CN104787315B - Duct power set and aircraft - Google Patents
Duct power set and aircraft Download PDFInfo
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- CN104787315B CN104787315B CN201510184487.8A CN201510184487A CN104787315B CN 104787315 B CN104787315 B CN 104787315B CN 201510184487 A CN201510184487 A CN 201510184487A CN 104787315 B CN104787315 B CN 104787315B
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Abstract
The present invention provides a kind of duct power set and aircraft, the duct power set include the first duct, the first rotor driver is provided with first duct, first rotor driver and the first duct coaxial line are set, and first rotor driver driven by the first power set and around the first duct axis rotate, wherein, the second duct is provided with outside first duct, second duct and the first duct coaxial line are set, and second be provided with the second rotor driver driven by the second power set in duct, second rotor driver is located between the first duct and the second duct, and second rotor driver and the second duct coaxial line set.The aircraft includes frame and rack-mounted duct power set.Duct power set of the invention can reduce the mutual disturbance of fluid, so as to reduce the energy loss of duct power set.
Description
Technical field
Apparatus field is provided the present invention relates to power, is to be related to a kind of duct power set and use this specifically
Plant the aircraft of duct power set.
Background technology
Unmanned vehicle is widely used in fields such as Aerial photography, air transports, existing unmanned winged
Row device is mostly Fixed Wing AirVehicle or Multi-axis aircraft, sets one or more wings on Fixed Wing AirVehicle, and
Propeller is set on wing, is driven propeller to rotate the air-flow for producing by motor and is promoted aircraft flight.
Multi-axis aircraft is a kind of rotor craft with two or more rotor shafts, as shown in figure 1, existing one kind
Multi-axis aircraft has four rotor shafts, and aircraft has a frame 10, and power supply, control circuit are provided with frame 10
Deng, and frame 10 is provided with four fulcrums 12, and four fulcrums 12 are evenly arranged in the circumference of frame 10, i.e., adjacent two
Angle between fulcrum 12 is 90 °.
The rotor arranged for about a pair is provided with the end of each fulcrum 12, on the direction of the axis of frame 10, on
Rotor 13 is located at the top of lower rotor 14, and upper rotor 13 is rotated by motor 15, and lower rotor 14 drives rotation by motor 16
Turn.Also, upper rotor 13 and the coaxial setting of lower rotor 14, therefore, the rotating shaft of motor 15 and the rotating shaft of motor 16 are coaxial lines.
Additionally, motor 15 is each attached to the end of support 12 with motor 16, and motor 15 is located at the top of support 12, and motor 16 is located at
The lower section of support 12.Generally, on four supports 12 of aircraft upper rotor 13, the rotating shaft of lower rotor 14 are parallel to each other, and
Parallel to the axis of frame 10.
Generally, the rotation direction of upper rotor 13 is opposite with the rotation direction of lower rotor 14, and upper rotor 13 is straight
The equal diameters of footpath and lower rotor 14, so that pulling force produced when lifting rotor rotational, is achieved in the vertical liter of aircraft
Drop is moved, moved forward and backward, lateral movement, elevating movement, roll motion and yawing rotation.
Upper rotor 13 and lower rotor 14 typically each have blade more than two panels, per a piece of blade by the oar near rotating shaft
Root, the oar tail away from rotating shaft and the oar abdomen between blade root and oar tail are constituted.During rotor wing rotation, the oar abdominal section pair of blade
Air effect is maximum, and the downwash flow speed of oar belly position is maximum.If the rotating speed of upper rotor 13 is higher than the rotating speed of lower rotor 14, upper rotor
13 high velocity airs for producing are beaten on the blade of lower rotor 14, form larger energy loss.If the rotating speed of upper rotor 13 is less than down
The rotating speed of rotor 14, upper rotor 13 then hinders the air-flow of lower rotor 14 to suck, and pneumatic efficiency is relatively low.Even if the rotating speed of upper rotor 13
Rotating speed with lower rotor 14 is identical, and when upper and lower blade is close to each other, the windage produced between upper and lower blade is more serious, gas
Dynamic rate efficiency is still relatively low.
Additionally, existing some aircraft drive the flight of aircraft using duct power set, such as notification number is
The Chinese invention patent of CN102114914B discloses a kind of aircraft of many rotor VTOL, is set in the frame of the aircraft
Lift power unit and thrust powers unit are equipped with, each lift power unit and thrust powers unit are a duct and move
Power apparatus, duct power set have the duct that can be fixed in frame, and duct is usually the cylindrical shape of open at both ends, and
Rotor is provided with duct and the power set of rotor wing rotation, such as motor are driven, rotor is driven in duct by motor
Interior rotation.
So, when rotor rotates in duct, the air-flow of generation flows in duct, so as to produce larger moving to duct
Power, and then promote aircraft to rise or go off course.Due to generally only setting one group of rotor, rotor in the duct of existing aircraft
Rotation is that the moment of torsion for producing is larger, is unfavorable for the control of aircraft.Two groups of phase mutual respects on duct axis are such as set in duct
Folded rotor, the then problem for causing pneumatic rate less efficient.
Additionally, existing part spitkit is also provided with duct dynamical system, for providing power to promote to ship
Ship is forward or changes the travel direction of ship.
The content of the invention
The main object of the present invention is to provide a kind of pneumatic efficiency duct power set higher.
It is a further object of the present invention to provide a kind of aircraft for improving duct power set pneumatic efficiency.
In order to realize above-mentioned main purpose, the duct power set that the present invention is provided include the first duct, the first duct
The first rotor driver is inside provided with, the first rotor driver and the first duct coaxial line are set, and the first rotor driver is by the first power
Device drives and the axis around the first duct rotates, wherein, the second duct is provided with outside the first duct, the second duct and first are contained
Road coaxial line is set, and the second rotor driver driven by the second power set is provided with the second duct, the second rotor driver position
Between the first duct and the second duct, and the second rotor driver and the second duct coaxial line are set.
From such scheme, isolated by the first duct between the first rotor driver and the second rotor driver, aircraft flies
Between the departure date, when the first rotor driver and the second rotor driver are reversely rotated, the downwash flow and second that the first rotor driver is produced
The downwash flow that rotor driver is produced is not overlapped, and effectively weakens flow-disturbing, reduces gas friction, so that duct power set
Energy loss is minimum, improves the stationarity of aircraft flight.
One preferred scheme is that mounting ring is provided with the second duct, and the first duct is arranged in mounting ring, and the second rotation
Swing device is sleeved on the outside of the first duct.
As can be seen here, the first duct being arranged on can effectively realize the first duct and the in the mounting ring of the second duct
The fixation of two ducts, it is ensured that the first duct will not be subjected to displacement relative to the second duct, and it is able to ensure that the first duct and
The coaxial line of two ducts is set.
Further scheme is that mounting hole is provided with the middle part of the first duct, and the first power set are fixed in mounting hole.
It can be seen that, the first power set can be fixed on the middle part of the first duct, and may insure the first power set
Axis is Chong Die with the axis of the first duct, therefore ensures that the first rotor driver rotates around the axis of the first duct.
Further scheme is that the second power set are arranged in mounting hole, and the second power set and the first power
Device coaxial line is set, and the rotating shaft of the first power set is hollow shaft, and the rotating shaft of the second power set passes through hollow shaft.
As can be seen here, the first power set and the second power set are installed in mounting hole, two can be saved and moved
The position that power apparatus are installed, and may insure the coaxial line arrangement of the first rotor driver and the second rotor driver, it is to avoid two
The air-flow produced after rotor driver rotation influences each other.
Further scheme is, on the first duct axis direction, the first rotor driver enters positioned at the duct of distance first
At the position of 1/3rd of mouth, on the second duct axis direction, the second rotor driver is located at distance the first duct entrance
At 1/3rd position.
Rotor driver is arranged at 1/3rd position of correspondence duct entrance, duct power set can be lifted
Pulling force, is conducive to duct power set to provide bigger power to aircraft.
Further scheme is, on the second duct axis direction, the entrance of the second rotor driver and the second duct it
Between the distance between the entrance of distance less than the first rotor driver and the second duct.
As can be seen here, in the second duct, the second rotor driver entering closer to the second duct than the first rotor driver
Mouthful, the additional pulling force of duct power set can be lifted.
To realize above-mentioned another object, the aircraft that the present invention is provided includes frame and the duct being fixed in frame
Power set, duct power set have the first duct, and the first power set and the first rotor driver are provided with the first duct,
First rotor driver and the first duct coaxial line are set, and the first rotor driver is driven and around the first duct by the first power set
Axis rotation, wherein, be provided with the second duct outside the first duct, the second duct and the setting of the first duct coaxial line, and second
The second power set and the second rotor driver driven by the second power set are provided with duct, the second rotor driver is located at the
Between one duct and the second duct, and the second rotor driver and the second duct coaxial line are set.
From such scheme, the duct power set of aircraft are provided with the first duct and the second duct, and first
Isolated by the first duct between rotor driver and the second rotor driver, produced by the first rotor driver and the second rotor driver
Air-flow will not be interfered, so as to weaken flow-disturbing, reduce gas friction, reduce the energy loss of duct power set, be improved
The stationarity of aircraft flight.
Brief description of the drawings
Fig. 1 is a kind of structure chart of existing aircraft.
Fig. 2 is the structure chart of duct power set first embodiment of the present invention.
Fig. 3 is the structure chart at another visual angle of duct power set first embodiment of the present invention.
Fig. 4 is the structure decomposition figure of duct power set first embodiment of the present invention.
Fig. 5 is the structure decomposition figure of the first duct and the second duct in duct power set first embodiment of the present invention.
Fig. 6 is the structure chart of the first duct and the second duct in duct power set first embodiment of the present invention.
Fig. 7 is the first power set and the second power set, the first culvert in duct power set first embodiment of the present invention
The structure decomposition figure in road.
Fig. 8 is the structure chart of hiding second duct in duct power set first embodiment of the present invention.
Fig. 9 is the structure chart of duct power set second embodiment of the present invention.
Figure 10 is the structure decomposition figure of duct power set second embodiment of the present invention.
Figure 11 is the partial structurtes enlarged drawing of duct power set second embodiment of the present invention.
Below in conjunction with drawings and Examples, the invention will be further described.
Specific embodiment
Duct power set of the invention may be mounted on aircraft, such as Multi-axis aircraft or Fixed Wing AirVehicle
On.If aircraft is Multi-axis aircraft, then flying instrument organic frame, sets one or more duct power set in frame,
Powered aircraft flight is provided from duct power set to frame.If aircraft is Fixed Wing AirVehicle, then aircraft
Frame includes fuselage and is fixed on the wing of fuselage both sides, and duct power set can be fixed on fuselage or wing, uses
In the power that rising or driftage are provided to frame.
Additionally, duct power set can also be arranged on spitkit, for realizing the driftage of ship, or it is ship
Forward power is provided, is described by as a example by carry-on duct power set below.
First embodiment：
Referring to Fig. 2 and Fig. 3, the duct power set of the present embodiment have two ducts, be respectively the first duct 25 and
Second duct 20, the first duct 25 and the second duct 20 are cylinder-like body, and open at both ends, from such as 2, first ducts 25
Diameter of the diameter less than the second duct 20, and the first duct 25 is arranged in the second duct 20.
Referring to Fig. 4, the first duct 25 has a shell 26 for cylindrical shape, and the installation of cylindrical shape is provided with shell 26
Hole 27, shell 26 and the equal open at both ends of mounting hole 27, and the axis of mounting hole 27 is Chong Die with the axis of shell 26.In shell
Connected by four pieces of connecting plates 28 between 26 and mounting hole 27, four pieces of connecting plates 28 uniform cloth in the circumference of the first duct 25
Put.In the present embodiment, the axial length of the axial length less than shell 26 of mounting hole 27, and mounting hole 27 is fully located at shell
In 26.
Second duct 20 is located at the outside of the first duct 25, and the second duct 20 is provided with the shell 21 of cylindrical shape, shell
21 open at both ends.It is provided with the mounting ring 22 of cylindrical shape in the shell 21, mounting ring 22 is also open at both ends, and mounting ring 22
Diameter of the diameter less than shell 21.Additionally, axial length of the axial length of mounting ring 22 less than shell 21, and mounting ring 22 is complete
It is located in shell 21 entirely.Preferably, mounting ring 22 is set with the coaxial line of shell 21.Also, lead between mounting ring 22 and shell 21
Four pieces of connecting plates 23 are crossed to connect, the two ends of each piece of connecting plate 23 be separately fixed at shell 21 inwall and mounting ring 22 it is outer
Wall, and four pieces of connecting plates 23 are evenly arranged in the circumference of the second duct 20.
First duct 25 is arranged in the mounting ring 22 of the second duct 20, as shown in figs. 5 and 6, outside the first duct 25
Footpath is equal with the internal diameter of mounting ring 22 or is slightly less than the internal diameter of mounting ring 22, and mounting ring 22 is fixed in order to the first duct 25
It is interior.Preferably, on the axis of the first duct 25, the axial length of the axial length more than mounting ring 22 of the first duct 25.
In the present embodiment, the first duct 25 and the coaxial line of the second duct 20 are set, therefore, in the second duct radially,
Mounting ring 22 is located at the centre of the second duct 20, and the first duct 25 is also in the centre of the second duct 20.
First rotor driver 37 is installed in the first duct 25, the first rotor driver 37 has three blades 38, three
Blade 38 is evenly arranged in the circumference of the first rotor driver 37.It is provided with as the first power set in the first duct 25
Motor 45, the middle part of motor 45 is provided with rotating shaft 46, and rotating shaft 46 is hollow shaft, and its middle part is provided with the through hole of circle.In the present embodiment,
First rotor driver 37 is arranged on one end of motor 45, and is rotated by rotating shaft 46.
Certainly, as the first power set motor can also be arranged on the first duct outside, motor by Chain conveyer,
The modes such as gear drive, V belt translation drive the first rotor driver to rotate.
Second rotor driver 30 is installed, the second rotor driver 30 has a housing 31 for circle in second duct 20,
The outer wall of housing 31 is provided with five blades 32, and five blades 32 are evenly arranged in the circumference of housing 31.Additionally, the inclination of blade 32
Direction is opposite with the incline direction of the blade 38 of the first rotor driver 37.Be provided with mounting post 33 in housing 31, mounting post 33 with
Be provided with five support bars 34 between housing 31, the two ends of each support bar be separately fixed at housing 31 and mounting post 33 it
Between.
Second rotor driver 30 is rotated by the motor 43 as the second power set, and motor 45 has rotating shaft 44, peace
Dress post 33 is fixed on the free end of rotating shaft 44, so as to realize that rotating shaft 44 drives the second rotor driver 30 to rotate.Certainly, as second
The motor of power set can also be arranged on the outside of the second duct, and motor is by modes such as Chain conveyer, gear drive, V belt translations
The second rotor driver is driven to rotate.
In the present embodiment, motor 45 and motor 43 are installed in mounting hole 27, as shown in fig. 7, in the first duct 25
Axis on, motor 43 and the coaxial line of motor 45 are arranged, it is preferable that the axis of motor 43 is with the axis of motor 45 in the first culvert
On the axis in road 25, therefore on the projecting direction of the end face of the first duct 25, motor 43 is overlap with motor 45.
It is provided with motor 45 and extend along the axis of motor 45 and through motor 45 and the through hole of rotating shaft 46 47, motor 43
Rotating shaft 44 can pass through through hole 47 and the rotating shaft 46 for hollow shaft, and extend to the top of rotating shaft 46, the second rotor driver
30 can be fixed in rotating shaft 46.Additionally, the middle part of the first rotor driver 37 also is provided with extending along the axis of the first rotor driver 37
And through the through hole 39 of the first rotor driver 37, rotating shaft 44 can pass through rotating shaft 39 and extend to the upper end of rotating shaft 39.
Because motor 43 is Chong Die with the axis of the first duct 25 with the axis of motor 45, therefore the first rotor driver 37,
Axis of the axis of two rotor drivers 30 also with the first duct 25 is Chong Die, and thus, the first duct 25, the second duct 20, first revolve
The axis of swing device 37, the second rotor driver 30, the first power set and the second power set is overlapped.
First rotor driver 37 is located in the first duct 25, and the second rotor driver 30 is located at the first rotor driver 25 and second
Between duct 20, it is preferable that the second rotor 30 is sleeved on the outside of the end of the first duct 25, as shown in figure 8, and the second rotor
The internal diameter of 30 devices occurs during avoiding the second rotor driver 30 from rotating slightly larger than the external diameter of the first duct 25 with the first duct 25
Rub and the rotation of the second rotor driver 30 of influence.
Certainly, two motors point be can also be using hollow shaft and the cooperation of solid shafting the invention is not restricted to two motors
Not for the first rotor driver and the second rotor driver provide power, and each motor and a rotor driver constitute one and move
The unit of power, two power units are arranged up and down in duct.
The outside of the first duct 25, i.e. the first rotor driver 37 and the second rotor driver are located at due to the second rotor driver 30
Isolated by the first duct 25 between 30, the downwash flow that such second rotor driver 30 is produced when rotating will not be to the first rotor
Device 37 is impacted, and the downwash flow produced during the rotation of the first rotor driver 37 will not also be caused to the second rotor driver 30
Influence, so that gas friction when reducing aircraft flight, makes the energy loss of duct power set minimum, and then improves flight
The stationarity of device flight, and save the electric energy that aircraft is used.
Preferably, on the axis direction of the first duct 25, the first rotor driver 37 is located at the entrance of the first duct of distance 25
The position at place 1/3rd, also, on the axis direction of the second duct 20, the second rotor driver 30 is located at the duct of distance second
The position of 20 porch 1/3rd, can so improve the additional pulling force produced by duct power set.
Certainly, on the axis direction of the first duct 25, the first rotor driver 37 is located at the exit of the first duct of distance 25
/ 3rd position, on the axis direction of the second duct 20, the second rotor driver 30 is exported positioned at the second duct of distance 20
The position at place 1/3rd.Or, on the axis direction of the first duct 25, the first rotor driver 37 is located at the duct of distance first
The position of 25 porch 1/3rd, and on the axis direction of the second duct 20, the second rotor driver 30 is located at distance second
The position in the exit 1/3rd of duct 20.Or, on the axis direction of the first duct 25, the first rotor driver 37 be located at away from
From the position in the exit 1/3rd of the first duct 25, and on the axis direction of the second duct 20, the second rotor driver 30
In the position of the porch 1/3rd of the second duct of distance 20.
Additionally, on the axis direction of the second duct 20, between the second rotor driver 30 and the entrance of the second duct 20 away from
From less than the distance between the first rotor driver 37 and the entrance of the second duct 20, the additional potential of the second duct 20 can be so improved
Power.It is of course also possible to be designed to the distance between the first rotor driver 37 and the entrance of the second duct 20 less than the second rotor driver
The distance between 30 and the entrance of the second duct 20, can so improve the additional pulling force of the first duct 25.Or, the second rotor dress
The distance between 30 and the entrance of the second duct 20 are put equal to the distance between the first rotor driver 37 and the entrance of the second duct 20, this
Sample can reduce flow perturbation and friction, further improve the stability of aircraft flight.
Also, the diameter of the first rotor driver 37 is less than the diameter of the second rotor driver 30, it is preferable that the first rotor driver
37 diameter is 0.4 times to 0.6 times of the diameter of the second rotor driver 30, it is preferable that the diameter of the first rotor driver 37 is second
0.5 times of the diameter of rotor driver 30, can so balance the ratio of the first duct 25 and the suction airflow of the second duct 20, be conducive to
The service life of the Homogeneouslly-radiating of the first duct 25 and the second duct 20, extension motor 43 and motor 45.
Additionally, in the present embodiment, the blade 32 of the quantity of blade 38 less than the second rotor driver 30 of the first rotor driver 37
Quantity, such design can reduce drive the first rotor driver 37 rotation power, extend motor 45 service life.
Certainly, the duct power set of the present embodiment have two ducts, and the culvert of more layers can be set during practical application
One rotor power device is set in road, and each duct, and each rotor power device is located at adjacent two-layer and contains
Between road, so as to realize that the air-flow between multilayer duct is isolated.
Second embodiment：
Referring to Fig. 9, the duct power set of the present embodiment have two ducts, be respectively less first duct of internal diameter with
And the second duct 60 on the outside of the first duct, in the present embodiment, the first duct is made up of two parts, and is mounted in respectively
Duct 50 in two ducts 60 and the duct 62 being fixed in the second duct 60.
Referring to Figure 10, mounting ring 61 is provided with the second duct 60, mounting ring 61 is fixed on the second culvert by polylith connecting plate
On the inwall in road 60.Duct 62 is provided with mounting ring 61, duct 62 is fixed on the second duct 60 by polylith connecting plate 63
Inwall on, and the coaxial line of 62 and second duct of duct 60 set.Duct 50 is arranged in mounting ring 61, and duct 50 is interior
Footpath is less than the internal diameter of the second duct 60, and the coaxial line of 50 and second duct of duct 60 is set.The upper end of duct 50 and duct 62
Lower end abuts, so as to constitute first duct of the present embodiment.Therefore, first duct of the present embodiment and the coaxial line of the second duct 60
Set.
A mounting hole 51 is provided with duct 50, mounting hole 51 is fixed on the inwall of duct 50 by polylith connecting plate 52
On.First rotor driver 56, and the first rotor driver 56 are installed by the motor as the first power set in duct 50
54 drive rotation.Preferably, the axis of the first rotor driver 56 is Chong Die with the axis of duct 50.
The second rotor driver 57 is provided between the first duct and the second duct 60, therefore the second rotor driver 57 is set
In the second duct 60, it is preferable that the second rotor driver 57 and the coaxial line of the second duct 60 are set.Second rotor driver 57 is by making
For the motor 55 of the second power set is rotated.
In the present embodiment, motor 54 and motor 55 are installed in mounting hole 51, and the rotating shaft of motor 54 is hollow shaft,
The rotating shaft of motor 55 can pass through motor 54 and its hollow shaft, and be upward through drive the second rotor dress of the first rotor driver 56
Put 57 rotations.
Referring to Figure 11, on the direction of the second duct 60, the entrance of duct 62 is located at the outside of the second duct 60, that is,
The entrance of the first duct is located at the outside of the second duct 60, and the entrance of such first duct is higher than the entrance of the second duct, also
It is that on the axis of the first duct, along the flow direction of air-flow, the entrance of the first duct is located at the upstream of the entrance of the second duct 60,
Air-flow is so conducive to enter the first duct.In addition, the porch of duct 62 is up big and down small horn-like, worn with improving air-flow
Cross the speed of the first duct.In addition, the entrance of the second duct 60 is also up big and down small horn-like, to improve air-flow through second
The speed of duct 60.
Isolated by the first duct between two rotor drivers set due to duct power set of the invention, first
When rotor driver and the second rotor driver are rotated in opposite directions, downwash flow and the second rotor dress that the first rotor driver is produced
The downwash flow for putting generation is not resulted in and interfered, and reduces gas friction, so as to reduce the energy loss of duct power set.
Finally it is emphasized that the invention is not restricted to above-mentioned implementation method, such as two blade quantity of rotor driver with
The change such as change of the position of shape, the change of incline direction, the first rotor driver in the first duct should also be included in this
In invention scope of the claims.Additionally, duct power set of the invention are not limited to using on board the aircraft, can be with
Using on the ship or car by air stream drives, such as aircushion vehicle and pneumatic sleigh.
Claims (8)
1. duct power set, including
First duct, is provided with the first rotor driver in first duct, first rotor driver is common with first duct
Axis is set, and first rotor driver is driven by the first power set and the axis around first duct rotates；
Its characteristic is：
The second duct is provided with outside first duct, second duct is set with the first duct coaxial line, and described
The second rotor driver driven by the second power set is provided with second duct, second rotor driver is located at described first and contains
Between road and second duct, and second rotor driver is set with the second duct coaxial line；
First rotor driver can be reversely rotated with second rotor driver；
Mounting ring is provided with second duct, first duct is arranged in the mounting ring, and second rotor is filled
Put the outside for being sleeved on first duct.
2. duct power set according to claim 1, it is characterised in that：
Mounting hole is provided with the middle part of first duct, first power set are fixed in the mounting hole.
3. duct power set according to claim 2, it is characterised in that：
Second power set are arranged in the mounting hole, and second power set are common with first power set
Axis is set；
The rotating shaft of first power set is hollow shaft, and the rotating shaft of second power set passes through the hollow shaft.
4. duct power set according to any one of claims 1 to 3, it is characterised in that：
On the first duct axis direction, first rotor driver be located at apart from the first duct entrance three/
At one position；
On the second duct axis direction, second rotor driver be located at apart from the second duct entrance three/
At one position.
5. duct power set according to any one of claims 1 to 3, it is characterised in that：
On the axis direction of first duct, the entrance of first duct is located at the entrance outside of second duct.
6. duct power set according to any one of claims 1 to 3, it is characterised in that：
On the axis of first duct, along the flow direction of air-flow, the entrance of first duct is located at described second and contains
The upstream of road entrance.
7. duct power set according to any one of claims 1 to 3, it is characterised in that：
Between 0.4 times to 0.6 times of the diameter of a diameter of described second rotor driver of first rotor driver.
8. aircraft, including,
Frame and the duct power set being fixed in the frame, the duct power set have the first duct, described
The first power set and the first rotor driver are provided with first duct, first rotor driver is coaxial with first duct
Line is set, and first rotor driver is driven by first power set and the axis around first duct rotates；
Its characteristic is：
The second duct is provided with outside first duct, second duct is set with the first duct coaxial line, and described
The second power set and the second rotor driver driven by second power set, second rotation are provided with second duct
Swing device is located between first duct and second duct, and second rotor driver is coaxial with second duct
Line is set；
First rotor driver can be reversely rotated with second rotor driver；
Mounting ring is provided with the middle part of second duct, first duct is arranged in the mounting ring, and second rotation
Swing device is sleeved on the end outside of first duct.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510184487.8A CN104787315B (en) | 2015-04-17 | 2015-04-17 | Duct power set and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510184487.8A CN104787315B (en) | 2015-04-17 | 2015-04-17 | Duct power set and aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN104787315A CN104787315A (en) | 2015-07-22 |
| CN104787315B true CN104787315B (en) | 2017-06-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510184487.8A Active CN104787315B (en) | 2015-04-17 | 2015-04-17 | Duct power set and aircraft |
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| RU2751925C1 (en) * | 2020-05-26 | 2021-07-20 | Александр Викторович Атаманов | Mounting system for pairs of electric motors of the coaxial propeller group of the aircraft |
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| RU2751925C1 (en) * | 2020-05-26 | 2021-07-20 | Александр Викторович Атаманов | Mounting system for pairs of electric motors of the coaxial propeller group of the aircraft |
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