow is uniformly and vertically output outwards through a propelling device at the tail end of the closed air duct, and the air flow around the exhaust port of the propelling device is driven to form strong back thrust.
As the preferred implementation scheme of the embodiment, each section of the sealed air duct is respectively provided with a sensor, the sealed air duct is connected with the propelling device through a variable-frequency air pressure pump, the air outlet of the propelling device is provided with a servo steering device, and the sensors, the variable-frequency air pressure pump, the air pressure pump and the servo steering device are controlled by a control chip to realize self adjustment.
The invention also provides a propelling device based on the multistage supercharging fan-blade-free air propelling method, which comprises a machine body 1 internally provided with a main air duct 2 and an auxiliary air duct 3, wherein one end of the main air duct 2 is connected with an end effector 4 through the auxiliary air duct 3, two sides of the other end of the main air duct 2 are symmetrically provided with air inlet air duct groups 5 with the same structure, and air outlets of the air inlet air duct groups 5 are communicated with the main air duct 2;
the end effector 4 comprises a first end effector 401 and a second end effector 402 which are symmetrically arranged on two sides of the machine body 1, the first end effector 401 and the second end effector 402 are identical in structure and adjustable in power respectively, the first end effector 401 comprises an effector shell 401a and a grid air duct 401b, the grid air duct 401b is longitudinally distributed between two ends of the inner side of the effector shell 401a, the transverse section of the grid air duct 401b is in a streamline shape with a wide upper part and a narrow lower part, an air gap 401c between the grid air ducts 401b is approximately trapezoid, and the grid air ducts 401b are arranged in parallel so that air outlet surfaces of air outlets at the tail ends of the air gaps 401c are arranged in parallel;
the air inlet air duct set 5 comprises a plurality of air inlet air duct pipes 501, the air inlet air duct pipes 501 are respectively provided with a small-sized mute air pressure pump 502, and an air inlet of each air inlet air duct pipe 501 is connected with a filtering and silencing device 503;
one end of the main air channel 2 is communicated with the auxiliary air channel 3 through a main air compressor 6, the other end of the main air channel 2 is communicated with the air inlet air channel group 5, and one end, close to the air inlet air channel group 5, of the main air channel 2 is also provided with a sensor I7;
the auxiliary air duct 3 is provided with an adjustable variable-frequency air compressor 8 and a sensor II 9, a gas pressure sensor III 10 is arranged at the joint of the tail end of the auxiliary air duct 3 and the tail end actuator 4, and the main air compressor 6, the adjustable variable-frequency air compressor 8, the small mute air pump 502, the sensor I7, the sensor II 9 and the sensor III 10 are all connected with a control system and controlled by the control system;
the joints of the main air duct 2 and the auxiliary air duct 3, the main air duct 2 and the air inlet air duct group 5, and the auxiliary air duct 3 and the tail end propeller 4 are in sealing connection.
As a preferred embodiment of this example, the secondary air duct 3 includes a secondary air duct first 301 vertically communicated with the main air duct, two ends of the secondary air duct first 301 are divided into a plurality of secondary air ducts second 302 by the variable frequency air compressor 8 and connected with the end effector 4, and the second sensor 9 is disposed on the secondary air duct first 301.
As a preferred implementation of this embodiment, the first auxiliary air duct 301 is further provided with a servo steering mechanism.
As a preferred embodiment of the present embodiment, the gap between the air inlet duct 501 increases gradually from one end near the main duct 2 to the other end.
As a preferred implementation manner of the embodiment, the control chip of the control system comprises a singlechip or a PLC.
The invention adopts an outer end multi-inlet air duct set 5 structure, and after the air inlet duct pipe 501 is sectionally provided with the small-sized mute air pump 502 and the filtering mute device 503, the main air compressor 6 and the adjustable frequency air compressor 8 respectively realize two-stage increasing acceleration and three-stage increasing acceleration on the air, so that the air pressure is increased step by step, the accelerated air forms controllable high-speed air flow at the grid duct 401b of the end effector 4 to drive peripheral air flow to form thrust, and the pressure of each section of the air duct and the wind power of the end are regulated and controlled by the sensing system and the control system unit, so that the self-adaptive regulation action can be realized according to different working conditions.
The grid air duct grids 401b which are arranged according to a certain numerical value interval are arranged in the end effector 4, the air outlet surfaces of the tail end air outlets of the grid air ducts 401b are distributed in parallel, the cross section of the grid air duct 401b is streamline with wide upper part and narrow lower part, the cross section is reduced according to the law of conservation of mass, the gas flow speed is increased, uniform backward pushing high-speed gas flow is formed around the tail end of the end effector 4, and the gas in the air gap 401c between the grid air ducts 401b and the gas around the device are driven to flow backward and fast through the gas flow, so that strong propelling capacity is formed.
The device is made of light high-hardness materials, and the main air duct 2 and the auxiliary air duct 3 meet certain pressure-bearing and load-bearing requirements; the interfaces of the main air duct 2 and the auxiliary air duct 3, the main air duct 2 and the air inlet air duct set 5 and the interfaces of the auxiliary air duct 3 and the end effector 4 ensure good sealing processes, and the interfaces of the sensing element and the actuating element reserved at the whole parts of the main air duct 2 and the auxiliary air duct 3 should also execute the sealing processes; the control chip of the control system is not limited to a PLC and a singlechip, but can also use a high-performance embedded chip unit, and a higher-precision database algorithm is introduced to complete the task of integral control, or the control chip is directly realized by a networking remote control and cloud computing mode; the database algorithm of the control system can be obtained according to a series of performance tests of the device, for example, the device is installed in an aircraft, a sensor for wind power and wind direction is added outside the aircraft, when the aircraft keeps a stable posture under the condition of different environmental airflows, the change value of the supercharging power at the left side and the right side of the propulsion device and the angle change value of a servo steering mechanism are recorded, and in addition, the emergency change which needs to be made by the propulsion device when the device is used for handling sudden stop and sudden rotation even more extreme working conditions can be recorded and used; the appearance of the device can be correspondingly adjusted according to specific practical conditions.
The invention and its embodiments have been described above with no limitation, and the actual construction is not limited to the embodiments of the invention as shown in the drawings. In summary, if one of ordinary skill in the art is informed by this disclosure, a structural manner and an embodiment similar to the technical solution should not be creatively devised without departing from the gist of the present invention.
Claims (4)
1. A propulsion unit based on multistage supercharging fan-blade-free air propulsion method is characterized in that: the air inlet air duct system comprises a machine body provided with a main air duct and an auxiliary air duct, wherein one end of the main air duct is connected with an end effector through the auxiliary air duct, air inlet air duct groups with the same structure are symmetrically arranged on two sides of the other end of the main air duct, and air outlets of the air inlet air duct groups are communicated with the main air duct;
the end effector comprises a first end effector and a second end effector which are symmetrically arranged on two sides of the machine body, the first end effector has the same structure as the second end effector and respectively adjustable power, the first end effector comprises an effector shell and grid air channels, the grid air channels are longitudinally distributed between two ends of the inner side of the effector shell, the transverse section of each grid air channel is in a streamline shape with a wide upper part and a narrow lower part, so that an air gap between the grid air channels is approximately trapezoidal, and the grid air channels are arranged in parallel so that air outlet surfaces of air outlets at the tail ends of the air gaps are arranged in parallel;
the air inlet air duct group comprises a plurality of air inlet air duct pipes, the air inlet air duct pipes are respectively provided with a small mute air pressure pump, and an air inlet of each air inlet air duct pipe is connected with the filtering and silencing device;
one end of the main air channel is communicated with the auxiliary air channel through a main air compressor, the other end of the main air channel is communicated with the air inlet air channel group, and one end, close to the air inlet air channel group, of the main air channel is also provided with a first sensor;
the auxiliary air duct is provided with an adjustable variable-frequency air compressor and a sensor II, a gas pressure sensor III is arranged at the joint of the tail end of the auxiliary air duct and the tail end actuator, and the main air compressor, the adjustable variable-frequency air compressor, the small-sized mute air compressor, the sensor I, the sensor II and the sensor III are connected with a control system and controlled by the control system;
the joints of the main air duct and the auxiliary air duct, the main air duct and the air inlet air duct set and the auxiliary air duct and the tail end propeller are all in sealing connection;
the auxiliary air duct comprises an auxiliary air duct I which is vertically communicated with the main air duct, two ends of the auxiliary air duct I are divided into a plurality of auxiliary air ducts II through an adjustable variable-frequency air compressor and are connected with an end effector, and the sensor II is arranged on the auxiliary air duct I;
the propelling method comprises the following steps: connecting a plurality of sections of air channels to form a closed air channel, arranging different air pressure pumps step by step in each section of the closed air channel, and arranging a pushing device capable of uniformly and vertically outputting gas at the tail end of the closed air channel;
introducing gas into a closed air duct, gradually pressurizing the gas by a plurality of air pressure pumps in the closed air duct, so that the pressure of the gas is gradually increased, the pressurized gas forms high-speed air flow, the high-speed air flow is uniformly and vertically output outwards through a propelling device at the tail end of the closed air duct, and the air flow around an exhaust port of the propelling device is driven to form strong back thrust;
the sealed wind channel each section sets up the sensor respectively, be connected through variable frequency air pressure pump between sealed wind channel and the advancing device, advancing device air outlet is equipped with servo steering device, sensor, variable frequency air pressure pump, servo steering device all control the chip control in order to realize self regulation.
2. The propulsion device based on the multistage supercharging bladeless air propulsion method according to claim 1, wherein the propulsion device is characterized in that: and a servo steering mechanism is further arranged on the first auxiliary air duct.
3. The propulsion device based on the multistage supercharging bladeless air propulsion method according to claim 1, wherein the propulsion device is characterized in that: the gap between the air inlet duct pipes is gradually increased from one end close to the main duct to the other end.
4. The propulsion device based on the multistage supercharging bladeless air propulsion method according to claim 1, wherein the propulsion device is characterized in that: the control chip of the control system comprises a singlechip or a 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 CN108163213A (en) | 2018-06-15 |
| CN108163213B true CN108163213B (en) | 2024-02-06 |
Family
ID=62513563
Family Applications (1)
| 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108163213B (en) |
Families Citing this family (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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070018034A1 (en) * | 2005-07-12 | 2007-01-25 | Dickau John E | Thrust vectoring |
-
2018
- 2018-02-07 CN CN201810120186.2A patent/CN108163213B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108163213A (en) | 2018-06-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11273907B2 (en) | Fluid systems that include a co-flow jet | |
| US11987352B2 (en) | Fluid systems that include a co-flow jet | |
| US10106246B2 (en) | Fluid systems that include a co-flow jet | |
| CN104520542B (en) | Comprise multiple turbines being installed in the fixed radial blades of fan upstream | |
| TWI588352B (en) | Submersible power plant having multiple turbines | |
| JP2011126517A (en) | Morphing ducted fan for vertical take-off and landing vehicle | |
| AU2014210666B2 (en) | Active Bleed For Airfoils | |
| CN103612751B (en) | Air amplification type aircraft propulsion device | |
| US5779196A (en) | Ram air drive laminar flow control system | |
| CN113682466A (en) | Aircraft non-control surface flight control method based on synthetic double-jet flow field control | |
| CN208165247U (en) | Unmanned plane based on gas jet technique turning | |
| CN108163213B (en) | Multistage supercharging fan-blade-free air propulsion method and propulsion device | |
| CN207826571U (en) | A kind of multi-stage booster Bladeless formula air propulsion device | |
| US9849975B2 (en) | Deflection cone in a reaction drive helicopter | |
| US10577086B2 (en) | High efficiency stall proof airfoil and means of control | |
| EP4086167A1 (en) | Aircraft having distributed fans for boundary layer ingestion | |
| US20220355916A1 (en) | Aircraft having distributed fans for boundary layer ingestion | |
| CN107487436B (en) | Fluidic system comprising a co-flow jet | |
| WO2011155871A9 (en) | Jet propulsion device with thrust vector control | |
| CN113738533B (en) | Independent driving turbofan system of series-connection supercharged electric turbine engine | |
| CN207004859U (en) | A kind of new vacuum pumping pump | |
| Kweder et al. | Investigation into the feasibility of an augmented propeller design with the use of a passive circulation control system | |
| Dayhoum et al. | WITHDRAWAL: Aerodynamic Investigation of Shrouded Rotors with Dual Exit Channels | |
| CN118220484A (en) | Jet-flow-based rotor flow control system and method | |
| CN114644100A (en) | Novel propeller system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |