CN109866932A - Propeller component and aircraft - Google Patents
Propeller component and aircraft Download PDFInfo
- Publication number
- CN109866932A CN109866932A CN201910321505.0A CN201910321505A CN109866932A CN 109866932 A CN109866932 A CN 109866932A CN 201910321505 A CN201910321505 A CN 201910321505A CN 109866932 A CN109866932 A CN 109866932A
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- propeller
- driving shaft
- seat
- transmission shaft
- bearing
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Abstract
The present invention provides a kind of propeller component, including the first transmission shaft and second driving shaft, the first propeller seat, the second propeller seat and motor group；First driving sleeve is set to the second driving shaft and is arranged coaxially, first transmission shaft rotates independently of each other with the second driving shaft, the first propeller seat is folded with the second propeller seat interval to be set and in oppositely arranged, the propeller component further includes the supporting element being fixedly connected with the first propeller seat, the supporting element is sheathed on the second driving shaft, the supporting element includes the body part for being fixed on the first propeller seat and surrounding a hollow region, the body part is equipped with engraved structure, the engraved structure is connected to the hollow region, the second driving shaft passes through the hollow region and connect with the second propeller seat.Compared with the relevant technologies, propeller component provided by the invention and aircraft energy consumption is small, cruising ability is strong, and flight efficiency is high.
Description
Technical field
The present invention relates to aircraft field, and especially one kind is related to propeller component and aircraft.
Background technique
With the development of society, the application field of unmanned vehicle is constantly expanded, either industry aircraft is still
Consumption aircraft all obtains significant progress, especially multiple propeller unmanned vehicle and fixed-wing unmanned vehicle is representative
Small miniature unmanned vehicle, all start to be widely applied in each application field, aircraft of spraying insecticide, aerial photography aircraft,
Explorer vehicle etc. also starts to be widely applied now.With the requirement to aircraft cruising ability, while there is propeller and consolidate
The compound rotor aircraft for determining the wing starts to rise.
The propeller component of the relevant technologies includes the first transmission shaft and second driving shaft, is arranged and is fixed on first transmission
First propeller seat of axis is arranged the second propeller seat for being fixed on the second driving shaft and respectively drives first biography
The motor group of moving axis and second driving shaft rotation；First driving sleeve is set to the second driving shaft and is in coaxially to set
It sets, first transmission shaft rotates independently of each other with the second driving shaft, the first propeller seat and second spiral
Paddle seat interval is folded to be set and in oppositely arranged.Not occur when guaranteeing that the first propeller seat and the second propeller seat rotate
Collision, the first propeller seat and the second propeller seat needs are spaced a distance, at this point, first propeller
Second driving shaft between seat and the second propeller seat is in naked state, in use, with aircraft altitude
Promotion, the second driving shaft be easy air pressure or wind-force effect under formed inclination, to be formed to first transmission shaft
It squeezes, causes energy loss, influence transmission efficiency, be unfavorable for the promotion of flying quality.
Therefore, it is necessary to provide one kind new propeller component and aircraft to solve the above problems.
Summary of the invention
A kind of the technical problem to be solved by the invention is to provide energy consumptions small, the good propeller component of flying quality and fly
Row device.
To solve the above problems, the propeller component includes the first transmission the present invention provides a kind of propeller component
Axis and second driving shaft are arranged and are fixed on the first propeller seat of first transmission shaft, are arranged and are fixed on second transmission
Second propeller seat of axis and the motor group for respectively driving first transmission shaft and second driving shaft rotation；Described
One driving sleeve is set to the second driving shaft and is arranged coaxially, and first transmission shaft and the second driving shaft are mutually only
Vertical rotation, the first propeller seat is folded with the second propeller seat interval to be set and in oppositely arranged, the propeller component
It further include the supporting element being fixedly connected with the first propeller seat, the supporting element is sheathed on the second driving shaft, described
Supporting element includes the body part for being fixed on the first propeller seat and surrounding a hollow region, and the body part is equipped with hollow out
Structure, the engraved structure are connected to the hollow region, and the second driving shaft passes through the hollow region and described second
The connection of propeller seat.
Preferably, first bearing, first transmission shaft are set between first transmission shaft and the second driving shaft
It is arranged and connect by first bearing realization with the second driving shaft, the first bearing includes at least two and mutual
Every setting.
Preferably, the motor group includes being sheathed on the second driving shaft and relative to opposite turn of the second driving shaft
Dynamic motor cabinet and turn along the axis direction group of the second driving shaft assigned in the first motor of the motor cabinet opposite end
Son and the second rotor, the first motor rotor, which is arranged, to be fixed on first transmission shaft and drives first transmission shaft
Rotation, second rotor, which is arranged, to be fixed on the second driving shaft and the second driving shaft is driven to rotate.
Preferably, first transmission shaft is an integral molding structure with the first motor rotor.
Preferably, second bearing is set between the motor cabinet and the second driving shaft, the motor cabinet and described the
Two transmission shafts are arranged connection by second bearing realization, and the second bearing includes at least two and is spaced apart from each other setting.
Preferably, the first propeller seat includes bottom plate, the top plate being arranged with the bottom plate parallel interval and connection
The connecting column of the bottom plate and the top plate, propeller are located between the bottom plate and the top plate.
Preferably, the bottom plate is equipped with perforative first through hole, and the top plate is equipped with perforative second through-hole and recess
Mounting groove, the mounting groove are connected to second through-hole, and the mounting groove, second through-hole, the first through hole
Center line is located along the same line, and the supporting element is fixedly installed in the mounting groove and fixes with the first propeller seat
Connection.
Preferably, the supporting element further includes extension and 3rd bearing, and the extension is set to the body part and leans on
One end of the nearly second propeller seat, and the extension is extended to form from the body part to the hollow region direction,
The 3rd bearing is contained in the hollow region and is carried on the extension, and the 3rd bearing is sheathed on described second
On transmission shaft.
Preferably, the quantity of the engraved structure is multiple, and multiple engraved structures are spaced apart from each other.
The present invention also provides a kind of aircraft, including fuselage, the cantilever extended by the rear end of the fuselage and are fixed on institute
State cantilever far from described fuselage one end such as above-mentioned propeller component, the first propeller seat and second propeller
Seat is in horizontally disposed.
Compared with the relevant technologies, in propeller component of the invention and aircraft, set the propeller component to be in
Coaxial twopiece drive shaft and double-propeller structure, and make the first propeller seat and the second propeller seat interval it is folded set and
In oppositely arranged, which makes the first propeller seat and the second propeller seat that can control revolving speed and steering respectively,
Revolving speed and the steering that the first propeller seat and the second propeller seat are adjusted according to different mission phases, form different angles
Degree and the auxiliary power of dynamics avoid aircraft always so that the aircraft is dynamically adapted required auxiliary power
High-power output and keep power rapidly depleting, realize energy conservation to improve cruising ability；Meanwhile it is solid on the first propeller seat
Determine supporting element, the supporting element is sheathed on the second driving shaft, and the second driving shaft passes through the supporting element and described the
The connection of two propeller seats, can limit the displacement of the second driving shaft, avoid occurring in the second driving shaft rotary course
Positional shift ensure that the rotational independence of the first propeller seat and the second propeller seat, improve flying quality；
Furthermore the setting of the engraved structure can reduce the contact area of the supporting element and air, reduces and rises resistance, meanwhile,
The engraved structure can also make the air of the supporting element two sides form good convection current, avoid air-flow to the supporting element shape
At collision, the offset of the second driving shaft is caused.
Detailed description of the invention
To describe the technical solutions in the embodiments of the present invention more clearly, make required in being described below to embodiment
Attached drawing is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the invention, for
For those of ordinary skill in the art, without creative efforts, it can also be obtained according to these attached drawings other
Attached drawing, in which:
Fig. 1 is the schematic perspective view of propeller component provided by the invention；
Fig. 2 is the decomposition texture schematic diagram of propeller component shown in FIG. 1；
Fig. 3 is the cross-sectional view of propeller component shown in FIG. 1；
Fig. 4 is the cross-sectional view that the second propeller shown in painting 2 is done；
Fig. 5 is the schematic perspective view of supporting element shown in Fig. 2；
Fig. 6 is the schematic perspective view of aircraft provided by the invention.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that the described embodiments are merely a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts all other
Embodiment shall fall within the protection scope of the present invention.
Please refer to Fig. 1-5, the present invention provides a kind of propeller component 100, and the screw assembly 100 includes the first biography
Moving axis 1, second driving shaft 2, the first propeller seat 3, the second propeller seat 4, motor group 5, first bearing 6, second bearing 7 and branch
Support member 8.
First transmission shaft 1 is sheathed on the second driving shaft 2 and is arranged coaxially, first transmission shaft 1 and institute
Second driving shaft 2 is stated to rotate independently of each other.Specifically, in the present embodiment, first transmission shaft 1 and second transmission
First bearing 6 is set between axis 2, and first transmission shaft 1, which is realized with the second driving shaft 2 by the first bearing 6, to be covered
If connection, to realize mutually indepedent rotation, i.e., the two can be achieved to relatively rotate.Preferably, the fulcrum to realize relative rotation
Balance, the first bearing 6 setting include at least two, and in present embodiment, the first bearing 6 is arranged two and each other
Every setting.Two first bearings 6 are rotated for first transmission shaft 1 with second driving shaft 2.
The first propeller seat 3, which is arranged, is fixed on first transmission shaft 1；The second propeller seat 4 is arranged fixation
In the second driving shaft 2, the first propeller seat 3 and the second propeller seat 4 are used to installation propeller, and described the
One transmission shaft 1 and the second driving shaft 2 respectively drive the spiral shell on the first propeller seat 3 and the second propeller seat 4
Revolve paddle rotation.
In present embodiment, the first propeller seat 3 is folded with the second propeller seat 4 interval to be set and is in reversely to set
It sets.The structure makes the first propeller seat 3 and the second propeller seat 4 that can control revolving speed and steering respectively, according to not
Adjust revolving speed and the steering of the first propeller seat 3 and the second propeller seat 4 with mission phase, formed different angle and
The auxiliary power of dynamics avoids high-power output always and keeps power rapidly depleting, realizes energy conservation to improve cruising ability.
The first propeller seat 3 include bottom plate 31, with 31 parallel interval of bottom plate be arranged top plate 32 and connect
The connecting column 33 of the bottom plate 31 and the top plate 32.It is understood that the connecting column 33 is corresponding across described when installation
Mounting hole on propeller, the bottom plate 31 and the top plate 32 are respectively arranged at the two sides of the propeller mounting base, and right
The propeller should be clamped, realizes the fixation of the propeller.
The bottom plate 31, which is arranged, is fixed on first transmission shaft 1, and the bottom plate 31, which is equipped with, runs through 31 liang of the bottom plate
The first through hole 311 of side.
The top plate 32 is equipped with the mounting groove 323 of the second through-hole 321 and recess through 32 two sides of top plate, described
Mounting groove 323 is connected to second through-hole 321, and the mounting groove 323, second through-hole 321 and the first through hole
311 center line is located along the same line, and further, the projection in the first through hole 321 to 31 direction of bottom plate is complete
The mounting groove 323 is fallen into the drop shadow spread in 31 direction of bottom plate, i.e., the sectional area of the described mounting groove 323 is greater than described
The sectional area of first through hole 321.
The first through hole 311 and 321 face of the second through-hole setting, the second driving shaft 2 sequentially pass through described
First through hole 311, second through-hole 321 and the mounting groove 323 extend to the second propeller seat 4.Further, institute
State diameter of the diameter greater than the second driving shaft 2 of first through hole 311 and second through-hole 321, the second driving shaft 2
Center line and the center line of the first through hole 311, second through-hole 321 be located along the same line.
The motor group 5 respectively drives first transmission shaft 1 and the second driving shaft 2 rotates comprising motor cabinet
51, first motor rotor 52 and the second rotor 53.
The motor cabinet 51 is sheathed on the second driving shaft 2 and relative to the second driving shaft 2 relative rotation.
In present embodiment, second bearing 7, the motor are set between the motor cabinet 51 and the second driving shaft 2
Seat 51 is arranged by the second bearing 7 realization with the second driving shaft 2 and is connect.It is rotated independently of each other to realize, i.e., two
Person can realize relative rotation.
To realize the fulcrum relatively rotated balance, the setting of second bearing 7 includes at least two, in present embodiment,
The second bearing 7 is arranged two and is spaced apart from each other setting.Two second bearings 7 are for realizing second rotor
53 rotate with second driving shaft 2.
Axis direction of the first motor rotor 52 with second rotor 53 along the second driving shaft 2 assembles
In the opposite end of the motor cabinet 51.
It is fixed on first transmission shaft 1 specifically, the first motor rotor 52 is arranged and drives first transmission
Axis 1 rotates, and first transmission shaft 1 then drives the first propeller seat 3 to rotate.More preferably, in present embodiment, described
One transmission shaft 1 is an integral molding structure with the first motor rotor 52, to save production cost.
Second rotor 53, which is arranged, to be fixed on the second driving shaft 2 and the second driving shaft 2 is driven to rotate,
The second driving shaft 2 then drives the second propeller seat 4 to rotate.
Above structure is that is, two motors are shared a motor cabinet 51 by the motor group 5, that is, will
The first propeller seat 3 and the second propeller seat 4 are assemblied on the motor cabinet 51, and one side structure is simple,
Volume is smaller, saves production cost, on the other hand mitigates the weight of the propeller component, more energy efficient.
The supporting element 8 is fixedly installed in the first propeller seat 3, and is sheathed on outside the second driving shaft 2
Circumference, specifically, supporting element 8 includes body part 81, extension 82 and 3rd bearing 83, the extension 82 and the body part
81 are integrally formed.Further, the body part 81 is fixedly installed in the mounting groove 323, and the body part 81 and institute
Stating between the first propeller seat 3 can be connected by bolt or other modes, and it is firm to connect, and the supporting element 8 with it is described
Separation can be dismantled between first propeller seat 3, for ease of maintenaince.
The body part 81 is cylindrical, surrounds a hollow region 810, and the second driving shaft 2 passes through described hollow
Extend in region 810 to 81 both ends of body part.The extension 82 is set to the body part 81 close to the second propeller
One end of seat 4, and the extension 82 is extended to form from the body part 81 to 810 direction of hollow region.
Further, engraved structure 811, the engraved structure 811 and the hollow area are additionally provided on the body part 81
Domain 810 be connected to, it is preferred that the quantity of the engraved structure 811 be it is multiple, the engraved structure 811 is spaced apart from each other setting,
Embodiment, the quantity of the engraved structure 811 are eight, and eight engraved structures are symmetrically disposed on the supporting element 8
Two sides can reduce the contact area of the supporting element 8 and air, reduces and rises resistance, meanwhile, the engraved structure 811 is also
The air of 8 two sides of supporting element can be made to form good convection current, avoid air-flow from forming the supporting element 8 and collide, cause
The offset of the second driving shaft 2.
The 3rd bearing 83 is contained in the hollow region 810, and is carried on the extension 82, it is possible to understand that
, the 3rd bearing 83 is sheathed on the second driving shaft 2.The 3rd bearing 83 abuts the body part 81, described
Body part 81 is fixedly connected with the first propeller seat 3, limits the offset of the second driving shaft 2, so that described second
The central axis of the center line of transmission shaft 2 and first transmission shaft 1 is always positioned on straight line, can be effectively prevented described the
Two transmission shafts 2, which shift, squeezes first transmission shaft 1, maintains first transmission shaft 1 and the second driving shaft 2 revolves
The independence turned, ensure that transmission efficiency, improves flying quality.Also, the setting of the supporting element 8 also enhances described
The intensity of two transmission shafts 2, extends service life.
It is understood that the length of the supporting element 8 can be according to the first propeller seat 3 and second spiral
The spacing of paddle seat 4 is adjusted, and the present invention is without limitation.
It is the schematic perspective view of aircraft of the present invention incorporated by reference to ginseng Fig. 6.The present invention also provides a kind of aircraft 200,
Including fuselage 10, the cantilever 20 extended by the rear end of the fuselage 10, the separate fuselage 10 1 for being fixed on the cantilever 20
The propeller component 100 at end, is each extended over by the fixed-wing 30 fixed-wing 30 that is extended by 10 two sides of fuselage
Third propeller 40 and the flight control system (not shown) for being fixed on the fuselage 10.The third propeller 40 is perpendicular to level
Face setting, more preferably, the third propeller 40 are tilted propeller.
The first propeller seat 3 and the second propeller seat 4 are in horizontally disposed.It is described when taking off vertically or landing
The setting of first propeller seat 3 and the second propeller seat 4 can provide the power of vertical ascent or decline.
The motor group 5 is electrically connected with the flight control system, and the flight control system is controlled and adjusted by the motor group 5
The revolving speed and steering of the first propeller seat 3 and the second propeller seat 5.Specifically, for example, the institute of the motor group 5
It states first motor rotor 52 and second rotor 53 is electrically connected with the flight control system respectively, the flight control system difference
Revolving speed and the steering of the first motor rotor 52 and second rotor 53 are controlled and adjusted, to realize first spiral shell
Revolving speed and the steering of paddle seat 3 and the second propeller seat 5 are revolved, to realize the power of output different directions and different capacity.
In present embodiment, the cantilever 20 is hinged and connected with the fuselage 10, and the cantilever 20 is relative to the fuselage
10 rotating range is with the fuselage 10 parallel to vertical with the fuselage 10, i.e., the described cantilever 20 relative to fuselage of stating can
Rotation is realized, so that the first propeller seat 3 and the second propeller seat 4 are adjusted by angle and realize the dynamic of different directions
Power output.
Compared with the relevant technologies, in propeller component of the invention and aircraft, set the propeller component to be in
Coaxial twopiece drive shaft and double-propeller structure, and make the first propeller seat and the second propeller seat interval it is folded set and
In oppositely arranged, which makes the first propeller seat and the second propeller seat that can control revolving speed and steering respectively,
Revolving speed and the steering that the first propeller seat and the second propeller seat are adjusted according to different mission phases, form different angles
Degree and the auxiliary power of dynamics avoid aircraft always so that the aircraft is dynamically adapted required auxiliary power
High-power output and keep power rapidly depleting, realize energy conservation to improve cruising ability；Meanwhile it is solid on the first propeller seat
Determine supporting element, the supporting element is sheathed on the second driving shaft, and the second driving shaft passes through the supporting element and described the
The connection of two propeller seats, can limit the displacement of the second driving shaft, avoid occurring in the second driving shaft rotary course
Positional shift ensure that the rotational independence of the first propeller seat and the second propeller seat, improve flying quality；
Furthermore the setting of the engraved structure can reduce the contact area of the supporting element and air, reduces and rises resistance, meanwhile,
The engraved structure can also make the air of the supporting element two sides form good convection current, avoid air-flow to the supporting element shape
At collision, the offset of the second driving shaft is caused.
The above description is only an embodiment of the present invention, is not intended to limit the scope of the invention, all to utilize this hair
Equivalent structure or equivalent flow shift made by bright specification and accompanying drawing content is applied directly or indirectly in other relevant skills
Art field, is included within the scope of the present invention.
Claims (10)
1. a kind of propeller component, the propeller component include the first transmission shaft and second driving shaft, be arranged be fixed on it is described
First propeller seat of the first transmission shaft is arranged the second propeller seat for being fixed on the second driving shaft and respectively drives institute
State the motor group of the first transmission shaft and second driving shaft rotation；First driving sleeve be set to the second driving shaft and
Be arranged coaxially, first transmission shaft rotates independently of each other with the second driving shaft, the first propeller seat with it is described
Second propeller seat interval is folded to be set and in oppositely arranged, which is characterized in that the propeller component further includes and first spiral shell
The supporting element that rotation paddle seat is fixedly connected, the supporting element are sheathed on the second driving shaft, and the supporting element includes being fixed on institute
It states the first propeller seat and surrounds the body part of a hollow region, the body part is equipped with engraved structure, the engraved structure
It is connected to the hollow region, the second driving shaft passes through the hollow region and connect with the second propeller seat.
2. propeller component according to claim 1, which is characterized in that first transmission shaft and the second driving shaft
Between first bearing is set, first transmission shaft is arranged by first bearing realization with the second driving shaft and is connect,
The first bearing includes at least two and is spaced apart from each other setting.
3. propeller component according to claim 1, which is characterized in that the motor group includes being sheathed on described second to pass
It moving axis and the motor cabinet relatively rotated relative to the second driving shaft and assembles along the axis direction of the second driving shaft
In the first motor rotor and the second rotor of the motor cabinet opposite end, the first motor rotor, which is arranged, is fixed on institute
It states the first transmission shaft and first transmission shaft is driven to rotate, second rotor, which is arranged, is fixed on the second driving shaft
And the second driving shaft is driven to rotate.
4. propeller component according to claim 3, which is characterized in that first transmission shaft and the first motor turn
Son is an integral molding structure.
5. propeller component according to claim 4, which is characterized in that between the motor cabinet and the second driving shaft
Second bearing is set, the motor cabinet is arranged by second bearing realization with the second driving shaft and is connect, and described second
Bearing includes at least two and is spaced apart from each other setting.
6. propeller component according to claim 1, which is characterized in that the first propeller seat includes bottom plate and institute
It states the top plate of bottom plate parallel interval setting and the connecting column of the connection bottom plate and the top plate, propeller is located in the bottom
Between plate and the top plate.
7. propeller component according to claim 6, which is characterized in that the bottom plate is equipped with perforative first through hole, institute
Mounting groove of the top plate equipped with perforative second through-hole and recess is stated, the mounting groove is connected to second through-hole, and the peace
Tankage, second through-hole, the first through hole center line be located along the same line, the supporting element is fixedly installed in described
It is fixedly connected in mounting groove and with the first propeller seat.
8. propeller component according to claim 7, which is characterized in that the supporting element further includes extension and third axis
It holds, the extension is set to the body part close to one end of the second propeller seat, and the extension is by described
Body portion is extended to form to the hollow region direction, and the 3rd bearing is contained in the hollow region and is carried on the extension
Portion, and the 3rd bearing is sheathed on the second driving shaft.
9. propeller component according to claim 1, which is characterized in that the quantity of the engraved structure is multiple, Duo Gesuo
Engraved structure is stated to be spaced apart from each other.
10. a kind of aircraft, which is characterized in that including fuselage, the cantilever extended by the rear end of the fuselage and be fixed on described
The propeller component as claimed in any one of claims 1 to 9 wherein far from described fuselage one end of cantilever, first propeller
Seat and the second propeller seat are in horizontally disposed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910321505.0A CN109866932A (en) | 2019-04-19 | 2019-04-19 | Propeller component and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910321505.0A CN109866932A (en) | 2019-04-19 | 2019-04-19 | Propeller component and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109866932A true CN109866932A (en) | 2019-06-11 |
Family
ID=66922907
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910321505.0A Pending CN109866932A (en) | 2019-04-19 | 2019-04-19 | Propeller component and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109866932A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020086595A1 (en) * | 2000-01-20 | 2002-07-04 | Jordan W. Bishop | Transmission for driving counter-rotating propellers, lubrication system, and associated methods |
| CA2546207A1 (en) * | 2006-05-08 | 2007-11-08 | Guangming Minc He | Flying vehicle |
| US20150125299A1 (en) * | 2013-11-05 | 2015-05-07 | Sikorsky Aircraft Corporation | Counter-rotating rotor system with stationary standpipe |
| WO2016053825A1 (en) * | 2014-10-01 | 2016-04-07 | Sikorsky Aircraft Corporation | Rotorcraft systems to reduce pilot workload |
| US20160122012A1 (en) * | 2014-11-04 | 2016-05-05 | Lg Electronics Inc. | Drone |
| US20170190415A1 (en) * | 2014-05-29 | 2017-07-06 | Sikorsky Aircraft Corporation | Transmission for coaxial multi-rotor system |
| US20180044029A1 (en) * | 2016-08-10 | 2018-02-15 | Koegler Patrick C | Coaxial aligned electric motor group for propelling an unmanned aerial system |
| CN207712288U (en) * | 2017-12-28 | 2018-08-10 | 深圳市边锋智驱科技有限公司 | A kind of folding propeller paddle folder with positioning column |
| CN208377052U (en) * | 2018-06-12 | 2019-01-15 | 翟占超 | Propeller component and aircraft |
| CN209852594U (en) * | 2019-04-19 | 2019-12-27 | 深圳市边锋智驱科技有限公司 | Propeller assembly and aircraft |
-
2019
- 2019-04-19 CN CN201910321505.0A patent/CN109866932A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020086595A1 (en) * | 2000-01-20 | 2002-07-04 | Jordan W. Bishop | Transmission for driving counter-rotating propellers, lubrication system, and associated methods |
| CA2546207A1 (en) * | 2006-05-08 | 2007-11-08 | Guangming Minc He | Flying vehicle |
| US20150125299A1 (en) * | 2013-11-05 | 2015-05-07 | Sikorsky Aircraft Corporation | Counter-rotating rotor system with stationary standpipe |
| US20170190415A1 (en) * | 2014-05-29 | 2017-07-06 | Sikorsky Aircraft Corporation | Transmission for coaxial multi-rotor system |
| WO2016053825A1 (en) * | 2014-10-01 | 2016-04-07 | Sikorsky Aircraft Corporation | Rotorcraft systems to reduce pilot workload |
| US20160122012A1 (en) * | 2014-11-04 | 2016-05-05 | Lg Electronics Inc. | Drone |
| US20180044029A1 (en) * | 2016-08-10 | 2018-02-15 | Koegler Patrick C | Coaxial aligned electric motor group for propelling an unmanned aerial system |
| CN207712288U (en) * | 2017-12-28 | 2018-08-10 | 深圳市边锋智驱科技有限公司 | A kind of folding propeller paddle folder with positioning column |
| CN208377052U (en) * | 2018-06-12 | 2019-01-15 | 翟占超 | Propeller component and aircraft |
| CN209852594U (en) * | 2019-04-19 | 2019-12-27 | 深圳市边锋智驱科技有限公司 | Propeller assembly and aircraft |
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