CN109878702A - Thrust vector control device - Google Patents
Thrust vector control device Download PDFInfo
- Publication number
- CN109878702A CN109878702A CN201711274351.1A CN201711274351A CN109878702A CN 109878702 A CN109878702 A CN 109878702A CN 201711274351 A CN201711274351 A CN 201711274351A CN 109878702 A CN109878702 A CN 109878702A
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- Prior art keywords
- air
- diversion division
- flow guide
- driving
- guide member
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Abstract
A kind of Thrust vector control device includes air-flow guide member, connecting elements, first driving device and the second driving device.Air-flow guide member is adjacent to exhaust port, air-flow guide member includes ontology, first driving portion, second driving portion and interconnecting piece, air-flow passes through ontology and is guided by ontology, first driving portion, second driving portion and interconnecting piece are connected to ontology, connecting elements is movably connected interconnecting piece and exhaust propulsion device, ontology is movably attached to jet-propulsion plant by interconnecting piece and connecting elements, first driving device is connected to the first driving portion and the first driving portion of driving keeps air-flow guide member mobile towards first direction, second driving device, it is connected to the second driving portion and the second driving portion of driving keeps air-flow guide member mobile towards second direction, wherein first direction and second direction are not parallel.
Description
Technical field
The present invention relates to a kind of airflow direction guiding device more particularly to a kind of Thrust vector control devices.
Background technique
Fly up into the sky the empty dream for being not only the mankind and a kind of travel pattern of very effective rate, has and quickly reaches purpose
The efficiency on ground, therefore, it is removable in addition to due to space to estrangement caused by people, so, flight be not only have amusement and commercial affairs
Property more has other application great demand.
For Fixed Wing AirVehicle, a large amount of personnel and cargo can be no doubt carried, but this kind of carrier needs to grow very much
Runway and a large amount of relevant launching and recovering equipment, therefore be confined to airport landing, to overcome this limitation, in addition develop rotation
Rotor aircraft, such as helicopter, can be in the range VTOL of small area.But it even can be with the rotor of VTOL
Aircraft is still to the airplane parking area of setting equivalent area, can not be as the upper and lower carrying everywhere of the vehicle on ground, and is intensively building
In the big city of object, helicopter narrow still difficult to get access and common roof.
Therefore, existing R&D team sets about researching and developing single vertical translation aircraft at present, can be intensive and empty in building
Between narrow metropolitan area use, individual lift device is due to small in size, without the relatively large wing as determining rotor aircraft, because
This, which does not just have, yet determines the elevating plane and empennage in control lifting and direction on rotor aircraft, therefore how to control individual lift device
Direction becomes the important topic of individual lift device.
Summary of the invention
In view of this, the purpose of the present invention is to provide a kind of Thrust vector control devices, for using exhaust propulsion device
Aircraft for, Thrust vector control device of the invention can be installed in exhaust propulsion device exhaust port, when exhaust promote
When air-flow generation thrust is discharged by exhaust port in device, Thrust vector control device of the invention can guide air-flow and change air-flow
Direction and thereby the direction for changing thrust make aircraft turn to or go up and down whereby.
Other objects and advantages of the present invention can from disclosed herein technical characteristic in be further understood.
It is the Thrust vector control device provided by the present invention up to above-mentioned one or partly or entirely purpose or other purposes
An embodiment can be used for the exhaust propulsion device of aircraft, exhaust propulsion device has exhaust port and can produce air-flow from arranging
Gas opening discharge and generate thrust, an embodiment of Thrust vector control device of the invention include air-flow guide member, connecting elements,
First driving device and the second driving device.Adjacent to exhaust port and around exhaust port, air-flow passes through air-flow guide member
Air-flow guide member is simultaneously guided by air-flow guide member, and connecting elements is movably coupled to air-flow guide member and exhaust propulsion device,
First driving device certain driving air-flow guide member is mobile towards first direction relative to exhaust propulsion device, and first direction is to be led by air-flow
The circumferential surface for drawing part passes through the center of air-flow guide member, and the second driving device certain driving air-flow guide member is relative to exhaust propulsion device court
Second direction is mobile, and second direction is to pass through the center of air-flow guide member by the circumferential surface of air-flow guide member, wherein first direction with
Second direction is not parallel.
In one embodiment of this invention, air-flow guide member includes ontology, the first driving portion, the second driving portion and connection
Portion, for air-flow by ontology and being guided by ontology, connecting elements is rotatably connected at interconnecting piece, ontology by interconnecting piece and
Connecting elements is rotatably connected at jet-propulsion plant, and the first driving portion, the second driving portion and interconnecting piece are connected to ontology,
First driving device is connected to the first driving portion and the first driving portion of driving, so that certain driving air-flow guide member is moved towards first direction
Dynamic, the second driving device is connected to the second driving portion and the second driving portion of driving, so that certain driving air-flow guide member is towards second direction
It is mobile.
In one embodiment of this invention, ontology includes the first diversion division and support sector, and the first diversion division is around exhaust
Opening, makes air-flow be guided by the first diversion division and be discharged towards a direction, support sector is supported in the inner wall of the first diversion division and maintains
State of first diversion division around exhaust port.
In one embodiment of this invention, support sector includes the first support member and the second support member, and first supports
The opposite both ends of component are connected to the inner wall of the first diversion division, and the opposite both ends of the second support member are connected to first and lead
The inner wall in stream portion, and the first support member and the second support member are connections intersected with each other.
In one embodiment of this invention, ontology further includes the second diversion division, the second diversion division and the first diversion division in same
The heart is arranged and connects support sector.
In one embodiment of this invention, the first diversion division and the second diversion division be in a tubular form.
In one embodiment of this invention, interconnecting piece is set to the interconnection of the first support member and the second support member
Place.
It in one embodiment of this invention, is to be located at first at the interconnection of the first support member and the second support member
The geometric center of diversion division.
In one embodiment of this invention, the first driving portion and the second driving portion are set to the first diversion division, and first drives
The dynamic geometric center 90 degree of central angles apart of portion and the second driving portion relative to the first diversion division.
In one embodiment of this invention, the first support member and the second support member are to intersect to set perpendicular to each other
It sets, and the first driving portion is provided at the junction of the first support member Yu the first diversion division, the second driving portion is provided at second
Hold the junction of component and the first diversion division.
In one embodiment of this invention, connecting elements includes universal joint.
In one embodiment of this invention, first driving device and the second driving device are to be set to exhaust propulsion device
On.
In one embodiment of this invention, first direction is vertical with second direction.
Thrust vector control device of the invention is arranged at the exhaust port of exhaust propulsion device, can will promote from exhaust
The air-flow of device discharge is directed to desired direction, is whereby more than the thrust for being vented propulsion device and makees along axle center
With can also act on other directions, so can produce steering and lifting for the aircraft of installing exhaust propulsion device
Effect.
The above description is only an overview of the technical scheme of the present invention, in order to better understand the technical means of the present invention,
And it can be implemented in accordance with the contents of the specification, and in order to allow above and other objects, features and advantages of the invention can
It is clearer and more comprehensible, it is special below to lift preferred embodiment, and cooperate attached drawing, detailed description are as follows.
Detailed description of the invention
Fig. 1 is the schematic diagram that an embodiment of Thrust vector control device of the invention is installed on exhaust propulsion device.
Fig. 2 is the stereoscopic schematic diagram of an embodiment of Thrust vector control device of the invention.
Fig. 3 is the schematic top plan view of Fig. 2.
Specific embodiment
For the present invention aforementioned and other technology contents, feature and effect refer to the preferable reality of schema in following cooperation
It applies in the detailed description of example, can clearly present.The direction term being previously mentioned in following embodiment, such as: upper and lower, left,
It is right, front or rear etc., it is only the direction with reference to annexed drawings.Therefore, the direction term used is intended to be illustrative and not intended to limit
The present invention.
Fig. 1, Fig. 2 and Fig. 3 are please referred to, Fig. 1 shows an embodiments of Thrust vector control device of the invention to be installed on exhaust
Propulsion device, Fig. 2, Fig. 3 indicate an embodiment of Thrust vector control device of the invention.The Thrust vector control device of the present embodiment
100, it can be used for the exhaust propulsion device P of aircraft, exhaust propulsion device P has air inlet openings Pi and exhaust port Po,
Airflow channel P1 is formed between air inlet openings Pi and exhaust port Po, air enters exhaust propulsion device P from air inlet openings Pi,
Exhaust propulsion device P can generate air-flow F with such as propeller in airflow channel P1, and arrange air-flow F from exhaust port Po
Out, Thrust vector control device 100 includes air-flow guide member 10, connecting elements 20, first driving device 30 and the second driving dress
Set 40.Air-flow guide member 10 is positioned adjacent in exhaust port Po, and air-flow guide member 10 is movably connected by connecting elements 20
It is connected to exhaust propulsion device P, and is directed at exhaust port Po, the air-flow being discharged from exhaust port Po can pass through air-flow guide member
10, in the present embodiment, connecting elements 20 can be the exhaust port Po that exhaust propulsion device P is fixed in such as one end, another
End be rotatably attached with air-flow guide member 10 so that air-flow guide member 10 can relative to exhaust port Po with exhaust port Po
It is swung on 360 degree of any direction in parallel plane, first driving device 30 and the second driving device 40 can elapse gas
Flow guide 10 is moved up with second party in a first direction respectively, wherein first direction and second direction can be above-mentioned 360
Two not parallel directions in any direction of degree, first direction are to pass through air-flow guide member by the circumferential surface of air-flow guide member 10
The direction at 10 center, second direction are also to pass through the direction at the center of air-flow guide member 10 by the circumferential surface of air-flow guide member 10,
But first direction is not parallel with second direction, while leading by changing in above-mentioned first direction and passage air-flow in second direction
The passage amount for drawing part 10 push away air-flow guide member 10 can relative to exhaust in all directions in the range of 360 degree of periphery
Axle center L into device P generates inclination, and can form difference relative to the axle center L of exhaust propulsion device P in either direction
Tilt angle, and air-flow F is guided on desired direction.
First driving device 30 and the second driving device 40 are set on exhaust propulsion device P, in the present embodiment, the
One driving device 30 and the second driving device 40 are to be set to institute between the shell P2 and airflow channel P1 of exhaust propulsion device P
In the space P3 of formation.In the present embodiment, first driving device 30 includes stepper motor and control line, control line connection step
Into the output shaft and air-flow guide member 10 of motor, controls the output shaft rotation of stepper motor and pull control line, lead air-flow
Draw part 10 to swing in one direction, the second driving device 40 also has stepper motor and control line, controls the output of stepper motor
Axis rotates and pulls control line, swings air-flow guide member 10 in another direction, so can control air-flow guide member 10 and exist
Axle center in all directions in the range of 360 degree of its periphery relative to exhaust propulsion device P generates inclination, and air-flow F is guided
On desired direction.
As shown in Figures 2 and 3, air-flow guide member 10 includes ontology 12, the first driving portion 14, the second driving portion 16 and connects
Socket part 18, air-flow F pass through ontology 12 and are guided by ontology 12, the first driving portion 14, the second driving portion 16 and interconnecting piece 18
It is connected to ontology 12, connecting elements 20 is movably connected interconnecting piece 18 and exhaust propulsion device P (please referring to Fig. 1), ontology
12 are movably attached to jet-propulsion plant P, in the present embodiment, connecting elements by interconnecting piece 18 and connecting elements 20
20 can be universal joint, therefore ontology 12 and interconnecting piece 18 can connect 360 degree of range centered on component 20 towards any
Direction swings and generates inclination with the axle center of exhaust propulsion device P, and first driving device 30 is connected to the first driving portion 14 and drives
Dynamic first driving portion 14 keeps air-flow guide member 10 mobile towards first direction, the second driving device 40 be connected to the second driving portion 16 and
The second driving portion 16 is driven to keep air-flow guide member 10 mobile towards second direction, in the present embodiment, first direction and second direction
Be it is not parallel, so can just make air-flow guide member 10 towards either in the range of 360 degree centered on connecting elements 20 to
It swings and generates inclination with the axle center of exhaust propulsion device P, and by changing air-flow guide member 10 in a first direction with second
Tilt angle between the adjustable air-flow guide member 10 of amount of movement on direction and the axle center of exhaust propulsion device P.Preferably
Be, first direction with second direction be it is vertical, can so adapt to the control mode based on rectangular coordinates.
In the present embodiment, ontology 12 includes the first diversion division 122 and the first support sector 120.First diversion division, 122 ring
Around exhaust port Po, air-flow F is set to be guided by the first diversion division 122 and be discharged towards a direction, support sector 120 is supported in the first water conservancy diversion
The inner wall in portion 122 and the shape for maintaining the first diversion division 122, and maintain the first diversion division 122 around exhaust port Po's whereby
State.First support sector 120 includes the first support member 124 and the second support member 126, the phase of the first support member 124
Pair both ends be connected to the inner wall of the first diversion division 122, the opposite both ends of the second support member 126 are connected to the first water conservancy diversion
The inner wall in portion 122, and the first support member 124 and the second support member 126 are connections intersected with each other.In the present embodiment,
First support member 124 and the second support member 126 are elongated member, are connected by the opposite end of the first support member 124
The opposite end of the inner wall and the second support member 126 that are connected to the first diversion division 122 is connected to the interior of the first diversion division 122
Wall surface can keep so that the inner wall of the first diversion division 122 is supported by the first support member 124 and the second support member 126
The shape of one diversion division 122, and maintain the first diversion division 122 around the state of exhaust port Po.It is preferred that first supports structure
It is the geometric center positioned at the first diversion division 122, the first diversion division 122 at the interconnection of part 124 and the second support member 126
The exhaust port Po of alignment exhaust propulsion device P, it is preferable that be vented propulsion device when air-flow guide member 10 does not generate displacement
The axle center L of P passes through the geometric center of the first diversion division 122.In the present embodiment, ontology 12 further includes the second diversion division 128, the
Two diversion divisions 128 are in be arranged concentrically and connect the first support member 124 and the second support member 126 with the first tubulose 122.
The air-flow F being discharged from the exhaust port Po of exhaust propulsion device P by the first diversion division 122 and the second diversion division 128, therefore by
By making the first diversion division 122 and the second diversion division 128 in generating amount of movement on first direction and second direction, first can control
Diversion division 122 and the second diversion division 128 are in all directions in the range of 360 degree of its periphery relative to exhaust propulsion device P's
Axle center generates inclination, and air-flow F is directed on desired direction.In the present embodiment, the first diversion division 122 is led with second
Stream portion 128 is in a tubular form, it is preferable that the first diversion division 122 and the second diversion division 128 are cylindrical, therefore the first diversion division 122
Geometric center be its center of circle.
In the present embodiment, the first driving portion 14 and the second driving portion 16 are set to the first diversion division 122, and the first driving
The geometric center 90 degree of central angles apart of portion 14 and the second driving portion 16 relative to the first diversion division 122.Such as Fig. 3 institute
Show, the first driving portion 14 and the second driving portion 16 are provided at the periphery wall of the first diversion division 122, in the present embodiment, first
Driving portion 14 and the second driving portion 16 are costals, along the axially extending of the first diversion division 122 and are set to the first diversion division 122
Periphery wall.In the present embodiment, the first driving portion 14 is provided at the junction of the first support member 124 and the first diversion division 122,
Second driving portion 16 is provided at the junction of the second support member 126 and the first diversion division 122.
Thrust vector control device 100 of the invention is arranged at the exhaust port Po of exhaust propulsion device P, can will be from row
The air-flow F of gas propulsion device P discharge is directed to desired direction, is whereby more than the thrust for being vented propulsion device P
Along pivotal role, other directions can also be acted on, so the aircraft of installing exhaust propulsion device P can produce and turn
To the effect with lifting.
The above described is only a preferred embodiment of the present invention, be not intended to limit the present invention in any form, though
So the present invention has been disclosed as a preferred embodiment, and however, it is not intended to limit the invention, any technology people for being familiar with this profession
Member, without departing from the scope of the present invention, when the method and technique content using the disclosure above make it is a little more
Equivalent embodiment that is dynamic or being modified to equivalent variations, but anything that does not depart from the technical scheme of the invention content, according to the present invention
Technical spirit any simple modification, equivalent change and modification to the above embodiments, still fall within technical solution of the present invention
In the range of.
Claims (13)
1. a kind of Thrust vector control device, for being vented propulsion device, the exhaust propulsion device has exhaust port and generation
Air-flow is discharged from the exhaust port characterized by comprising
Air-flow guide member, adjacent to the exhaust port and around the exhaust port, the air-flow is guided by the air-flow
Part is simultaneously guided by the air-flow guide member；
Connecting elements movably connects the air-flow guide member and the exhaust propulsion device；
First driving device drives the air-flow guide member mobile towards first direction relative to the exhaust propulsion device, described
First direction is the center for passing through the air-flow guide member by the circumferential surface of the air-flow guide member；And
Second driving device drives the air-flow guide member mobile towards second direction relative to the exhaust propulsion device, described
Second direction is to pass through the center of the air-flow guide member by the circumferential surface of the air-flow guide member, wherein the first direction and institute
It is not parallel to state second direction.
2. Thrust vector control device as described in claim 1, which is characterized in that the air-flow guide member includes ontology, first
Driving portion, the second driving portion and interconnecting piece, the air-flow pass through the ontology and are guided by the ontology, the connection structure
Part is rotatably coupled the interconnecting piece, and the ontology is rotatably connected at by the interconnecting piece and the connecting elements
The jet-propulsion plant, first driving portion, second driving portion and the interconnecting piece are connected to the ontology, institute
It states first driving device and is connected to first driving portion and driving first driving portion, to drive the air-flow guide member
Mobile towards the first direction, second driving device is connected to second driving portion and driving second driving portion,
To drive the air-flow guide member mobile towards the second direction.
3. Thrust vector control device as claimed in claim 2, which is characterized in that the ontology includes the first diversion division and branch
Hold portion, first diversion division around the exhaust port, make the air-flow by first diversion division guide and towards a direction
Discharge, the support sector are supported in the inner wall of first diversion division and maintain first diversion division around the exhaust port
State.
4. Thrust vector control device as claimed in claim 3, which is characterized in that the support sector include the first support member with
And second support member, the opposite both ends of first support member are connected to the inner wall of first diversion division, described
The opposite both ends of second support member are connected to the inner wall of first diversion division, and first support member with it is described
Second support member is connection intersected with each other.
5. Thrust vector control device as claimed in claim 3, which is characterized in that the ontology further includes the second diversion division, institute
It is in be arranged concentrically and connect the support sector that the second diversion division, which is stated, with first diversion division.
6. Thrust vector control device as claimed in claim 5, which is characterized in that first diversion division and second water conservancy diversion
Portion is in a tubular form.
7. Thrust vector control device as claimed in claim 3, which is characterized in that the interconnecting piece is set to described first and supports structure
At the interconnection of part and second support member.
8. Thrust vector control device as claimed in claim 3, which is characterized in that first support member and described second
Holding is the geometric center for being located at first diversion division at the interconnection of component.
9. Thrust vector control device as claimed in claim 3, which is characterized in that first driving portion and second drive
Dynamic portion is set to first diversion division, and first driving portion and second driving portion are relative to first diversion division
Geometric center 90 degree of central angles apart.
10. Thrust vector control device as claimed in claim 9, which is characterized in that first support member and described
Two support member are arranged in a crossed manner perpendicular to each other, and first driving portion is provided at first support member and described the
The junction of one diversion division, second driving portion are provided at the connection of second support member Yu first diversion division
Place.
11. Thrust vector control device as described in claim 1, which is characterized in that the connecting elements includes universal joint.
12. Thrust vector control device as described in claim 1, which is characterized in that the first driving device and described second
Driving device is set in the exhaust propulsion device.
13. Thrust vector control device as described in claim 1, which is characterized in that the first direction and the second direction
It is vertical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711274351.1A CN109878702A (en) | 2017-12-06 | 2017-12-06 | Thrust vector control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711274351.1A CN109878702A (en) | 2017-12-06 | 2017-12-06 | Thrust vector control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109878702A true CN109878702A (en) | 2019-06-14 |
Family
ID=66923561
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711274351.1A Pending CN109878702A (en) | 2017-12-06 | 2017-12-06 | Thrust vector control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109878702A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113799990A (en) * | 2020-06-17 | 2021-12-17 | 林瑶章 | Propulsion device with double-layer flow guide assembly and flight carrier with propulsion device |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB888943A (en) * | 1959-08-17 | 1962-02-07 | Rolls Royce | Improvements in or relating to fan units |
| US4649701A (en) * | 1986-02-11 | 1987-03-17 | The United States Of America As Represented By The Secretary Of The Navy | Thrust nozzle with insulation |
| US4809932A (en) * | 1986-12-20 | 1989-03-07 | Messerschmitt-Bokow-Blohm GmbH | Thrust vector control for aircraft |
| CN1046019A (en) * | 1989-04-11 | 1990-10-10 | 通用电气公司 | Nozzle with thrust vectoring in yaw direction |
| CN2344561Y (en) * | 1998-04-01 | 1999-10-20 | 陈长林 | Jet tail pipe device capable of changing thrust direction in all bearing |
| US20080105781A1 (en) * | 2006-03-28 | 2008-05-08 | Airbus France | Aircraft with reduced environmental impact |
| CN101985903A (en) * | 2010-09-03 | 2011-03-16 | 清华大学 | Two-stage engine thrust steering mechanism |
| CN102114906A (en) * | 2009-12-31 | 2011-07-06 | 般若科技股份有限公司 | Propulsion system for ships |
| CN202754143U (en) * | 2012-07-26 | 2013-02-27 | 沈阳申蓝航空科技有限公司 | Rotating engine vertical take-off and landing aircraft |
| CN105308301A (en) * | 2013-04-23 | 2016-02-03 | 空中客车防务及航天公司 | Orientable rocket-motor system |
| CN106314777A (en) * | 2016-08-29 | 2017-01-11 | 英华达（上海）科技有限公司 | UAV (unmanned aerial vehicle) |
| CN106882392A (en) * | 2015-12-16 | 2017-06-23 | 空客直升机德国有限公司 | The aircraft of the exhaust of hot air part with the discharge section being pivotally mounted on including two |
-
2017
- 2017-12-06 CN CN201711274351.1A patent/CN109878702A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB888943A (en) * | 1959-08-17 | 1962-02-07 | Rolls Royce | Improvements in or relating to fan units |
| US4649701A (en) * | 1986-02-11 | 1987-03-17 | The United States Of America As Represented By The Secretary Of The Navy | Thrust nozzle with insulation |
| US4809932A (en) * | 1986-12-20 | 1989-03-07 | Messerschmitt-Bokow-Blohm GmbH | Thrust vector control for aircraft |
| CN1046019A (en) * | 1989-04-11 | 1990-10-10 | 通用电气公司 | Nozzle with thrust vectoring in yaw direction |
| CN2344561Y (en) * | 1998-04-01 | 1999-10-20 | 陈长林 | Jet tail pipe device capable of changing thrust direction in all bearing |
| US20080105781A1 (en) * | 2006-03-28 | 2008-05-08 | Airbus France | Aircraft with reduced environmental impact |
| CN102114906A (en) * | 2009-12-31 | 2011-07-06 | 般若科技股份有限公司 | Propulsion system for ships |
| CN101985903A (en) * | 2010-09-03 | 2011-03-16 | 清华大学 | Two-stage engine thrust steering mechanism |
| CN202754143U (en) * | 2012-07-26 | 2013-02-27 | 沈阳申蓝航空科技有限公司 | Rotating engine vertical take-off and landing aircraft |
| CN105308301A (en) * | 2013-04-23 | 2016-02-03 | 空中客车防务及航天公司 | Orientable rocket-motor system |
| CN106882392A (en) * | 2015-12-16 | 2017-06-23 | 空客直升机德国有限公司 | The aircraft of the exhaust of hot air part with the discharge section being pivotally mounted on including two |
| CN106314777A (en) * | 2016-08-29 | 2017-01-11 | 英华达（上海）科技有限公司 | UAV (unmanned aerial vehicle) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113799990A (en) * | 2020-06-17 | 2021-12-17 | 林瑶章 | Propulsion device with double-layer flow guide assembly and flight carrier with propulsion device |
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