CN206466172U - A kind of tandem type derotation wing power set - Google Patents
A kind of tandem type derotation wing power set Download PDFInfo
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- CN206466172U CN206466172U CN201621348549.0U CN201621348549U CN206466172U CN 206466172 U CN206466172 U CN 206466172U CN 201621348549 U CN201621348549 U CN 201621348549U CN 206466172 U CN206466172 U CN 206466172U
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- rotor
- fixing axle
- drive device
- power set
- wing power
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Abstract
The utility model proposes a kind of tandem type derotation wing power set, including derotation wing power set；Derotation wing power set include upper rotor, lower rotor, upper drive device, lower drive device and fixing axle；Upper drive device is installed in fixing axle；Upper rotor is installed on the output end of drive device；Upper drive device drives upper rotor to be rotated around fixing axle；Lower drive device is installed in fixing axle；Lower rotor is installed on the output end of lower drive device；Lower drive device drives lower rotor to be rotated around fixing axle.The utility model proposes it is a kind of it is coaxial, tandem type, tandem type derotation wing power set with independent safety device can be achieved, it has the beneficial effects such as manufacturing process is simple, manufacture difficulty is low, security reliability is high, cost is low and service life is high.
Description
Technical field
The utility model is related to airmanship field, specifically refers to the tandem type derotation wing power set of aircraft.
Background technology
Coaxial derotation wing power set, also known as coaxial double-oar power set, principle are reversely rotated by upper and lower rotor,
Form the equalising torque of helicopter horizontal direction because its " aerodynamic characteristic symmetrical, mobility is good ", " contour dimension is compact ",
" stability is good, it is not necessary to the torque in tail-rotor balancing helicopter horizontal direction ", " in the case of high efficiency, same motor, lift
The advantages such as big 12% or so " of lift than pure helicopter, in current international depopulated helicopter development field, to tend to approval " altogether
Shaft type helicopter ".
Fig. 1 is refer to, is the structure chart of traditional coaxial derotation wing power set, it is respectively by interior axle a and outer shaft b
Upper rotor c and lower rotor d rotation is controlled respectively, and its power is all realized by motor-driven gear transmission.Wherein, it is interior
Axle a and outer shaft b design, will keep level（Dimension process is strict）, the strength of materials require it is high, all increase the coaxial derotation wing
The mechanical technology difficulty of power set；Meanwhile, because needing the parts such as " gear ", " bearing " to be driven in package unit,
So self friction power is very big, i.e., power consumption penalty is very big, high to the power requirement of motor in itself；And, without independent safety dress
Put.
Utility model content
In order to solve the above problems, the utility model proposes a kind of coaxial, tandem type can be achieved, with independent peace
The tandem type derotation wing power set of full device.
What the utility model was achieved through the following technical solutions：
The utility model proposes a kind of tandem type derotation wing power set, including derotation wing power set；
Derotation wing power set include upper rotor, lower rotor, upper drive device, lower drive device and fixing axle；
Upper drive device is installed in fixing axle；Upper rotor is installed on the output end of drive device；Upper drive device band
Dynamic upper rotor is rotated around fixing axle；
Lower drive device is installed in fixing axle；Lower rotor is installed on the output end of lower drive device；Lower drive device band
Dynamic lower rotor is rotated around fixing axle.
Further, the bottom of the fixing axle is arranged on the top of aircraft；The center of the fixing axle, which is provided with, to be run through
The routing hole of whole fixing axle；Cable is provided with routing hole；The input of cable and the way circuit of aircraft are connected, on cable simultaneously
It is associated with the upper drive device and lower drive device of derotation wing power set.
Further, the upper drive device includes coil, stator and rotor；Stator and rotor using the axis of fixing axle as
Axle center is distributed；Rotor and fixing axle are rotated and are connected, and stator is fixedly connected with fixing axle, and coil is around being located on stator, coil and line
The output end electrical connection of cable；Rotor produces relative motion in coil electricity with stator, and rotor drives upper rotor around fixing axle
Rotate.
Further, upper drive device also includes base；The base, which is one, has the framework of accommodating chamber；Base with
Fixing axle is fixedly connected；The stator is contained in the accommodating chamber, so that stator is fixed on fixing axle.
Further, the upper drive device also includes rotor disk；The rotor disk is used to install rotor；The rotor
Disk is in thin annular shape, and the thin annulus is distributed by axle center of the axis of the fixing axle；The rotor disk is arranged on rotor top,
The upper rotor is arranged on the top surface of rotor disk.
Further, the upper rotor includes at least two panels blade.
Further, the tandem type derotation wing power set also include safety device；The safety device is arranged on solid
The top of dead axle.
Further, the safety device includes parachute and parachute storage device；The parachute storage device is set
Put on the top of fixing axle；The parachute has the housed state for being contained in parachute storage device, and deployment exists
Make the deployed condition of aircraft down on fixing axle.
The beneficial effects of the utility model：
1. derotation wing power set of the present utility model are by the way of coaxial, used with traditional derotation wing power set
The mode of non co axial is compared, and its manufacturing process is simple, manufacture difficulty and holistic cost are reduced.
2. derotation wing power set of the present utility model, which use to be directly driven with drive device, goes up rotor, or under
The lower rotor of drive device direct drive, wherein upper drive device essence is exactly a motor, inside does not have gear drive, because
This, compared with the traditional approach that rotor is driven by motor-driven gear transmission, this case eliminates gear drive, so that a whole set of dress
The frictional force put reduces, and then kinetic equation loss is reduced, so that the overall service life extension of power set.
3. the design of safety device in the utility model has been Flight Vehicle Design independent, high reliability, high security
Complete machine safety equipment, and highly merged with the nucleus equipment derotation wing power set of aircraft, so as to reach aircraft
The new high degree of security.
4. the tandem type derotation wing power set of this case support the tandem type extension of power set, power performance is realized
Linear to expand, this feature breaches traditional derotation wing power set and does not possess the situation that power performance linearly expands.
Brief description of the drawings
Fig. 1 is the structural representation of traditional coaxial derotation wing power set in background technology；
Fig. 2 is tandem type derotation wing power set schematic diagram of the present utility model；
Fig. 3 be Fig. 2 in a set of derotation wing power set schematic diagram；
Fig. 4 is the upper rotor in Fig. 3, upper drive device, the structural representation of fixing axle；
Fig. 5 be Fig. 4 in base structural representation；
Fig. 6 be Fig. 4 in rotor structural representation.
Embodiment
For clearer, complete explanation the technical solution of the utility model, below in conjunction with the accompanying drawings to the utility model
It is described further.
Fig. 2 is refer to, the tandem type derotation wing power set provided for embodiment of the present utility model, it includes
Two sets of derotation wing power set 1；In other embodiments, the tandem type derotation wing power set can include it is a set of, three sets,
Even more many set derotation wing power set 1, belong to the technical solution of the utility model.Specifically, rear extended meeting is illustrated.
Fig. 3 is refer to, derotation wing power set 1 include upper rotor 11, lower rotor 14, upper drive device 12, lower driving dress
Put 15 and fixing axle 13.
Fixing axle 13 is an elongated axle, and the center of the fixing axle 13 is provided with the routing hole through whole fixing axle 13
（Not shown in figure）, the routing hole is interior to be provided with cable 16；During installation, the fixing axle 13 is erected to the top of aircraft 3,
The bottom of the fixing axle 13 is arranged on to the top of aircraft 3, the way circuit of the input of cable 16 and aircraft 3 is connected
Connect, the upper drive device 12 and lower drive device 15 of derotation wing power set 1 are parallel with the output end of cable 16.
Upper drive device 12 is installed in fixing axle 13；Upper rotor 11 is installed on the output end of drive device 12；It is upper to drive
Dynamic device 12 drives upper rotor 11 to be rotated around fixing axle 13.
Preferably, Fig. 4 is refer to, the upper drive device 12 includes coil, stator 122 and rotor 123；The He of stator 122
Rotor 123 is distributed by axle center of the axis of fixing axle 13；Rotor 123 is rotated with fixing axle 13 and is connected, stator 122 and fixing axle 13
It is fixedly connected, coil is around being located on stator 122, and coil is electrically connected with the output end of cable 16, specifically, the correspondence of fixing axle 13
The position of upper drive device 12 is provided with threading hole（Not shown in figure）, the output end of cable 16 is through threading hole to connect with coil
Connect；When being electrified on coil, rotor 123 produces relative motion with stator 122, and rotor 123 drives upper rotor 11 around fixing axle
13 rotate.Adjusted by the energization direction and energization size of regulating winding rotor 123 rotation direction and slewing rate it is big
It is small.
As can be seen here, derotation wing power set 1 of the present utility model are used with the direct drive of drive device 12
Rotor 11, wherein the upper essence of drive device 12 is exactly a motor, inside does not have gear drive, therefore, is driven compared with by motor
Moving gear is driven to drive the traditional approach of rotor, and this case eliminates gear drive, so that the frictional force of package unit reduces,
Then kinetic equation loss is reduced.
Upper drive device 12 also includes base 124；Fig. 5 is refer to, the base 124 is by one thin cylinder panel 1241
The framework with accommodating chamber 1243 surrounded with a bottom plate 1242.The center of bottom plate 1242 is provided with a mounting hole 1244,
The base 124 is set in fixing axle 13 by mounting hole 1244, and base 124 is fixedly connected with fixing axle 13；It is described fixed
Son 122 is contained in the accommodating chamber 1243, so that stator 122 is fixed in fixing axle 13, the stator 122 is the bottom of by
Seat 124 and be fixed in fixing axle 13.
Fig. 4 is refer to, stator 122 is in the cylindrical shape with centre bore, and it includes the inner surface being arranged concentrically and outer surface；
The bottom of stator 122 and the bottom plate 1242 of base 124 are connected, and the outer surface of stator 122 coordinates with the inner surface of base 124
Connection, the inner surface of stator 122 is set in fixing axle 13, and the inner surface of stator 122 and the interval of the outer surface of fixing axle 13
Rotor 123.
Fig. 6 is refer to, rotor 123 is by a top plate 1231, an inner cylinder face plate 1232 and an outside cylinder panel
1233 rotary bodies surrounded, wherein inner cylinder face plate 1232 and outside cylinder panel 1233 are coaxially disposed.Wherein, inner cylinder face plate
1232 are set in fixing axle 13 by bearing 18, are connected so that the rotor 123 is rotated with fixing axle 13；Meanwhile, rotor 123
Stator 122 and base 124 are contained between inner cylinder face plate 1232 and outside cylinder panel 1233, i.e., described rotor 123 it is interior
Cylinder panel 1232 is connected with the inner surface of stator 122, and the outside cylinder panel 1233 of the rotor 123 is and base
What 124 thin cylinder panel 1241 was connected.
In the present embodiment, the upper drive device 12 also includes rotor disk 17；The rotor disk 17 is used to install rotation
The wing 11；The rotor disk 17 is in thin annular shape, and the thin annulus is distributed by axle center of the axis of the fixing axle 13；The rotor disk
On 17 bottom surface and the top plate 1231 of rotor 123, the upper rotor 11 is arranged on the top surface of rotor disk 17.
In the present embodiment, the upper rotor 11 includes two panels blade 111, and two panels blade 111 is symmetrically distributed in rotor disk
On the circumference of 17 top surfaces；In other embodiments, the upper rotor 11 includes at least two panels blade 111, can be 3, four
Or more blades 111, the blade 111 is evenly distributed on the circumference of the top surface of rotor disk 17.
Lower drive device 15 is installed in fixing axle 13；Lower rotor 14 is installed on the output end of lower drive device 15；It is lower to drive
Dynamic device 15 drives lower rotor 14 to be rotated around fixing axle 13.
As can be seen here, derotation wing power set 1 of the present utility model are by the way of coaxial, with traditional anti-rotor power
Device 1 is compared by the way of non co axial, and its manufacturing process is simple, manufacture difficulty and holistic cost are reduced
In the present embodiment, Fig. 3 is refer to, the structure of the lower drive device 15 and upper drive device 12 is designed to
, the mounting means of lower rotor 14 is also the same.
In the present embodiment, the way circuit of aircraft 3 by the output end of cable 16 control respectively upper drive device 12 and
Lower drive device 15, so that the steering of up-down drive device 15 is identical or on the contrary, so that upper rotor 11 and backspin
Steering between the wing 14 is identical or on the contrary, so as to be supplied to the lift that aircraft 3 rises.
In the present embodiment, the tandem type derotation wing power set include two sets of derotation wing power set 1, i.e. this implementation
The tandem type derotation wing power set of example can produce twice of above-mentioned lift, and the derotation wing power set 1 itself
The gravity of generation is much smaller than the size of the lift of its generation, i.e., described tandem type derotation wing power set include anti-rotor power and filled
The tricks for putting 1 is more, just can produce bigger lift to aircraft 3.Therefore, the tandem type derotation wing power set of this case are supported
The tandem type extension of power set, realizes the linear expansion of power performance, this feature breaches traditional anti-rotor power
Device 1 does not possess the situation that power performance linearly expands.
The tandem type derotation wing power set also include safety device 2；Fig. 3 is refer to, the safety device 2 is arranged on
The top of fixing axle 13.
Specifically, refer to Fig. 2, the safety device 2 includes parachute 21 and parachute storage device 22；The landing
Umbrella storage device 22 is arranged on the top of fixing axle 13；The parachute 21 has the collecting for being contained in parachute storage device 22
State, and parachute 21 are deployed in the deployed condition for making aircraft 3 slow down on fixing axle 13.
Preferably, the parachute storage device 22 can be according to the work of the speed, posture and power set of aircraft 3
The factors such as state, are independently judged or according to artificial operational order, are discharged and are released a parachute 21, to ensure that aircraft 3 is pacified
It is high-fall fall.
Preferably, parachute 21 is to utilize air drag principle, by relative to air movement, inflating expanded expandable
Aerodynamic decel erator.
The design of safety device 2 in this case, is that aircraft 3 devises independent, high reliability, high security complete machine
Safety equipment, and highly merged with the nucleus equipment derotation wing power set 1 of aircraft 3, so as to reach the safety of aircraft 3
The new high degree of property.
Certainly, the utility model can also have other numerous embodiments, based on present embodiment, the ordinary skill of this area
Personnel obtain other embodiment on the premise of any creative work is not made, and belong to the utility model and are protected
Scope.
Claims (8)
1. a kind of tandem type derotation wing power set, it is characterised in that including derotation wing power set (1)；
Derotation wing power set (1) include upper rotor (11), lower rotor (14), upper drive device (12), lower drive device (15)
And fixing axle (13)；
Upper drive device (12) is installed in fixing axle (13)；Upper rotor (11) is installed on the output end of drive device (12)；
Rotor (11) is rotated around fixing axle (13) in upper drive device (12) drive；
Lower drive device (15) is installed in fixing axle (13)；Lower rotor (14) is installed on the output end of lower drive device (15)；
Lower drive device (15) drives lower rotor (14) to be rotated around fixing axle (13).
2. tandem type derotation wing power set according to claim 1, it is characterised in that the bottom of the fixing axle (13)
Top installed in aircraft (3)；The center of the fixing axle (13) is provided with the routing hole through whole fixing axle (13)；Wiring
Cable (16) is provided with hole；The input of cable (16) is connected with the way circuit of aircraft (3), in the output end of cable (16) simultaneously
It is associated with the upper drive device (12) and lower drive device (15) of derotation wing power set (1).
3. tandem type derotation wing power set according to claim 2, it is characterised in that upper drive device (12) bag
Include coil, stator (122) and rotor (123)；Stator (122) and rotor (123) are distributed by axle center of the axis of fixing axle (13)；
Rotor (123) and fixing axle (13) are rotated and are connected, and stator (122) is fixedly connected with fixing axle (13), and coil is around being located at stator
(122) on, coil is electrically connected with the output end of cable (16)；Rotor (123) produces relative in coil electricity with stator (122)
Motion, and rotor (11) is rotated around fixing axle (13) in rotor (123) drive.
4. tandem type derotation wing power set according to claim 3, it is characterised in that upper drive device (12) also includes
Base (124)；The base (124), which is one, has the framework of accommodating chamber (1243)；Base (124) is fixed with fixing axle (13)
Connection；The stator (122) is contained in the accommodating chamber (1243), so that stator (122) is fixed on fixing axle (13).
5. tandem type derotation wing power set according to claim 4, it is characterised in that the upper drive device (12) is also
Including rotor disk (17)；The rotor disk (17) is used to install rotor (11)；The rotor disk (17) is in thin annular shape, and this is thin
Annulus is distributed by axle center of the axis of the fixing axle (13)；The rotor disk (17) is arranged on rotor (123) top, described
Upper rotor (11) is arranged on the top surface of rotor disk (17).
6. tandem type derotation wing power set according to claim 5, it is characterised in that the upper rotor (11) is included extremely
Few two panels blade (111).
7. tandem type derotation wing power set according to claim 2, it is characterised in that the anti-rotor power of tandem type
Device also includes safety device (2)；The safety device (2) is arranged on the top of fixing axle (13).
8. tandem type derotation wing power set according to claim 3, it is characterised in that the safety device (2) includes
Parachute (21) and parachute storage device (22)；The parachute storage device (22) is arranged on the top of fixing axle (13)；
The parachute (21) has the housed state for being contained in parachute storage device (22), and parachute (21) is deployed in fixing axle
(13) deployed condition of aircraft down is made on.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621348549.0U CN206466172U (en) | 2016-12-09 | 2016-12-09 | A kind of tandem type derotation wing power set |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621348549.0U CN206466172U (en) | 2016-12-09 | 2016-12-09 | A kind of tandem type derotation wing power set |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206466172U true CN206466172U (en) | 2017-09-05 |
Family
ID=59709160
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621348549.0U Expired - Fee Related CN206466172U (en) | 2016-12-09 | 2016-12-09 | A kind of tandem type derotation wing power set |
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| Country | Link |
|---|---|
| CN (1) | CN206466172U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106697277A (en) * | 2016-12-09 | 2017-05-24 | 周欣 | Cascading style reverse rotor power device |
-
2016
- 2016-12-09 CN CN201621348549.0U patent/CN206466172U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106697277A (en) * | 2016-12-09 | 2017-05-24 | 周欣 | Cascading style reverse rotor power device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170905 Termination date: 20171209 |