CN113401350A - Ducted aircraft - Google Patents
Ducted aircraft Download PDFInfo
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- CN113401350A CN113401350A CN202110621876.8A CN202110621876A CN113401350A CN 113401350 A CN113401350 A CN 113401350A CN 202110621876 A CN202110621876 A CN 202110621876A CN 113401350 A CN113401350 A CN 113401350A
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- transmission mechanism
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- transmission assembly
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- 230000005540 biological transmission Effects 0.000 claims abstract description 204
- 230000001360 synchronised effect Effects 0.000 claims abstract description 108
- 230000007246 mechanism Effects 0.000 claims abstract description 104
- 230000000712 assembly Effects 0.000 claims abstract description 19
- 238000000429 assembly Methods 0.000 claims abstract description 19
- 238000000034 method Methods 0.000 description 13
- 230000009467 reduction Effects 0.000 description 13
- 230000008569 process Effects 0.000 description 8
- 230000009471 action Effects 0.000 description 5
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
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Abstract
The invention provides a ducted aircraft, comprising: the device comprises a machine body, four transmission assemblies, a first synchronous transmission mechanism and a second synchronous transmission mechanism; the first transmission assembly and the second transmission assembly are arranged on one side of the machine body, the third transmission assembly and the fourth transmission assembly are arranged on the other side of the machine body, one end of the first synchronous transmission mechanism is connected to the first transmission assembly, the other end of the first synchronous transmission mechanism is connected to the third transmission assembly, one end of the second synchronous transmission mechanism is connected to the second transmission assembly, and the other end of the second synchronous transmission mechanism is connected to the fourth transmission assembly; wherein, first transmission assembly, second transmission assembly, third transmission assembly and fourth transmission assembly's structure is the same, and every transmission assembly includes: the ducted aircraft comprises a duct, an engine and a propeller, wherein the duct is connected to an aircraft body, the propeller is arranged in the duct, the engine is connected to the propeller, the engine is connected to one of a first synchronous transmission mechanism or a second synchronous transmission mechanism, and the ducted aircraft is large in overall load, long in flight time and stable in flight.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a ducted aircraft.
Background
In recent years, the application of unmanned aerial vehicles shows explosive growth, especially multi-rotor unmanned aerial vehicles to advantages such as its convenient operation, environmental suitability are strong, the operation is stable, extensively apply to task scenes such as aerial photography, electric power patrol line, agriculture and forestry plant protection, frontier defense patrol. Traditional many rotor unmanned aerial vehicle adopts the motor as the power supply, battery powered, and this kind of mode is because battery energy density is low, when providing the same energy, required quality is big, therefore the complete machine load is less, and the time of flight is shorter. When adopting the engine as the power supply, because be the oil-fired, and oily ability density is very high, still can progressively reduce at the in-process quality of oil consumption simultaneously, then can overcome electronic many rotor unmanned aerial vehicle load little, the shortcoming of short time of flight, but oil moves many rotor unmanned aerial vehicle also has its shortcoming, is exactly the rotational speed of a plurality of rotors of accurate and synchro control to influence unmanned aerial vehicle's flight stability. In the face of the strong demands of agriculture and forestry plant protection, emergency rescue and other task scenes on large-load, long-endurance and high-stability unmanned aerial vehicles, it is necessary to develop a ducted aircraft which can have large complete machine load, long endurance and stable flight.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a ducted aircraft which has the advantages of large overall load, long flight time and stable flight.
In order to achieve the above object, the present invention provides a ducted aircraft comprising: the device comprises a machine body, four transmission assemblies, a first synchronous transmission mechanism and a second synchronous transmission mechanism;
wherein, four drive assembly do: the transmission mechanism comprises a first transmission assembly, a second transmission assembly, a third transmission assembly and a fourth transmission assembly;
the first transmission assembly and the second transmission assembly are arranged on one side of the machine body, the third transmission assembly and the fourth transmission assembly are arranged on the other side of the machine body, one end of the first synchronous transmission mechanism is connected to the first transmission assembly, the other end of the first synchronous transmission mechanism is connected to the third transmission assembly, one end of the second synchronous transmission mechanism is connected to the second transmission assembly, and the other end of the second synchronous transmission mechanism is connected to the fourth transmission assembly;
wherein the first transmission assembly, the second transmission assembly, the third transmission assembly and the fourth transmission assembly have the same structure, and each transmission assembly comprises: the bypass is connected to the fuselage, the screw propeller is arranged in the bypass, the engine is connected to the screw propeller, and the engine is connected to one of the first synchronous transmission mechanism or the second synchronous transmission mechanism.
Preferably, each of the transmission assemblies further comprises: and the engine is connected to the one-way clutch, the engine is connected to the propeller through the one-way clutch, and the engine is connected to one of the first synchronous transmission mechanism or the second synchronous transmission mechanism through the implement clutch.
Preferably, the engine is a piston engine.
Preferably, each of the transmission assemblies further comprises: the engine comprises a bracket and a housing, wherein the bracket is connected to the duct, the engine is arranged on the bracket, and the housing covers the engine.
Preferably, each of the transmission assemblies further comprises: and the slip flow rudder is arranged on the lower end surface of the duct.
Preferably, the method further comprises the following steps: and the steering engine is connected to the slipstream rudder.
Preferably, the method further comprises the following steps: the synchronous transmission mechanism comprises a first synchronous transmission mechanism node, a second synchronous transmission mechanism node and a connecting rod, wherein the first synchronous transmission mechanism node and the second synchronous transmission mechanism node are arranged in the machine body, the first synchronous transmission mechanism is connected to the first synchronous transmission mechanism node, the second synchronous transmission mechanism is connected to the second synchronous transmission mechanism node, one end of the connecting rod is connected to the first synchronous transmission mechanism node, and the other end of the connecting rod is connected to the second synchronous transmission mechanism node.
Preferably, the duct is connected to the fuselage by a quilted beam or frame.
The invention has the beneficial effects that:
(1) the ducted aircraft provided by the invention can be used for enabling the whole ducted aircraft to have large load and long endurance by taking the engine as a power source.
(2) In the working process, the rising of the ducted aircraft can be realized by increasing the engine rotating speed of the first transmission assembly, the second transmission assembly, the third transmission assembly and the fourth transmission assembly to improve the thrust, and the detail process of rotating speed increase is as follows: the engine with high starting speed drives the four propellers to act through the first synchronous transmission mechanism and the second synchronous transmission mechanism, but because the load is too large, a single engine cannot be driven quickly, the increase of the rotating speed can be inhibited, then the engine started subsequently catches up to provide power together, the synchronous rotation of the four transmission assemblies can be realized, and the stable takeoff and flight of the ducted aircraft are realized.
(3) In the working process, the thrust can be reduced through the reduction of the engine rotating speed of the first transmission assembly, the second transmission assembly, the third transmission assembly and the fourth transmission assembly, and the detail process of the rotating speed reduction is as follows: the speed of the engine is reduced, the speed of the propellers is reduced simultaneously under the action of resistance, and the four propellers always rotate at the same speed due to the first synchronous transmission mechanism and the second synchronous transmission mechanism; if the rotating speed reduction rate of the propeller is greater than the rotating speed reduction rate of the engine, the engine with the slow rotating speed reduction bears the load, but the load is too large, so that the rotating speed reduction rate of a single engine cannot be borne, the rotating speed reduction rate of the single engine is increased, the reducing speeds of other engines are caught up, the condition that the four engines bear the load together is finally formed, synchronous rotation of the four transmission assemblies can be realized, and stable landing of the ducted aircraft is realized.
Drawings
FIG. 1 is a schematic structural view of a ducted aircraft in accordance with a first embodiment of the present invention;
FIG. 2 is a schematic structural view of a ducted aircraft in accordance with a second embodiment of the present invention;
FIG. 3 is a schematic structural view of a ducted aircraft in accordance with a third embodiment of the present invention;
FIG. 4 is a schematic structural view of a ducted aircraft in accordance with a fourth embodiment of the present invention;
figure 5 is a schematic structural view of a ducted aircraft in accordance with a fifth embodiment of the present invention.
Description of reference numerals:
1, a machine body; 2, an engine; 3, a propeller; 4, a duct; 5, a slipstream rudder; 6 a first synchronous transmission mechanism; 7 a one-way clutch; 8 a first synchronous drive mechanism node; 9 a second synchronous drive mechanism node; 10 a second synchronous transmission mechanism; 11. a first transmission assembly; 12 a second transmission assembly; 13 a third transmission assembly; 14 fourth transmission component and 15 connecting rod.
Detailed Description
The technical scheme of the invention is described in detail in the following with reference to the accompanying drawings.
FIG. 1 is a schematic structural view of a ducted 4 aircraft according to a first embodiment of the present invention; FIG. 2 is a schematic structural view of a ducted 4 aircraft according to a second embodiment of the present invention; FIG. 3 is a schematic structural view of a ducted 4 aircraft in accordance with a third embodiment of the present invention; FIG. 4 is a schematic structural view of a ducted 4 aircraft in accordance with a fourth embodiment of the present invention; figure 5 is a schematic structural view of a ducted 4 aircraft according to a fifth embodiment of the invention.
As shown in fig. 1 to 5, according to an aspect of the present invention, there is provided a ducted 4 aircraft comprising: the device comprises a machine body 1, four transmission assemblies, a first synchronous transmission mechanism 6 and a second synchronous transmission mechanism 10;
wherein, four drive assembly do: a first transmission assembly 11, a second transmission assembly 12, a third transmission assembly 13 and a fourth transmission assembly 14;
the first transmission assembly 11 and the second transmission assembly 12 are arranged on one side of the machine body 1, the third transmission assembly 13 and the fourth transmission assembly 14 are arranged on the other side of the machine body 1, one end of the first synchronous transmission mechanism 6 is connected to the first transmission assembly 11, the other end of the first synchronous transmission mechanism is connected to the third transmission assembly 13, one end of the second synchronous transmission mechanism 10 is connected to the second transmission assembly 12, and the other end of the second synchronous transmission mechanism is connected to the fourth transmission assembly 14;
wherein the first transmission assembly 11, the second transmission assembly 12, the third transmission assembly 13 and the fourth transmission assembly 14 have the same structure, and each of the transmission assemblies comprises: the engine comprises a duct 4, an engine 2 and a propeller 3, wherein the duct 4 is connected to the fuselage 1, the propeller 3 is arranged in the duct 4, the engine 2 is connected to the propeller 3, and the engine 2 is connected to one of the first synchronous transmission mechanism 6 or the second synchronous transmission mechanism 10.
The ducted 4 aircraft provided by the invention can enable the ducted 4 aircraft to have large overall load and long endurance by taking the engine 2 as a power source.
During the operation, the ascent of the ducted 4 aircraft can be realized by increasing the rotating speed and thrust of the engine 2 of the first transmission assembly 11, the second transmission assembly 12, the third transmission assembly 13 and the fourth transmission assembly 14, and the detail process of the rotating speed increase is as follows: the engine 2 with high starting speed drives the four propellers 3 to act through the first synchronous transmission mechanism 6 and the second synchronous transmission mechanism 10, but because the load is too large, the single engine 2 cannot be driven quickly, the increase of the rotating speed can be inhibited, then the engine 2 started subsequently catches up to provide power together, the synchronous rotation of the four transmission components can be realized, and the stable takeoff and flight of the ducted 4 aircraft are realized.
During operation, the thrust can be reduced by the rotation speed reduction of the engine 2 of the first transmission assembly 11, the second transmission assembly 12, the third transmission assembly 13 and the fourth transmission assembly 14, and the detail process of the rotation speed reduction is as follows: the speed of the engine 2 is reduced, the speed of the propellers 3 is reduced simultaneously under the action of resistance, and the four propellers 3 are always at the same rotating speed due to the first synchronous transmission mechanism 6 and the second synchronous transmission mechanism 10; if the rotating speed reduction rate of the propeller 3 is greater than that of the engine 2, the engine 2 with the slow rotating speed reduction bears the load, but the load is too large, so that the rotating speed reduction rate of the engine 2 cannot be increased due to the fact that a single engine 2 cannot bear the load, the falling speed of other engines 2 is caught up, the condition that the four engines 2 bear the load together is finally formed, synchronous rotation of the four transmission assemblies can be achieved, and stable landing of the ducted 4 aircraft is achieved.
As shown in fig. 1 to 5, a first transmission assembly 11 and a second transmission assembly 12 disposed at one side of the body 1 and a third transmission assembly 13 and a fourth transmission assembly 14 disposed at the other side of the body 1 are symmetrically distributed along a central axis of the body 1.
As a preferred solution, each of the transmission assemblies further includes: and a one-way clutch 7, wherein the engine 2 is connected to the one-way clutch 7, the engine 2 is connected to the propeller 3 through the one-way clutch 7, and the engine 2 is connected to one of the first synchronous transmission mechanism 6 and the second synchronous transmission mechanism 10 through an implement clutch.
In the technical scheme, the one-way clutch 7 is further included, the engine 2 can drive the propellers 3 to rotate conveniently through the one-way clutch 7, and meanwhile, the four propellers 3 of the four transmission assemblies can synchronously rotate conveniently through the first synchronous transmission mechanism 6 or the second synchronous transmission mechanism 10.
Preferably, the engine 2 is a piston engine 2.
In the technical scheme, the engine 2 is a piston engine 2, and the ducted 4 aircraft can have stronger power and endurance capacity through selection of the piston engine 2.
As a preferred solution, each of the transmission assemblies further includes: the support is connected to the duct 4, the engine 2 is arranged on the support, and the outer cover is arranged on the engine 2.
In the technical scheme, each transmission assembly further comprises a support and a cover, so that the engine 2 is convenient to mount, and meanwhile, sundries can be prevented from entering the engine 2.
As a preferred solution, each of the transmission assemblies further includes: and the slipstream rudder 5 is arranged on the lower end surface of the duct 4.
In the technical scheme, the device further comprises a slipstream rudder 5, so that the heading of the aircraft in the duct 4 can be controlled conveniently.
As a preferred technical solution, the method further comprises: and the steering engine is connected to the slipstream rudder 5.
In the technical problem, the duct 4 aircraft further comprises a steering engine, and the orientation of the slipstream rudder 5 can be changed through the arrangement of the steering engine, so that the heading of the duct 4 aircraft can be changed.
As a preferred technical solution, the method further comprises: the synchronous transmission device comprises a first synchronous transmission mechanism node 8, a second synchronous transmission mechanism node 9 and a connecting rod 15, wherein the first synchronous transmission mechanism node 8 and the second synchronous transmission mechanism node 9 are arranged in the machine body 1, the first synchronous transmission mechanism 6 is connected to the first synchronous transmission mechanism node 8, the second synchronous transmission mechanism 10 is connected to the second synchronous transmission mechanism node 9, one end of the connecting rod 15 is connected to the first synchronous transmission mechanism node 8, and the other end of the connecting rod 15 is connected to the second synchronous transmission mechanism node 9.
In the technical scheme, the four-propeller synchronous driving mechanism further comprises a first synchronous driving mechanism node, a second synchronous driving mechanism node and a connecting rod, the first synchronous driving mechanism 6 can be connected to the second synchronous driving mechanism 10 through the first synchronous driving mechanism node, the second synchronous driving mechanism node and the connecting rod, and four propellers 3 of four driving assemblies can be driven synchronously.
As a preferred solution, the duct 4 is connected to the fuselage 1 by means of quilting beams or frames.
DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION
FIG. 1 is a schematic structural view of a ducted 4 aircraft according to a first embodiment of the present invention; FIG. 2 is a schematic structural view of a ducted 4 aircraft according to a second embodiment of the present invention; FIG. 3 is a schematic structural view of a ducted 4 aircraft in accordance with a third embodiment of the present invention; FIG. 4 is a schematic structural view of a ducted 4 aircraft in accordance with a fourth embodiment of the present invention; FIG. 5 is a schematic structural diagram of a ducted 4 aircraft according to a fifth embodiment of the present invention
As shown in fig. 1 to 5, the ducted 4 aircraft includes: the structure of a certain type ducted 4 aircraft comprises a fuselage 1, four ducts 4, four groups of engines 2, four one-way clutches 7, four groups of slipstream rudders 5, a clutch synchronous transmission mechanism, four propellers 3 and the like. The four ducts 4 are symmetrically arranged, and the ducts 4 and the machine body 1 are fixedly connected by adopting quilting beams, frames or other forms; the engine 2 is directly connected with the one-way clutch 7, the engine 2 adopts a piston engine 2, the one-way clutch 7 is directly connected with the propeller 3, and the whole engine 2 is arranged on a support of the duct 4 and covered by an outer cover; the slipstream rudders 5 are arranged at the lower ends of the ducts 4, and can realize angular deflection by being driven by the steering engine, and the slipstream rudders 5 of the adjacent ducts 4 are symmetrically arranged and are on the same plane relative to the slipstream rudders 5 of the ducts 4; the one-way clutch 7 realizes synchronous rotation through the first synchronous transmission mechanism 6 and the second synchronous transmission mechanism 10, and simultaneously ensures that the adjacent ducts 4 are opposite in rotation direction; the first synchronous transmission mechanism 6, the second synchronous transmission mechanism 10 and the connecting rod are of an H-shaped transmission structure, and the first synchronous transmission mechanism node and the second synchronous transmission mechanism node are arranged inside the machine body 1.
Unmanned aerial vehicle rises, increases through driving system rotational speed and improves thrust and realize, the detail process that the rotational speed increases: the added fast engine 2 drives the four groups of propellers 3 to act through the one-way clutch 7, the first synchronous transmission mechanism 6 and the second synchronous transmission mechanism 10, but the single engine 2 cannot be driven fast due to too large load, the increase of the rotating speed is inhibited, and then the power is provided together through the catch-up of the engine 2 later. Unmanned aerial vehicle descends, reduces through driving system rotational speed and reduces thrust and realize, the detail process that the rotational speed reduces: the speed of the engine 2 is reduced, the speed of the propellers 3 is reduced simultaneously under the action of resistance, and the four propellers 3 are always at the same rotating speed due to the first synchronous transmission mechanism 6 and the second synchronous transmission mechanism 10; if the speed of the propeller 3 is reduced more than the speed of the engine 2, the engine 2 with a slow speed reduction is loaded, but the load is too large, and the single engine 2 cannot bear the load, so that the speed of the reduced speed of the engine 2 is increased, the reduced speed of the other engine 2 is caught up, and finally the four engines 2 bear the load together.
The action control of the unmanned aerial vehicle on advancing, retreating, rotating and left-right moving is realized through different deviation of the slipstream rudder 5, and the action speed is controlled through the deflection angle of the slipstream rudder 5.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art will understand that various changes, modifications and substitutions can be made without departing from the spirit and scope of the invention as defined by the appended claims. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A ducted aircraft, comprising: the device comprises a machine body, four transmission assemblies, a first synchronous transmission mechanism and a second synchronous transmission mechanism;
wherein, four drive assembly do: the transmission mechanism comprises a first transmission assembly, a second transmission assembly, a third transmission assembly and a fourth transmission assembly;
the first transmission assembly and the second transmission assembly are arranged on one side of the machine body, the third transmission assembly and the fourth transmission assembly are arranged on the other side of the machine body, one end of the first synchronous transmission mechanism is connected to the first transmission assembly, the other end of the first synchronous transmission mechanism is connected to the third transmission assembly, one end of the second synchronous transmission mechanism is connected to the second transmission assembly, and the other end of the second synchronous transmission mechanism is connected to the fourth transmission assembly;
wherein the first transmission assembly, the second transmission assembly, the third transmission assembly and the fourth transmission assembly have the same structure, and each transmission assembly comprises: the bypass is connected to the fuselage, the screw propeller is arranged in the bypass, the engine is connected to the screw propeller, and the engine is connected to one of the first synchronous transmission mechanism or the second synchronous transmission mechanism.
2. The ducted aircraft according to claim 1, wherein each of said transmission assemblies further comprises: and the engine is connected to the one-way clutch, the engine is connected to the propeller through the one-way clutch, and the engine is connected to one of the first synchronous transmission mechanism or the second synchronous transmission mechanism through the implement clutch.
3. The ducted aircraft according to claim 1 wherein said engine is a piston engine.
4. The ducted aircraft according to claim 1, wherein each of said transmission assemblies further comprises: the engine comprises a bracket and a housing, wherein the bracket is connected to the duct, the engine is arranged on the bracket, and the housing covers the engine.
5. The ducted aircraft according to claim 1, wherein each of said transmission assemblies further comprises: and the slip flow rudder is arranged on the lower end surface of the duct.
6. The ducted aircraft according to claim 5, further comprising: and the steering engine is connected to the slipstream rudder.
7. The ducted aircraft according to claim 1, further comprising: the synchronous transmission mechanism comprises a first synchronous transmission mechanism node, a second synchronous transmission mechanism node and a connecting rod, wherein the first synchronous transmission mechanism node and the second synchronous transmission mechanism node are arranged in the machine body, the first synchronous transmission mechanism is connected to the first synchronous transmission mechanism node, the second synchronous transmission mechanism is connected to the second synchronous transmission mechanism node, one end of the connecting rod is connected to the first synchronous transmission mechanism node, and the other end of the connecting rod is connected to the second synchronous transmission mechanism node.
8. The ducted aircraft according to claim 1, characterized in that said duct is connected to said fuselage by means of quilting beams or frames.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110621876.8A CN113401350A (en) | 2021-06-04 | 2021-06-04 | Ducted aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110621876.8A CN113401350A (en) | 2021-06-04 | 2021-06-04 | Ducted aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN113401350A true CN113401350A (en) | 2021-09-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110621876.8A Pending CN113401350A (en) | 2021-06-04 | 2021-06-04 | Ducted aircraft |
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| CN (1) | CN113401350A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113911377A (en) * | 2021-11-12 | 2022-01-11 | 北京航空航天大学 | Power transmission device of oil-driven ducted aircraft |
| CN114455059A (en) * | 2021-12-27 | 2022-05-10 | 浙江云途飞行器技术有限公司 | Individual soldier aircraft |
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| WO2015117509A1 (en) * | 2014-02-08 | 2015-08-13 | 杨华东 | Variable-pitch flight unit |
| CN104859851A (en) * | 2015-04-27 | 2015-08-26 | 刘朝阳 | Multi-rotor aircraft driven by duct lift fans with diversion helms |
| CN205554616U (en) * | 2016-03-31 | 2016-09-07 | 广东大冶摩托车技术有限公司 | Four rotor crafts of driving feather of fuel |
| CN106976551A (en) * | 2017-03-17 | 2017-07-25 | 沈阳无距科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN107757904A (en) * | 2017-11-17 | 2018-03-06 | 北京航景创新科技有限公司 | A kind of dynamic rotor wing unmanned aerial vehicle of displacement four of oil |
| CN112339984A (en) * | 2020-11-18 | 2021-02-09 | 武汉纺织大学 | Variable-pitch four-duct fan aircraft with foldable aircraft body |
| CN215475777U (en) * | 2021-06-04 | 2022-01-11 | 四川垚磊科技有限公司 | Ducted aircraft |
-
2021
- 2021-06-04 CN CN202110621876.8A patent/CN113401350A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015117509A1 (en) * | 2014-02-08 | 2015-08-13 | 杨华东 | Variable-pitch flight unit |
| CN104859851A (en) * | 2015-04-27 | 2015-08-26 | 刘朝阳 | Multi-rotor aircraft driven by duct lift fans with diversion helms |
| CN205554616U (en) * | 2016-03-31 | 2016-09-07 | 广东大冶摩托车技术有限公司 | Four rotor crafts of driving feather of fuel |
| CN106976551A (en) * | 2017-03-17 | 2017-07-25 | 沈阳无距科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN107757904A (en) * | 2017-11-17 | 2018-03-06 | 北京航景创新科技有限公司 | A kind of dynamic rotor wing unmanned aerial vehicle of displacement four of oil |
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| CN215475777U (en) * | 2021-06-04 | 2022-01-11 | 四川垚磊科技有限公司 | Ducted aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113911377A (en) * | 2021-11-12 | 2022-01-11 | 北京航空航天大学 | Power transmission device of oil-driven ducted aircraft |
| CN114455059A (en) * | 2021-12-27 | 2022-05-10 | 浙江云途飞行器技术有限公司 | Individual soldier aircraft |
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