CN107795669A - Coaxial aircraft transmission device and aircraft - Google Patents
Coaxial aircraft transmission device and aircraft Download PDFInfo
- Publication number
- CN107795669A CN107795669A CN201711277466.6A CN201711277466A CN107795669A CN 107795669 A CN107795669 A CN 107795669A CN 201711277466 A CN201711277466 A CN 201711277466A CN 107795669 A CN107795669 A CN 107795669A
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- CN
- China
- Prior art keywords
- axle
- jackshaft
- transmission device
- coaxial
- connecting cylinder
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/02—Gearboxes; Mounting gearing therein
- F16H57/023—Mounting or installation of gears or shafts in the gearboxes, e.g. methods or means for assembly
-
- 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
- B64C27/10—Helicopters with two or more rotors arranged coaxially
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Retarders (AREA)
Abstract
A kind of coaxial aircraft transmission device and aircraft, belong to drive mechanism technical field.The coaxial aircraft transmission device includes the first jackshaft, the second jackshaft and coaxially arranged first axle and the second axle, first axle and the first jackshaft are connected by gear train, first jackshaft and the second jackshaft are connected by gear train, second jackshaft and the second axle are connected by gear train, and the first jackshaft and the second jackshaft are arranged symmetrically in the both sides of first axle.Coaxial aircraft transmission device provided by the invention has the advantages of simple and compact for structure, stability is strong.Present invention also offers a kind of aircraft for including above-mentioned coaxial aircraft transmission device.
Description
Technical field
The present invention relates to drive mechanism technical field, in particular to a kind of coaxial aircraft transmission device and flight
Device.
Background technology
Coaxial aircraft is also known as coaxial dual-rotor helicopter, and it refers to that aircraft has around same theory axis a positive and a negative
The two secondary rotor up and down of rotation, coaxial aircraft, which has, turns to two opposite width rotors, and moment of torsion is in course caused by two secondary rotors
Mutually balanced under constant state of flight, directional control always can be realized away from differential caused uneven moment of torsion by upper and lower rotor,
It has compared to single rotor craft does not need that tail slurry counter balance torque, lift be big, rotor radius is small under same load, pitch rotation
The advantages that inertia is small, therefore be subject to the people's attention and widely study, but coaxial aircraft also have it is complicated, on
During lower rotor running the defects of damaged in collision easy due to asymmetric lift, which also limits its application.
Therefore, it is necessary to a kind of compact-sized reliable, stability is strong and the coaxial transmission device of stable drive.
The content of the invention
It is an object of the invention to provide a kind of coaxial aircraft transmission device, and it has simple and compact for structure, stability
The advantages of strong.
Another object of the present invention is to provide a kind of aircraft, it has, and structural stability is strong, big excellent of rotation lift
Point.
What embodiments of the invention were realized in：
A kind of coaxial aircraft transmission device, it includes the first jackshaft, the second jackshaft and coaxially arranged first axle
With the second axle, first axle and the first jackshaft are connected by gear train, and the first jackshaft and the second jackshaft pass through gear
Group drive connection, the second jackshaft and the second axle are connected by gear train, the first jackshaft and the second middle axial symmetry cloth
Put in the both sides of first axle.
In preferred embodiments of the present invention, in addition to connecting cylinder and the support base provided with ball holding tank, first axle it is remote
One end of second axle is rotatable in connecting cylinder, and the one end of connecting cylinder away from the second axle 130 is provided with to rotate and accommodated located at ball
Bulb in groove.
In preferred embodiments of the present invention, in addition to the 3rd axle being connected with first axle by gear train, the 3rd
One end of axle is rotatable in connecting cylinder.
In preferred embodiments of the present invention, above-mentioned connecting cylinder is connected with least one for driving its relative support seat to turn
Dynamic runner assembly.
In preferred embodiments of the present invention, above-mentioned runner assembly includes electric pushrod and connecting rod, the both ends difference of connecting rod
It is hinged with electric pushrod and connecting cylinder.
In preferred embodiments of the present invention, be arranged with telophragma on above-mentioned connecting cylinder, each runner assembly with centre
Disk connects.
In preferred embodiments of the present invention, in addition to the first protection cylinder, connecting cylinder, support base and runner assembly are respectively positioned on
In first protection cylinder.
In preferred embodiments of the present invention, in addition to the second protection cylinder, the first jackshaft, the second jackshaft, first axle
It is respectively positioned on the second axle in the second protection cylinder.
In preferred embodiments of the present invention, above-mentioned first axle is connected with the drive component for driving it to rotate, driving
Component includes motor, and the output shaft of motor is connected by conical gear group and first axle.
Present invention also offers a kind of aircraft, and it includes at least one above-mentioned coaxial aircraft transmission device.
The beneficial effect of the embodiment of the present invention is：Coaxial aircraft transmission device provided in an embodiment of the present invention includes first
Jackshaft, the second jackshaft and coaxially arranged first axle and the second axle, first axle and the first jackshaft are driven by gear train
Connection, the first jackshaft and the second jackshaft are connected by gear train, and the second jackshaft and the second axle are passed by gear train
Dynamic connection, the first jackshaft and the second jackshaft are arranged symmetrically in the both sides of first axle.Coaxial aircraft provided by the invention passes
Dynamic device has the advantages of simple and compact for structure, stability is strong.Passed present invention also offers one kind comprising above-mentioned coaxial aircraft
The aircraft of dynamic device, it has, and structural stability is strong, rotates the advantages of lift is big.
Brief description of the drawings
In order to illustrate the technical solution of the embodiments of the present invention more clearly, below by embodiment it is required use it is attached
Figure is briefly described, it will be appreciated that the following drawings illustrate only certain embodiments of the present invention, therefore be not construed as pair
The restriction of scope, for those of ordinary skill in the art, on the premise of not paying creative work, can also be according to this
A little accompanying drawings obtain other related accompanying drawings.
Fig. 1 is the sectional view for the coaxial aircraft transmission device that the embodiment of the present invention 1 provides；
Fig. 2 is the sectional view for the coaxial aircraft transmission device that the embodiment of the present invention 2 provides；
Fig. 3 is the structural representation for the aircraft that the embodiment of the present invention 3 provides；
Fig. 4 is the sectional view of coaxial aircraft transmission device in the embodiment of the present invention 3.
In figure：001- coaxial aircraft transmission devices；002- coaxial aircraft transmission devices；003- coaxial aircrafts are driven
Device；The jackshafts of 100- first；101- first gears；102- second gears；The gears of 103- the 3rd；The gears of 104- the 4th；105-
5th gear；The gears of 106- the 6th；The gears of 107- the 7th；108- eighth gears；The jackshafts of 110- second；120- first axles；
The axles of 130- second；140- connecting cylinders；141- bulbs；150- support bases；151- ball holding tanks；160- telophragmas；170- is electronic to be pushed away
Bar；171- connecting rods；180- motors；The conical gears of 181- first；The conical gears of 182- second；190- first protects cylinder；
200- second protects cylinder；The axles of 210- the 3rd.
Embodiment
To make the purpose, technical scheme and advantage of the embodiment of the present invention clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
Part of the embodiment of the present invention, rather than whole embodiments.The present invention implementation being generally described and illustrated herein in the accompanying drawings
The component of example can be configured to arrange and design with a variety of.
Therefore, below the detailed description of the embodiments of the invention to providing in the accompanying drawings be not intended to limit it is claimed
The scope of the present invention, but be merely representative of the present invention selected embodiment.It is common based on the embodiment in the present invention, this area
The every other embodiment that technical staff is obtained under the premise of creative work is not made, belong to the model that the present invention protects
Enclose.
It should be noted that：Similar label and letter represents similar terms in following accompanying drawing, therefore, once a certain Xiang Yi
It is defined, then it further need not be defined and explained in subsequent accompanying drawing in individual accompanying drawing.
In the description of the invention, it is necessary to explanation, term " " center ", " on ", " under ", "left", "right", " vertical ",
The orientation or position relationship of the instruction such as " level ", " interior ", " outer " be based on orientation shown in the drawings or position relationship, or should
Invention product using when the orientation usually put or position relationship, be for only for ease of the description present invention and simplify description, without
It is instruction or implies that signified device or element there must be specific orientation, with specific azimuth configuration and operation, therefore not
It is understood that as limitation of the present invention.In addition, term " first ", " second ", " the 3rd " etc. are only used for distinguishing description, and can not manage
Solve to indicate or implying relative importance.
In addition, the term such as term " level ", " vertical ", " pendency " is not offered as requiring part abswolute level or pendency, and
It is to be slightly tilted.Such as " level " only refers to that its direction is more horizontal with respect to for " vertical ", is not to represent the structure
Must be fully horizontal, but can be slightly tilted.
In the description of the invention, it is also necessary to explanation, unless otherwise clearly defined and limited, term " setting ",
" installation ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or one
Connect body；Can be mechanical connection or electrical connection；Can be joined directly together, can also be indirect by intermediary
It is connected, can is the connection of two element internals.For the ordinary skill in the art, on being understood with concrete condition
State the concrete meaning of term in the present invention.
In the present invention, unless otherwise clearly defined and limited, fisrt feature second feature it " on " or it " under "
Can directly it be contacted including the first and second features, it is not directly to contact but pass through it that can also include the first and second features
Between other characterisation contact.Moreover, fisrt feature second feature " on ", " top " and " above " to include first special
Sign is directly over second feature and oblique upper, or is merely representative of fisrt feature level height and is higher than second feature.Fisrt feature exists
Second feature " under ", " lower section " and " following " fisrt feature that includes are immediately below second feature and obliquely downward, or be merely representative of
Fisrt feature level height is less than second feature.
Embodiment 1
It refer to shown in Fig. 1, present embodiments provide a kind of coaxial aircraft transmission device 001, including the first jackshaft
100th, the second jackshaft 110 and the coaxially arranged axle 130 of first axle 120 and second, the jackshaft 100 of first axle 120 and first are logical
Gear train drive connection is crossed, the first jackshaft 100 and the second jackshaft 110 are connected by gear train, the second jackshaft 110
It is connected with the second axle 130 by gear train, the first jackshaft 100 and the second jackshaft 110 are arranged symmetrically in first axle 120
Both sides.In the present embodiment, first gear 101 is arranged with first axle 120, the 3rd gear is arranged with the first jackshaft 100
103 and the second gear 102 that is engaged with first gear 101, the 5th gear 105 is arranged with the second jackshaft 110 and with the 3rd
The 4th gear 104 that gear 103 engages, the 6th gear 106 engaged with the 5th gear 105 is arranged with the second axle 130.
The coaxial aircraft transmission device 001 that the present embodiment provides is simple and compact for structure, the passing power that can stablize.Its
Middle power is delivered on the second axle 130 by first axle 120 and via the first jackshaft 100 and the second jackshaft 110, to realize
The function that the axle 130 of first axle 120 and second reversely rotates, passes through the He of first gear 101 when wherein first axle 120 turns clockwise
The rotate counterclockwise of the first jackshaft of gear set drive 100 that second gear 102 forms, by the when the first jackshaft 100 rotates
The second jackshaft of gear set drive 110 of three gears 103 and the 4th gear 104 composition turns clockwise, and the second jackshaft 110 revolves
The rotate counterclockwise of the second axle of gear set drive 130 being made up of when turning the 5th gear 105 and the 6th gear 106, passes through first
The power train of the jackshaft 110 of jackshaft 100 and second and multiple travelling gears composition realizes that the axle 130 of first axle 120 and second is anti-
To the function of rotation, and the first jackshaft 100 and the second jackshaft 110 are arranged symmetrically in the two of the axle 130 of first axle 120 and second
Side, the equalising torque of the whole coaxial aircraft transmission device 001 in transmission process can be ensured, keep the steady of its transmission process
It is fixed to carry out, improve the structural stability of coaxial aircraft transmission device 001.
Coaxial aircraft transmission device 001 also includes connecting cylinder 140 and the support base 150 provided with ball holding tank 151, and first
The one end of axle 120 away from the second axle 130 is rotatable in connecting cylinder 140, the one end of connecting cylinder 140 away from the second axle 130
Provided with the bulb 141 rotated in ball holding tank 151, connecting cylinder 140 is connected with least one for driving its relative support
The runner assembly that seat 150 rotates.In the present embodiment, connecting cylinder 140 is connected with four runner assemblies.Limit is provided with connecting cylinder 140
Determine the bearing of 120 radial and axial position of first axle.Connecting cylinder 140 passes through the bulb 141 that one end is set and the end of support base 150
The ball holding tank 151 of setting is rotatablely connected, and the one end of first axle 120 away from the second axle 130 is rotated in connecting cylinder 140,
When first axle 120 is rotated and power is transferred into the second axle 130, four phases of runner assembly drive connection cylinder 140 can be passed through
Support base 150 is rotated, so as to drive the relative support seat 150 of 120 and second axle of first axle 130 to rotate, to adjust first axle 120
With the relative position of the second axle 130 and support base 150.
Telophragma 160 is arranged with connecting cylinder 140, four runner assemblies are connected with telophragma 160, and runner assembly includes
Electric pushrod 170 and connecting rod 171, the both ends of connecting rod 171 are be hinged with electric pushrod 170 and connecting cylinder 140 respectively.The present embodiment
In, junction being arranged circumferentially along telophragma 160 of connecting rod 171 and telophragma 160 in four runner assemblies.User can
To promote connected connecting rod 171 to move by controlling electric pushrod 170 to stretch, so as to drive centre by connecting rod 171
Disk 160 produces rotation relative to connecting cylinder 140, drives four connecting rods 171 flexible respectively by four electric pushrods 170, can be right
Thrust and pulling force corresponding to the surrounding generation of telophragma 160, so as to drive the relative connecting cylinder on four direction of telophragma 160
140 movements, change so as to freely adjust the relative position of the axle 130 of first axle 120 and second and connecting cylinder 140.
First axle 120 is connected with the drive component for driving it to rotate, and drive component includes motor 180, drives
The output shaft of motor 180 is connected by conical gear group and the first jackshaft 100.Outside motor 180 and connecting cylinder 140
Wall connects and the first conical gear 181 is arranged with the output shaft of motor 180, and the Shang Tao societies of first axle 120 have and the first circle
The second conical gear 182 that bevel gear 181 engages.Motor 180 drives first axle 120 to rotate by conical gear group, and
It can be rotated to adapt to aircraft flight attitudes vibration with the relative support seat 150 of connecting cylinder 140.
Embodiment 2
As shown in Fig. 2 the present embodiment 2 provides a kind of coaxial aircraft transmission device 002, coaxial aircraft transmission dress
Set to 0 02 roughly the same with the coaxial aircraft transmission device 001 in embodiment 1, difference is, the coaxial aircraft transmission device
Also include the 3rd axle 210 being connected with first axle 120 by gear train in 002, one end of the 3rd axle 210 is rotatable to be set
In in connecting cylinder 140, being arranged with the 7th gear 107 in first axle 120, it is arranged with the 3rd axle 210 and is engaged with the 7th gear 107
Eighth gear 108.The coaxial aircraft transmission device 002 that the present embodiment provides passes with the coaxial aircraft that embodiment 1 provides
Dynamic device 001 is compared, by increased 3rd axle 210 can user-friendly drive device power is transferred to the 3rd axle
210, and power is further transferred to the axle 130 of first axle 120 and second by the 3rd axle 210 stabilization.
Embodiment 3
It refer to shown in Fig. 3 and Fig. 4, present embodiments provide a kind of aircraft, it includes fuselage and on fuselage
One coaxial aircraft transmission device 003, coaxial aircraft transmission device 003 include the first jackshaft 100, the second jackshaft
110 and the coaxially arranged axle 130 of first axle 120 and second, the jackshaft 100 of first axle 120 and first passes through gear train transmission and connected
Connect, the first jackshaft 100 and the second jackshaft 110 are connected by gear train, and the second jackshaft 110 and the second axle 130 are logical
Gear train drive connection is crossed, the first jackshaft 100 and the second jackshaft 110 are arranged symmetrically in the both sides of first axle 120, first axle
First gear 101 is arranged with 120, the 3rd gear 103 is arranged with the first jackshaft 100 and is engaged with first gear 101
Second gear 102, the 5th gear 105 and the 4th gear 104 engaged with the 3rd gear 103 are arranged with the second jackshaft 110,
The 6th gear 106 engaged with the 5th gear 105 is arranged with second axle 130.First jackshaft 100 is connected with for driving it
The drive component of rotation, a rotor is arranged with respectively on the axle 130 of first axle 120 and second.
Coaxial aircraft transmission device 003 also includes connecting cylinder 140 and the support base 150 provided with ball holding tank 151, support
Seat 150 is connected with the body of aircraft, and the one end of first axle 120 away from the second axle 130 is rotatable in connecting cylinder 140,
The one end of connecting cylinder 140 away from the second axle 130 is provided with the bulb 141 rotated in ball holding tank 151, is covered on connecting cylinder 140
Provided with telophragma 160, telophragma 160 is connected with four runner assemblies for being used to drive its relative support seat 150 to rotate, rotating group
Part includes electric pushrod 170 and connecting rod 171, and the both ends of connecting rod 171 are be hinged with electric pushrod 170 and telophragma 160 respectively.
Coaxial aircraft transmission device 003 also includes the first protection cylinder 190 and second and protects cylinder 200, connecting cylinder 140, branch
Support seat 150 and runner assembly are respectively positioned in the first protection cylinder 190；First jackshaft 100, the second jackshaft 110, first axle 120
It is respectively positioned on the second axle 130 in the second protection cylinder 200.It is provided with second protection cylinder 200 and is respectively used to rotation and fixes among first
Axle 100, the second jackshaft 110, the bearing of the axle 130 of first axle 120 and second.First protection cylinder 190 and second protects the energy of cylinder 200
Enough more axles and Transmission gears to being included in coaxial aircraft transmission device 003 are protected, and are improved coaxial aircraft and are passed
The structural stability of dynamic device 003.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (10)
1. a kind of coaxial aircraft transmission device, it is characterised in that it includes the first jackshaft, the second jackshaft and coaxially arranged
First axle and the second axle, the first axle and first jackshaft be connected by gear train, first jackshaft
It is connected with second jackshaft by gear train, second jackshaft and second axle are driven by gear train and connected
Connect, first jackshaft and second jackshaft are arranged symmetrically in the both sides of the first axle.
2. coaxial aircraft transmission device according to claim 1, it is characterised in that hold also including connecting cylinder and provided with ball
Receive the support base of groove, the one end of the first axle away from second axle is rotatable in the connecting cylinder, the connection
The one end of cylinder away from second axle 130 is provided with the bulb rotated in the ball holding tank.
3. coaxial aircraft transmission device according to claim 2, it is characterised in that also include passing through with the first axle
3rd axle of gear train drive connection, one end of the 3rd axle are rotatable in the connecting cylinder.
4. coaxial aircraft transmission device according to claim 2, it is characterised in that the connecting cylinder is connected with least one
It is individual to be used to drive the runner assembly that it is rotated relative to the support base.
5. coaxial aircraft transmission device according to claim 4, it is characterised in that the runner assembly includes electronic push away
Bar and connecting rod, the both ends of the connecting rod are hinged with the electric pushrod and the connecting cylinder respectively.
6. coaxial aircraft transmission device according to claim 4, it is characterised in that be arranged with centre on the connecting cylinder
Disk, each runner assembly are connected with the telophragma.
7. coaxial aircraft transmission device according to claim 4, it is characterised in that described also including the first protection cylinder
The connecting cylinder, the support base and the runner assembly are respectively positioned in the first protection cylinder.
8. coaxial aircraft transmission device according to claim 1, it is characterised in that described also including the second protection cylinder
First jackshaft, second jackshaft, the first axle and second axle are respectively positioned in the second protection cylinder.
9. coaxial aircraft transmission device according to claim 1, it is characterised in that the first axle is connected with for driving
The drive component of its rotation is moved, the drive component includes motor, and the output shaft of the motor passes through conical gear
Group is connected with the first axle.
10. a kind of aircraft, it is characterised in that it includes at least one coaxial winged as claimed in any one of claims 1-9 wherein
Row device transmission device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711277466.6A CN107795669A (en) | 2017-12-06 | 2017-12-06 | Coaxial aircraft transmission device and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711277466.6A CN107795669A (en) | 2017-12-06 | 2017-12-06 | Coaxial aircraft transmission device and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107795669A true CN107795669A (en) | 2018-03-13 |
Family
ID=61537401
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711277466.6A Pending CN107795669A (en) | 2017-12-06 | 2017-12-06 | Coaxial aircraft transmission device and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107795669A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2122833U (en) * | 1992-05-30 | 1992-11-25 | 李晓阳 | Drive differential mechanism for coaxial rotorcrafts |
| US20090057482A1 (en) * | 2007-08-29 | 2009-03-05 | Charles Lin | Transmission Device for a Twin-Rotor Helicopter |
| CN202070153U (en) * | 2011-04-06 | 2011-12-14 | 深圳市艾特航模股份有限公司 | Rotor drive device of coaxial dual-propeller model helicopter |
| CN102658865A (en) * | 2012-05-17 | 2012-09-12 | 李游 | Coaxial drive and control structure for coaxial contrarotation rotor helicopter |
| CN104859854A (en) * | 2015-04-16 | 2015-08-26 | 北京航空航天大学 | Heavy-load low-structure-complexity double-coaxial-twin-rotor unmanned aerial vehicle |
| CN207514205U (en) * | 2017-12-06 | 2018-06-19 | 亚伯兰环保科技（北京）有限公司 | Coaxial aircraft transmission device and aircraft |
-
2017
- 2017-12-06 CN CN201711277466.6A patent/CN107795669A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2122833U (en) * | 1992-05-30 | 1992-11-25 | 李晓阳 | Drive differential mechanism for coaxial rotorcrafts |
| US20090057482A1 (en) * | 2007-08-29 | 2009-03-05 | Charles Lin | Transmission Device for a Twin-Rotor Helicopter |
| CN202070153U (en) * | 2011-04-06 | 2011-12-14 | 深圳市艾特航模股份有限公司 | Rotor drive device of coaxial dual-propeller model helicopter |
| CN102658865A (en) * | 2012-05-17 | 2012-09-12 | 李游 | Coaxial drive and control structure for coaxial contrarotation rotor helicopter |
| CN104859854A (en) * | 2015-04-16 | 2015-08-26 | 北京航空航天大学 | Heavy-load low-structure-complexity double-coaxial-twin-rotor unmanned aerial vehicle |
| CN207514205U (en) * | 2017-12-06 | 2018-06-19 | 亚伯兰环保科技（北京）有限公司 | Coaxial aircraft transmission device and aircraft |
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