CN113060290A - Electric propeller - Google Patents
Electric propeller Download PDFInfo
- Publication number
- CN113060290A CN113060290A CN202110469133.3A CN202110469133A CN113060290A CN 113060290 A CN113060290 A CN 113060290A CN 202110469133 A CN202110469133 A CN 202110469133A CN 113060290 A CN113060290 A CN 113060290A
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- CN
- China
- Prior art keywords
- air
- cabin
- air inlet
- annular mounting
- nozzle
- 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
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- 230000006835 compression Effects 0.000 claims abstract description 22
- 238000007906 compression Methods 0.000 claims abstract description 22
- 238000005507 spraying Methods 0.000 claims abstract description 22
- 238000002347 injection Methods 0.000 claims abstract description 13
- 239000007924 injection Substances 0.000 claims abstract description 13
- 230000002093 peripheral effect Effects 0.000 claims description 6
- 238000000034 method Methods 0.000 abstract description 7
- 239000000295 fuel oil Substances 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 32
- 238000012423 maintenance Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 238000003915 air pollution Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
Images
Classifications
-
- 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
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
-
- 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
- B64D27/16—Aircraft characterised by the type or position of power plant of jet type
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention relates to the technical field of engines, in particular to an electric propeller which comprises a shell, wherein an air injection cabin and an air compression cabin are arranged in the shell, and the air injection cabin and the air compression cabin are communicated through a nozzle arranged between the air injection cabin and the air compression cabin; a boosting device for accelerating air to enter the air spraying cabin is arranged in the nozzle; a plurality of auxiliary air inlet devices are arranged at one end of the shell, which is provided with the air inlet, and the auxiliary air inlet devices are communicated with the air compression cabin; the auxiliary air inlet device comprises a hollow air inlet column arranged on the shell, and air flow accelerating devices used for accelerating air flow are arranged in the air inlet column. The invention has simple integral structure, takes the auxiliary air inlet device as a power source, can improve the stability of the engine, embeds the vector fan in the air inlet column, can also improve the safety performance, does not use fuel oil in the whole process, can greatly reduce pollution, can reduce noise to a certain extent, and realizes the electric air engine in the true sense.
Description
Technical Field
The invention relates to the technical field of engines, in particular to an electric propeller.
Background
At present, aeroengines used by various aircrafts belong to combustion engine engines, not only a large amount of energy sources such as fuel oil, gas and the like are consumed during operation, but also air pollution is caused, the combustion engine engines are complex in mechanical structure, large in size and high in maintenance difficulty, and generate large noise during operation.
The engine with a single power source basically has no self-rescue possibility when meeting the faults of blade breakage, engine flameout and the like. With the emergence of novel aircrafts such as unmanned planes, electric airplanes and electric flying automobiles, an electric air engine is urgently needed as a power source of the future flying electric aircrafts, particularly, in a manned state, the engine cannot be in a mode of a single motor and a single propeller, and the manned electric aircrafts are easy to encounter the occurrence of events such as bird impact and the like or the occurrence of events such as single motor failure and the like in the air flying process.
Disclosure of Invention
In order to solve the problems, the invention provides an electric propeller which has the advantages of simple structure, no complex mechanical structure, low maintenance cost, multiple electric power sources, improved reliability, no pollution to the atmospheric environment in the use process, low noise, reduced potential safety hazard of the existing engine and safer use process.
The invention relates to an electric propeller which comprises a shell, wherein a gas spraying cabin and a gas compressing cabin are arranged in the shell, the gas spraying cabin is communicated with the gas compressing cabin through a nozzle arranged between the gas spraying cabin and the gas compressing cabin, one end of the gas spraying cabin, which is far away from the nozzle, is a gas spraying hole, one end of the gas compressing cabin, which is far away from the nozzle, is a gas inlet, and the gas spraying hole and the gas inlet both extend out of the shell;
a boosting device for accelerating air to enter the air spraying cabin is arranged in the nozzle;
a plurality of auxiliary air inlet devices are arranged at one end of the shell, which is provided with the air inlet, and the auxiliary air inlet devices are communicated with the air compression cabin;
the auxiliary air inlet device comprises a hollow air inlet column arranged on the shell, and air flow accelerating devices used for accelerating air flow are arranged in the air inlet column.
Preferably, the airflow accelerating device comprises a scroll, and the scroll is fixedly connected with the inner wall of the air inlet column through a scroll fixing arm arranged on the peripheral surface of the scroll;
the vortex shaft is sleeved with a plurality of vector fan propelling motors, vector fans matched with the inner areas of the air inlet columns are arranged on the vector fan propelling motors, and when the vector fan propelling motors drive the vector fans to rotate, air enters the air compressing cabin through the air inlet columns.
Preferably, six vector fan propulsion motors are arranged on the same scroll, wherein four vector fan propulsion motors are located on the same side of the scroll fixing arm connected to the scroll.
Or preferably, one end of the shell, which is provided with the auxiliary air inlet device, comprises a plurality of annular mounting plates;
in two adjacent annular mounting plates, the inner diameter of one annular mounting plate is larger than that of the other annular mounting plate, and the central axes of the two annular mounting plates are positioned on the same straight line;
two adjacent annular mounting plates are fixedly connected through a middle annular plate;
the gas inlet is arranged at the center of the annular mounting plate with the smallest outer diameter;
and a plurality of air inlet columns are uniformly distributed on the annular mounting plate.
Preferably, the middle annular plate is cylindrical, and the outer diameter of one end of the middle annular plate is larger than that of the other end of the middle annular plate; the central axes of the middle ring plates are positioned on the same straight line and are superposed with the central axis of the ring-shaped mounting plate;
the gas inlet projects through at least two annular mounting plates in a direction away from the compressed gas cabin.
Preferably, the annular mounting plates are provided in three.
Preferably, one end, close to the nozzle, of the air inlet column on the annular mounting plate with the largest outer diameter is arranged towards the nozzle, and the central axis of the air inlet column on the annular mounting plate is intersected with the central axis of the connected annular mounting plate;
the central axes of the air inlet columns on the other two annular mounting plates are parallel to the central axis of the connected annular mounting plate.
Preferably, the boosting device comprises a boosting scroll, and the boosting scroll is fixedly connected with the inner wall of the nozzle through a boosting scroll fixing arm arranged on the peripheral surface of the boosting scroll;
the air compressor is characterized in that a plurality of turbofan propulsion motors are sleeved on the boosting scroll shaft, the turbofan propulsion motors are provided with turbofan wheels matched with the inner areas of the nozzles, and when the turbofan propulsion motors drive the turbofan wheels to rotate, the turbofan wheels eject air in the air compression chamber through the nozzles.
Preferably, the vector fan propulsion motor and the turbofan propulsion motor are both connected with an engine controller through the same electronic governor, and the engine controller power management module is electrically connected with a power supply;
the air inlet column is internally provided with a temperature sensor for detecting the temperature of the vector fan, a rotating speed sensor for detecting the rotating speed of the vector fan and an air speed sensor for detecting the air speed in the air inlet column, and the temperature sensor, the rotating speed sensor and the air speed sensor are all connected with the engine controller;
the temperature sensor, the wind speed sensor, the rotating speed sensor, the vector fan propelling motor and the turbine fan propelling motor are all connected with the power management module.
Preferably, the housing comprises an inner shell and an outer shell, the inner shell being fixedly arranged within the outer shell;
the air injection cabin, the air compression cabin and the nozzle are all arranged in the inner shell, the maximum inner diameter of the air injection cabin is smaller than that of the air compression cabin, and the maximum inner diameter of the nozzle is not larger than the minimum inner diameter of the air injection cabin and the air compression cabin;
the shell is in a cone cylinder shape, one end of the shell is fixedly connected with the annular mounting plate with the largest outer diameter, and the gas outlet is arranged at the other end of the shell;
one end of the air inlet column, which is far away from the compressed air cabin, is provided with a cover body for preventing foreign matters from entering, and the cover body is fixedly connected with the air inlet column.
The invention has simple integral structure, no complex mechanical structure, convenient maintenance and maintenance cost saving, takes the auxiliary air inlet device as a power source, can improve the stability of the engine, wherein the power source can be increased or decreased along with the magnitude of required thrust, can be suitable for various scenes, embeds the vector fan in the air inlet column, can also improve the safety performance and reduce the injury to personnel, does not use fuel oil in the whole process, can greatly reduce pollution, can reduce noise to a certain extent, and realizes the electric air engine in the true sense.
Drawings
FIG. 1 is a schematic view of the structure of the present invention.
Fig. 2 is a schematic view of the internal structure of the present invention.
FIG. 3 is a schematic view of the planer structure of the present invention.
FIG. 4 is a schematic structural diagram of a vector fan according to the present invention.
FIG. 5 is a schematic structural diagram of a vector fan according to the present invention.
FIG. 6 is a schematic structural diagram of a turbofan according to the present invention.
Fig. 7 is a schematic view of the air flow of the present invention.
FIG. 8 is a control system diagram of the present invention.
Reference numerals: 1-outer shell, 2-inner shell, 3-compressed air cabin, 4-nozzle, 5-jet cabin, 6-air inlet, 7-air inlet column, 8-cover body, 9-vector fan, 10-vector fan propelling motor, 11-scroll, 12-scroll fixing arm, 13-turbo fan, 14-turbo fan propelling motor, 15-boosting scroll and 16-boosting scroll fixing arm.
Detailed Description
The invention relates to an electric propeller which comprises a shell, wherein a gas spraying cabin 5 and a gas compressing cabin 3 are arranged in the shell, the gas spraying cabin 5 is communicated with the gas compressing cabin 3 through a nozzle 4 arranged between the gas spraying cabin 5 and the gas compressing cabin 3, one end of the gas spraying cabin 5, which is far away from the nozzle 4, is a gas spraying hole, one end of the gas compressing cabin 3, which is far away from the nozzle 4, is a gas inlet 6, and the gas spraying hole and the gas inlet 6 both extend out of the shell;
a boosting device for accelerating air to enter the air spraying cabin 5 is arranged in the nozzle 4;
a plurality of auxiliary air inlet devices are arranged at one end of the shell, which is provided with the air inlet 6, and the auxiliary air inlet devices are communicated with the air compressing cabin 3;
the auxiliary air inlet device comprises a hollow air inlet column 7 arranged on the shell, and air flow accelerating devices used for accelerating air flow are arranged in the air inlet column 7.
The airflow accelerating device comprises a scroll shaft 11, wherein the scroll shaft 11 is fixedly connected with the inner wall of the air inlet column 7 through a scroll shaft fixing arm 12 arranged on the peripheral surface of the scroll shaft 11;
the vortex shaft 11 is sleeved with a plurality of vector fan propelling motors 10, the vector fan propelling motors 10 are provided with vector fans 9 matched with the inner areas of the air inlet columns 7, and when the vector fan propelling motors 10 drive the vector fans 9 to rotate, air enters the air compression cabin 3 through the air inlet columns 7.
Six vector fan propulsion motors 10 are arranged on the same scroll 11, wherein four vector fan propulsion motors 10 are positioned on the same side of a scroll fixing arm 12 connected to the scroll 11.
The end of the shell, which is provided with the auxiliary air inlet device, comprises a plurality of annular mounting plates;
in two adjacent annular mounting plates, the inner diameter of one annular mounting plate is larger than that of the other annular mounting plate, and the central axes of the two annular mounting plates are positioned on the same straight line;
two adjacent annular mounting plates are fixedly connected through a middle annular plate;
the gas inlet 6 is arranged at the center of the annular mounting plate with the smallest outer diameter;
a plurality of air inlet columns 7 are uniformly distributed on the annular mounting plate.
The middle annular plate is cylindrical, and the outer diameter of one end of the middle annular plate is larger than that of the other end of the middle annular plate; the central axes of the middle ring plates are positioned on the same straight line and are superposed with the central axis of the ring-shaped mounting plate;
the gas inlet 6 projects away from the compressed gas chamber 3 by at least two annular mounting plates.
The annular mounting plates are arranged in three.
One end, close to the nozzle 4, of the air inlet column 7 on the annular mounting plate with the largest outer diameter in the three annular mounting plates is arranged towards the nozzle 4, and the central axis of the air inlet column 7 on the annular mounting plate is intersected with the central axis of the connected annular mounting plate;
the central axes of the air inlet columns 7 on the other two annular mounting plates are parallel to the central axis of the connected annular mounting plate.
The boosting device comprises a boosting scroll shaft 15, and the boosting scroll shaft 15 is fixedly connected with the inner wall of the nozzle 4 through a boosting scroll shaft fixing arm 16 arranged on the peripheral surface of the boosting scroll shaft 15;
the boosting scroll shaft 15 is sleeved with a plurality of turbofan propulsion motors 14, the turbofan propulsion motors 14 are provided with turbofan 13 matched with the inner area of the nozzle 4, when the turbofan propulsion motors 14 drive the turbofan 13 to rotate, the turbofan 13 ejects air in the compressed air cabin 3 through the nozzle 4.
The vector fan propulsion motor 10 and the turbofan propulsion motor 14 are both connected with an engine controller through the same electronic governor, and the engine controller is electrically connected with a power supply through a power management module; the rotating speed of each vector fan propelling motor 10 in each air inlet column 7 is adjusted through an engine controller and an electronic speed regulator, so that the control of the overall thrust of the invention is facilitated.
And a temperature sensor for detecting the temperature of the vector fan 9, a rotating speed sensor for detecting the rotating speed of the vector fan 9 and an air speed sensor for detecting the air speed in the air inlet column 7 are arranged in the air inlet column 7, and the temperature sensor, the rotating speed sensor and the air speed sensor are all connected with the engine controller.
The temperature sensor, the wind speed sensor, the rotational speed sensor, the vector fan 9, the vector fan propulsion motor 10 and the turbofan propulsion motor 14 are all connected with a power management module, wherein the power management module can supply power for different electronic elements.
In one embodiment, the power management module may be a VITA-62 compatible power converter of Huage trade, Inc., the electronic governor may be an E6 type electronic governor, the engine controller may be an Arm-based general microcontroller of Enzhipu semiconductor Dutch, Inc., the speed sensor may be an YD62 explosion-proof speed sensor of Shanghai vibration measurement Automation instruments, Inc., the speed sensor may be a miniature mini pen type pipeline speed sensor of Beijing Hua accustomed technologies, Inc., and the temperature sensor may be a DS18B20 digital temperature sensor of Wuzhongzhongzhong sensor technologies, Inc.
The shell comprises an inner shell 2 and an outer shell 1, wherein the inner shell 2 is fixedly arranged in the outer shell 1;
the air injection cabin 5, the air compression cabin 3 and the nozzle 4 are all arranged in the inner shell 2, the maximum inner diameter of the air injection cabin 5 is smaller than the maximum inner diameter of the air compression cabin 3, and the maximum inner diameter of the nozzle 4 is not larger than the minimum inner diameter of the air injection cabin 5 and the air compression cabin 3;
the outer shell 1 is in a cone cylinder shape, one end of the outer shell 1 is fixedly connected with the annular mounting plate with the largest outer diameter, and the gas outlet is arranged at the other end of the outer shell 1;
one end of the air inlet column 7 far away from the compressed air chamber 3 is provided with a cover body 8 for preventing foreign matters from entering, and the cover body 8 is fixedly connected with the air inlet column 7.
Still install temperature sensor and revolution speed sensor in the air inlet column 7, can look over the rotational speed of vector fan 9 in real time and the temperature on it, wherein the quantity of air inlet column 7 can suitably increase or reduce according to the size of thrust, and the air that accelerates through air inlet column 7 finally enters into air compressing cabin 3.
The working principle of the invention is as follows:
the vector fan propulsion motor 10 drives the vector fan 9 which is arranged on the vector fan propulsion motor to rotate around a vortex shaft 11 which is arranged on a vortex shaft fixing arm 12 fixedly connected on the inner wall of the air inlet column 7, in the rotating process of the vector fan 9, external air enters the air inlet column 7 through a cover body 8 arranged on the air inlet column 7, the air passes through the air inlet column 7 and is accelerated by the vector fan 9 to rapidly enter the compression chamber 3 in the inner shell 2, a part of the air changes the direction in the compression chamber 3, the air in the compression chamber 3 rapidly passes through the nozzle opening 4 and is ejected out of the nozzle opening 4 to the air injection chamber 5, because the compression chamber 3 has a large amount of air flowing at the moment, a large amount of air is driven to enter the compression chamber 3 through the air inlet 6, so that the air inlet 6 and the air inlet column 7 both have air to enter the compression chamber 3, and the compression chamber 3 has more air passing through the nozzle opening 4 due to the large amount of air flowing together, and is thus ejected out of the housing, thereby generating a corresponding thrust.
The invention has simple integral structure, no complex mechanical structure, convenient maintenance and maintenance cost saving, takes the auxiliary air inlet device as a power source, can improve the stability of the engine, wherein the power source can be increased or decreased along with the magnitude of required thrust, can be suitable for various scenes, embeds the vector fan 9 in the air inlet column 7, can also improve the safety performance and reduce the harm to personnel, does not use fuel oil in the whole process, can greatly reduce pollution, can reduce noise to a certain extent, and realizes the electric air engine in the true sense.
Claims (10)
1. An electric propeller comprises a shell, and is characterized in that an air spraying cabin (5) and a compressed air cabin (3) are arranged in the shell, the air spraying cabin (5) is communicated with the compressed air cabin (3) through a nozzle (4) arranged between the air spraying cabin (5) and the compressed air cabin (3), one end of the air spraying cabin (5) far away from the nozzle (4) is a gas spraying hole, one end of the compressed air cabin (3) far away from the nozzle (4) is a gas inlet (6), and the gas spraying hole and the gas inlet (6) extend out of the shell;
a boosting device for accelerating air to enter the air spraying cabin (5) is arranged in the nozzle (4);
a plurality of auxiliary air inlet devices are arranged at one end of the shell, which is provided with the air inlet (6), and the auxiliary air inlet devices are communicated with the air compression cabin (3);
the auxiliary air inlet device comprises a hollow air inlet column (7) arranged on the shell, and air flow accelerating devices used for accelerating air flow are arranged in the air inlet column (7).
2. The electric propeller as recited in claim 1, wherein the airflow accelerating device comprises a scroll shaft (11), the scroll shaft (11) is fixedly connected with the inner wall of the air inlet column (7) through a scroll shaft fixing arm (12) arranged on the peripheral surface of the scroll shaft (11);
the vector fan air compressor is characterized in that a plurality of vector fan propelling motors (10) are sleeved on the scroll shafts (11), vector fans (9) matched with the inner area of the air inlet column (7) are arranged on the vector fan propelling motors (10), when the vector fan propelling motors (10) drive the vector fans (9) to rotate, air enters the air compression cabin (3) through the air inlet column (7).
3. An electric propeller as claimed in claim 2, characterized in that six vector fan propulsion motors (10) are arranged on the same scroll shaft (11), wherein four vector fan propulsion motors (10) are located on the same side of the scroll shaft fixing arm (12) to which the scroll shaft (11) is connected.
4. An electric thruster as claimed in any one of claims 1 to 3 wherein the end of the housing at which the auxiliary air inlet means is located comprises a plurality of annular mounting plates;
in two adjacent annular mounting plates, the inner diameter of one annular mounting plate is larger than that of the other annular mounting plate, and the central axes of the two annular mounting plates are positioned on the same straight line;
two adjacent annular mounting plates are fixedly connected through a middle annular plate;
the gas inlet (6) is arranged at the center of the annular mounting plate with the smallest outer diameter;
a plurality of air inlet columns (7) are uniformly distributed on the annular mounting plate.
5. The electric propeller as claimed in claim 4, wherein the intermediate ring plate has a cylindrical shape, and an outer diameter of one end of the intermediate ring plate is larger than that of the other end; the central axes of the middle ring plates are positioned on the same straight line and are superposed with the central axis of the ring-shaped mounting plate;
the gas inlet (6) extends out through at least two annular mounting plates in the direction away from the compressed gas chamber (3).
6. An electric thruster as claimed in claim 5 wherein said annular mounting plate is provided in three.
7. An electric thruster according to claim 6, characterized in that the end of the inlet column (7) of the three annular mounting plates with the largest outer diameter, which end is close to the nozzle (4), is arranged towards the nozzle (4), and the central axis of the inlet column (7) of the annular mounting plates intersects the central axis of the connected annular mounting plates;
the central axes of the air inlet columns (7) on the other two annular mounting plates are parallel to the central axis of the connected annular mounting plate.
8. The electric propeller as claimed in claim 3, wherein the boosting device comprises a boosting scroll (15), the boosting scroll (15) is fixedly connected with the inner wall of the nozzle (4) through a boosting scroll fixing arm (16) arranged on the peripheral surface of the boosting scroll (15);
the air compressor is characterized in that a plurality of turbofan propulsion motors (14) are sleeved on the boosting scroll shaft (15), turbofan (13) matched with the inner area of the nozzle (4) are arranged on the turbofan propulsion motors (14), and when the turbofan propulsion motors (14) drive the turbofan (13) to rotate, the turbofan (13) ejects air in the compressed air cabin (3) through the nozzle (4).
9. The electric thruster of claim 8, wherein said vector fan propulsion motor (10) and turbofan propulsion motor (14) are connected to an engine controller through the same electronic governor, said engine controller being electrically connected to a power supply through a power management module;
a temperature sensor for detecting the temperature of the vector fan (9), a rotating speed sensor for detecting the rotating speed of the vector fan (9) and a wind speed sensor for detecting the wind speed in the air inlet column (7) are arranged in the air inlet column (7), and the temperature sensor, the rotating speed sensor and the wind speed sensor are all connected with the engine controller;
the temperature sensor, the wind speed sensor, the rotating speed sensor, the vector fan (9), the vector fan propulsion motor (10) and the turbofan propulsion motor (14) are all connected with the power management module.
10. An electric thruster according to claim 4, characterized in that the housing comprises an inner casing (2) and an outer casing (1), the inner casing (2) being fixedly arranged inside the outer casing (1);
the air injection cabin (5), the compressed air cabin (3) and the nozzle (4) are all arranged in the inner shell (2), the maximum inner diameter of the air injection cabin (5) is smaller than the maximum inner diameter of the compressed air cabin (3), and the maximum inner diameter of the nozzle (4) is not larger than the minimum inner diameter of the air injection cabin (5) and the compressed air cabin (3);
the outer shell (1) is in a cone cylinder shape, one end of the outer shell (1) is fixedly connected with the annular mounting plate with the largest outer diameter, and the gas jet hole is formed in the other end of the outer shell (1);
one end of the air inlet column (7) far away from the compressed air cabin (3) is provided with a cover body (8) for preventing foreign matters from entering, and the cover body (8) is fixedly connected with the air inlet column (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110469133.3A CN113060290A (en) | 2021-04-29 | 2021-04-29 | Electric propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110469133.3A CN113060290A (en) | 2021-04-29 | 2021-04-29 | Electric propeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113060290A true CN113060290A (en) | 2021-07-02 |
Family
ID=76568279
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110469133.3A Pending CN113060290A (en) | 2021-04-29 | 2021-04-29 | Electric propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113060290A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101871441A (en) * | 2009-04-22 | 2010-10-27 | 袁锋 | Electric jet engine |
| US20140060005A1 (en) * | 2008-08-19 | 2014-03-06 | Richard H. Lugg | Magnetic advanced generation jet electric turbine |
| CN205559070U (en) * | 2016-03-04 | 2016-09-07 | 王力丰 | Use system and aircraft of compressed air as application of force source |
| CN207161224U (en) * | 2017-01-05 | 2018-03-30 | 南京工业职业技术学院 | A kind of unsteady annular jet jet pipe for improving pulse detonation engine thrust coefficient |
| CN110588969A (en) * | 2019-10-01 | 2019-12-20 | 重庆碟翔航空科技有限公司 | Three-dimensional variable propulsion flying saucer |
| CN111237084A (en) * | 2020-02-17 | 2020-06-05 | 王镇辉 | Electric-driven jet aircraft engine and aircraft |
| CN111486071A (en) * | 2020-04-24 | 2020-08-04 | 北京卫星环境工程研究所 | Air suction type electric propeller |
| US20200385136A1 (en) * | 2019-06-07 | 2020-12-10 | Bryan B. Solstin | Laminar inducing apparatus |
-
2021
- 2021-04-29 CN CN202110469133.3A patent/CN113060290A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140060005A1 (en) * | 2008-08-19 | 2014-03-06 | Richard H. Lugg | Magnetic advanced generation jet electric turbine |
| CN101871441A (en) * | 2009-04-22 | 2010-10-27 | 袁锋 | Electric jet engine |
| CN205559070U (en) * | 2016-03-04 | 2016-09-07 | 王力丰 | Use system and aircraft of compressed air as application of force source |
| CN207161224U (en) * | 2017-01-05 | 2018-03-30 | 南京工业职业技术学院 | A kind of unsteady annular jet jet pipe for improving pulse detonation engine thrust coefficient |
| US20200385136A1 (en) * | 2019-06-07 | 2020-12-10 | Bryan B. Solstin | Laminar inducing apparatus |
| CN110588969A (en) * | 2019-10-01 | 2019-12-20 | 重庆碟翔航空科技有限公司 | Three-dimensional variable propulsion flying saucer |
| CN111237084A (en) * | 2020-02-17 | 2020-06-05 | 王镇辉 | Electric-driven jet aircraft engine and aircraft |
| CN111486071A (en) * | 2020-04-24 | 2020-08-04 | 北京卫星环境工程研究所 | Air suction type electric propeller |
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