CN209427022U - Rotatory beta structure of aircraft rotor - Google Patents
Rotatory beta structure of aircraft rotor Download PDFInfo
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- CN209427022U CN209427022U CN201822213022.2U CN201822213022U CN209427022U CN 209427022 U CN209427022 U CN 209427022U CN 201822213022 U CN201822213022 U CN 201822213022U CN 209427022 U CN209427022 U CN 209427022U
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- rotor
- fixed seat
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- limiting fixed
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- 238000000034 method Methods 0.000 abstract description 4
- 230000007246 mechanism Effects 0.000 description 46
- 238000006073 displacement reaction Methods 0.000 description 33
- 238000010586 diagram Methods 0.000 description 5
- 230000000630 rising effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000009795 derivation Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
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Abstract
The utility model discloses a rotatory beta structure of aircraft rotor relates to unmanned air vehicle technique field. The rotary folding structure of the aircraft rotor wing comprises a rotor wing paddle clamping seat and a limiting fixed seat; one end of the rotor wing paddle holder is used for rotatably connecting a rotor wing blade, and the rotor wing blade can rotate relative to the rotor wing paddle holder and is used for realizing the folding of the rotor wing blade relative to the airframe; the other end of rotor oar holder is connected on spacing fixing base, and rotor oar holder can slide and rotate for spacing fixing base for realize rotor blade's attitude adjustment. The utility model discloses a rotatory beta structure of aircraft rotor for rotor blade's inclination itself can obtain the adjustment, has strengthened the adjustment ability of flight gesture, and unmanned aerial vehicle's flight stability obtains guaranteeing effectively, and, make rotor blade can be folding for the fuselage, insert the fuselage seam after rotor blade is folding, improved unmanned aerial vehicle's portability and ease for use, solved current unmanned aerial vehicle space and taken big problem.
Description
Technical field
The utility model relates to air vehicle technique fields, more particularly to a kind of aircraft rotor rotary folding structure.
Background technique
Existing unmanned plane flies unstable, is easy to be affected by the wind, and space hold is larger, it has not been convenient to carry.
Utility model content
The purpose of this utility model is to provide a kind of aircraft rotor rotary folding structures, to solve to deposit in the prior art
The big technical problem of unmanned plane space hold.
To achieve the goals above, the utility model uses following technical scheme:
A kind of aircraft rotor rotary folding structure provided by the utility model, including rotor holder and limit are fixed
Seat；
For being rotatablely connected rotor blade, the rotor blade can be relative to the rotation for one end of the rotor holder
The rotation of wing paddle holder, the folding for realizing rotor blade relative to fuselage；
The other end of the rotor holder is connected on the limiting fixed seat, and the rotor holder can be relative to
The limiting fixed seat sliding and rotation, for realizing the pose adjustment of rotor blade.
Further, the other end of the rotor holder is connected on the limiting fixed seat by sliding bearing.
Further, retaining spring is provided between the rotor holder and the limiting fixed seat；
The retaining spring is used to limit the relative position of the rotor holder and the limiting fixed seat.
Further, the retaining spring is socketed on the sliding bearing；
One end of the retaining spring is connect with the rotor holder, the other end of the retaining spring and the limit
Fixing seat connection.
Further, the rotor holder includes limiting slot and rotating base；
One end of the rotating base is arranged in the limiting slot；
The rotating base is socketed on the limiting fixed seat.
Further, the rotating base is socketed the rotating base on the limiting fixed seat by sliding bearing
It can slide and rotate relative to the limiting fixed seat.
Further, the rotor holder further includes position limit arm；
The other end of the rotating base is arranged in the position limit arm, and the position limit arm exists for limiting the rotating base
Range on the limiting fixed seat.
Further, the other end of the rotor holder is connected on the limiting fixed seat, the limiting fixed seat
It is connected on propeller hub.
Further, the propeller hub is arranged on fuselage by central axis, and the propeller hub can turn on the central axis
It is dynamic.
Further, rotor brushless motor is provided on the central axis；
The rotor brushless motor realizes the rotor blade phase for driving the propeller hub to rotate on the central axis
Fuselage is rotated.
Aircraft rotor rotary folding structure provided by the utility model, enables the tilt angle of rotor blade itself
It is adjusted, strengthens the adjustment capability of flight attitude, so that the flight stability of unmanned plane is effectively ensured, also,
Rotor blade is folded relative to fuselage, rotor blade is inserted into fuselage seam after folding, and improves unmanned plane just
The property taken and ease for use solve the problems, such as that existing unmanned plane space hold is big.
Detailed description of the invention
It, below will be right in order to illustrate more clearly of specific embodiment of the present invention or technical solution in the prior art
Specific embodiment or attached drawing needed to be used in the description of the prior art are briefly described, it should be apparent that, it is described below
In attached drawing be that some embodiments of the utility model are not paying creativeness for those of ordinary skill in the art
Under the premise of labour, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is a kind of overall structure diagram of portable aircraft provided by the embodiment of the utility model；
Fig. 2 is a kind of overall structure diagram of portable aircraft provided by the embodiment of the utility model；
Fig. 3 is a kind of partial structurtes signal of aircraft rotor rotary folding structure provided by the embodiment of the utility model
Figure；
Fig. 4 is a kind of partial structurtes signal of aircraft rotor rotary folding structure provided by the embodiment of the utility model
Figure；
Fig. 5 is a kind of partial structure diagram of portable aircraft provided by the embodiment of the utility model；
Fig. 6 is a kind of partial structure diagram of portable aircraft provided by the embodiment of the utility model；
Fig. 7 is a kind of partial structure diagram of portable aircraft provided by the embodiment of the utility model；
Fig. 8 is a kind of part-structure signal of aircraft rotor rotary folding structure provided by the embodiment of the utility model
Figure.
Appended drawing reference:
000- fuselage；100- rotor mechanism；200- wing drop pitch-changing mechanism；300- folding and unfolding lift；
110- rotor blade；120- aircraft rotor rotary folding structure；130- propeller hub；140- rotor brushless motor；
210- displacement connecting rod；220- displacement rotates outer ring；230- displacement steering engine；240- rocker arm；250- displacement rotates inner ring；
310- rises and falls steering engine；320- folding and unfolding sliding block；340- anti-slip part；
410- synchronising (connecting) rod；
121- rotor holder；122- limiting fixed seat；123- sliding bearing；124- retaining spring；
331- first connecting rod；332- second connecting rod；333- third connecting rod；334- fourth link；The 5th connecting rod of 335-；336-
Six-bar linkage；337- support link；
1211- limiting slot；1212- rotating base；1213- position limit arm.
Specific embodiment
The technical solution of the utility model is clearly and completely described below in conjunction with attached drawing, it is clear that described
Embodiment is the utility model a part of the embodiment, instead of all the embodiments.Based on the embodiments of the present invention, originally
Field those of ordinary skill every other embodiment obtained without making creative work belongs to practical
Novel protected range.
It is in the description of the present invention, it should be noted that term " center ", "upper", "lower", "left", "right", " perpendicular
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" is to be based on the orientation or positional relationship shown in the drawings, and is only
For ease of description the utility model and simplify description, rather than the device or element of indication or suggestion meaning must have it is specific
Orientation, be constructed and operated in a specific orientation, therefore should not be understood as limiting the present invention.In addition, term " the
One ", " second ", " third " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " is pacified
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
The concrete meaning of language in the present invention.
Embodiment one:
In the optinal plan of the present embodiment, as shown in figure 3, a kind of aircraft rotor rotary folding provided in this embodiment
Structure, including rotor holder 121 and limiting fixed seat 122；
For being rotatablely connected rotor blade 110, rotor blade 110 can be relative to rotor for one end of rotor holder 121
Paddle holder 121 rotates, the folding for realizing rotor blade 110 relative to fuselage 000；
The other end of rotor holder 121 is connected on limiting fixed seat 122, and rotor holder 121 can be relative to limit
The position sliding of fixing seat 122 and rotation, for realizing the pose adjustment of rotor blade 110.
In the optinal plan of the present embodiment, the other end of rotor holder 121 is connected to limit by sliding bearing 123
In fixing seat 122.
In the optinal plan of the present embodiment, retaining spring is provided between rotor holder 121 and limiting fixed seat 122
124；
Retaining spring 124 is used to limit the relative position of rotor holder 121 Yu limiting fixed seat 122.
In the optinal plan of the present embodiment, retaining spring 124 is socketed on sliding bearing 123；
One end of retaining spring 124 is connect with rotor holder 121, the other end and limiting fixed seat of retaining spring 124
122 connections.
In the optinal plan of the present embodiment, as shown in figure 8, rotor holder 121 includes limiting slot 1211 and rotation base
Seat 1212；
One end of rotating base 1212 is arranged in limiting slot 1211；
Rotating base 1212 is socketed on limiting fixed seat 122.
In the optinal plan of the present embodiment, rotating base 1212 is socketed in limiting fixed seat 122 by sliding bearing 123
On, rotating base 1212 can be slided and be rotated relative to limiting fixed seat 122.
In the optinal plan of the present embodiment, rotor holder 121 further includes position limit arm 1213；
The other end of rotating base 1212 is arranged in position limit arm 1213, and position limit arm 1213 exists for limiting rotating base 1212
Range on limiting fixed seat 122.
In the optinal plan of the present embodiment, fixed as shown in figure 4, the other end of rotor holder 121 is connected to limit
On seat 122, limiting fixed seat 122 is connected on propeller hub 130.
In the optinal plan of the present embodiment, propeller hub 130 is arranged on fuselage 000 by central axis, and propeller hub 130 can be
It is rotated on central axis.
Rotor brushless motor 140 is provided in the optinal plan of the present embodiment, on central axis；
Rotor brushless motor 140 realizes rotor blade 110 relative to machine for driving propeller hub 130 to rotate on center shaft
Body 000 rotates.
Embodiment two:
In the optinal plan of the present embodiment, as shown in Fig. 1 to Fig. 2, Fig. 5 to Fig. 7, one kind provided in this embodiment is portable
Formula aircraft, comprising:
Rotor mechanism 100, rotor mechanism 100 include rotor blade 110, propeller hub 130 and the flight as described in embodiment one
Device rotor wing rotation foldable structure 120；Rotor blade 110 is arranged by aircraft rotor rotary folding structure 120 in propeller hub 130
On, rotor blade 110 can relative to aircraft rotor rotary folding structure 120 rotate with realize rotor blade 110 relative to
The folding of fuselage 000；Propeller hub 130 is arranged on fuselage 000 by central axis, and propeller hub 130 can rotate on center shaft and phase
For inclined；Rotor brushless motor 140 is provided on central axis, rotor brushless motor 140 is for driving propeller hub 130 to exist
It is rotated on central axis, so that rotor blade 110 be driven to rotate relative to fuselage 000；
Wing drop pitch-changing mechanism 200, on the centrally disposed axis of wing drop pitch-changing mechanism 200, wing drop displacement machine
Structure 200 can be rotated synchronously with rotor mechanism 100, and wing drop pitch-changing mechanism 200 is for controlling rotor mechanism 100 relative in
Spindle tilt；Wing drop pitch-changing mechanism 200 includes displacement connecting rod 210, displacement rotation outer ring 220 and displacement steering engine 230；Displacement
On the centrally disposed axis of steering engine 230, displacement steering engine 230 can be with rotating on center shaft；Displacement rotates outer ring 220 and is arranged in
In mandrel, displacement rotation outer ring 220 can rotate on center shaft, and displacement rotates outer ring 220 and passes through rocker arm 240 and displacement steering engine
230 connections, displacement steering engine 230 can drive displacement to rotate outer ring 220 relative to inclined by rocker arm 240；Displacement connects
On displacement rotation outer ring 220, the other end of displacement connecting rod 210 is arranged on propeller hub 130 for one end setting of bar 210；
Folding and unfolding lift 300, including the steering engine 310 that rises and falls, folding and unfolding sliding block 320, movable rod component and anti-slip part 340；
Folding and unfolding sliding block 320 is arranged in 000 bottom of fuselage, and folding and unfolding sliding block 320 can be slided relative to fuselage 000；Movable rod component
One end is arranged on folding and unfolding sliding block 320, and the other end of movable rod component is arranged in anti-slip part 340；The steering engine 310 that rises and falls setting exists
On fuselage 000, the steering engine 310 that rises and falls is for driving folding and unfolding sliding block 320 to slide on center shaft, so that movable rod component phase
Fuselage 000 is unfolded or is collapsed；
Gondola installing mechanism, setting are used for link block gondola in 000 bottom of fuselage；
Battery modules mechanism is arranged on fuselage 000；Battery modules mechanism includes intelligent battery group, and intelligent battery group is used
In for the rotor brushless motor 140 of rotor mechanism 100, the displacement steering engine 230 of wing drop pitch-changing mechanism 200 and folding and unfolding alighting gear
The power supply of steering engine 310 of rising and falling of structure 300；
Central control mechanism, at the same with battery modules mechanism and rotor brushless motor 140, displacement steering engine 230 and the rudder that rises and falls
Machine 310 is electrically connected；Central control mechanism is for controlling rotor brushless motor 140, displacement steering engine 230 and 310 work of steering engine of rising and falling
Make；
Wherein, the quantity of rotor mechanism 100 is 2, is arranged on fuselage 000 by central axis；2 rotor mechanisms
100 settings symmetrical above and below, the rotor brushless motor 140 of one of rotor mechanism 100 and the rotor of another rotor mechanism 100
Brushless motor 140 is coaxial oppositely arranged；
The quantity of wing drop pitch-changing mechanism 200 is 2, is connect respectively with 2 rotor mechanisms 100；2 wing drops become
It is connected between spacing mechanism 200 by synchronization mechanism；
The quantity of intelligent battery group is 2, and respectively 2 rotor mechanisms 100 are powered, while respectively 2 wing drops
Pitch-changing mechanism 200 is powered.
In the present embodiment, 2 100 coaxial-symmetrical of rotor mechanism settings, 2 rotor brushless motors 140 are oppositely arranged, make
The ability for obtaining this aircraft resistance wind-force is stronger, significantly reduces influence of the wind-force to flight, flies more steady, automatic
Under the action of tilting pitch-changing mechanism 200, the 110 expansion amplitude of rotor blade of rotor mechanism 100 can be controlled, so that this flies
The flight attitude of row device can be adjusted, meanwhile, the setting of aircraft rotor rotary folding structure 120, so that rotor blade
110 tilt angles itself can be also adjusted, and further enhance the adjustment capability of flight attitude, so that this aircraft
Flight stability is effectively ensured, also, the setting of aircraft rotor rotary folding structure 120, so that rotor blade 110
It can be folded relative to fuselage 000, rotor blade 110 is inserted into 000 seam of fuselage after folding, and is reduced this aircraft and is not used
When space hold, convenient for storage and transport etc., improve the portability and ease for use of this aircraft.
In the present embodiment, wing drop pitch-changing mechanism 200 deflects, and rotor blade 110 is made to generate feathering, realizes and flies
The control of the control of the flight attitude of row device, flight attitude is more flexible.
In the optinal plan of the present embodiment, aircraft rotor rotary folding structure 120 includes rotor holder 121 and limit
Position fixing seat 122；Rotor blade 110 is rotatably connected on one end of rotor holder 121, and rotor blade 110 can be relative to rotation
Wing paddle holder 121 rotates, and realizes folding of the rotor blade 110 relative to fuselage 000；The other end of rotor holder 121 connects
On limiting fixed seat 122, rotor holder 121 can be slided and be rotated relative to limiting fixed seat 122, realize rotor blade
110 pose adjustment.
In the optinal plan of the present embodiment, the other end of rotor holder 121 is connected to limit by sliding bearing 123
In fixing seat 122.
In the present embodiment, the setting of sliding bearing 123 enables rotor holder 121 relative to limiting fixed seat
122 are slided and are rotated, and structure is simple, the operation is stable.
In the optinal plan of the present embodiment, retaining spring is provided between rotor holder 121 and limiting fixed seat 122
124, retaining spring 124 is used to limit the relative position of rotor holder 121 Yu limiting fixed seat 122.
In the optinal plan of the present embodiment, retaining spring 124 is socketed on sliding bearing 123, and the one of retaining spring 124
End is connect with rotor holder 121, and the other end of retaining spring 124 is connect with limiting fixed seat 122.
In the present embodiment, sliding bearing 123 and 124 mating reaction of retaining spring, by rotor after the expansion of rotor blade 110
Blade 110 is locked, guarantees that in flight course be not in safety accident.
In the optinal plan of the present embodiment, rotor holder 121 includes limiting slot 1211, rotating base 1212 and limit
Arm 1213；One end of rotating base 1212 is arranged in limiting slot 1211；The another of rotating base 1212 is arranged in position limit arm 1213
End, position limit arm 1213 is for limiting range of the rotating base 1212 on limiting fixed seat 122；Rotating base 1212 passes through
Sliding bearing 123 is socketed on limiting fixed seat 122, and rotating base 1212 can slide and turn relative to limiting fixed seat 122
It is dynamic.
In the optinal plan of the present embodiment, movable rod component includes sequentially connected first connecting rod 331, second connecting rod
332 and third connecting rod 333；First connecting rod 331 is connected to 000 bottom of fuselage, and anti-slip part 340 is connected on third connecting rod 333.
In the optinal plan of the present embodiment, movable rod component further includes fourth link 334, the 5th connecting rod 335 and
Six-bar linkage 336；One end of fourth link 334 is connected on first connecting rod 331, and the other end of fourth link 334 is connected to the 5th
On connecting rod 335, one end of the 5th connecting rod 335 is connected on second connecting rod 332, and the other end of the 5th connecting rod 335 is connected to the 6th
One end of connecting rod 336, the other end of six-bar linkage 336 are connected on third connecting rod 333.
It in the present embodiment, further include support link 337, one end of support link 337 is connected to the bottom of fuselage, support
The other end of connecting rod 337 is connected to the one end of fourth link 334 being connected with first connecting rod 331.
In the present embodiment, when the steering engine 310 that rises and falls drives 320 upward sliding of folding and unfolding sliding block, first connecting rod 331 is to moving up
Dynamic, support link 337 is rotated up, and the angle between first connecting rod 331 and support link 337 incrementally increases, and is located towards same
One straight line, fourth link 334 are rotated up, and drive second connecting rod 332 to be rotated up, fourth link 334 is leaned on second connecting rod 332
Closely, close up, drive the 5th connecting rod 335 to close up with third connecting rod 333, so that movable rod component integrally collapses；Reverse-direction derivation can
The expansion process for learning movable rod component, repeats no more.
Wherein, the steering engine 310 that rises and falls is arranged on folding and unfolding sliding block 320, and the steering engine 310 that rises and falls drives folding and unfolding sliding block 320 at center
It is slided on axis.
In the present embodiment, the guarantee aircraft of folding and unfolding lift 300 is in the steady landing of complex road surface, when being furnished with gondola,
Pod equipment is protected, and reduces flight resistance in flight.
In the optinal plan of the present embodiment, synchronization mechanism includes synchronising (connecting) rod 410；One end of synchronising (connecting) rod 410 and its
In the displacement rotation outer ring 220 of wing drop pitch-changing mechanism 200 connect, the other end of synchronising (connecting) rod 410 and another from
The displacement rotation outer ring 220 of dynamic inclination pitch-changing mechanism 200 connects.
In the present embodiment, synchronization mechanism enables 2 wing drop pitch-changing mechanisms 200 to rotate synchronously with central axis；
Synchronization mechanism is semirigid structure, keeps aircraft flight more steady, improves flight continuation of the journey, lifting capacity.
In the present embodiment, the quantity of synchronising (connecting) rod 410 is multiple, is uniformly distributed, so that 2 wing drop pitch-changing mechanisms
200 synchronism is more stable.
In the optinal plan of the present embodiment, wing drop pitch-changing mechanism 200 further includes displacement rotation inner ring 250；Displacement
Rotation inner ring 250 is fixedly connected with displacement rotation outer ring 220；One end of rocker arm 240 is connect with displacement rotation inner ring 250, rocker arm
240 other end is connect with displacement steering engine 230.
In the present embodiment, displacement rotation inner ring 250 setting so that wing drop pitch-changing mechanism 200 have it is bigger
Working space nargin can more efficiently play the role of controlling flight attitude.
In the present embodiment, displacement rotation inner ring 250, displacement rotation outer ring 220 and displacement steering engine 230 can be wholely set,
On center shaft by the structure setting of flexible connector and bearing fit, concretely on the centrally disposed axis of bearing, elasticity
Connector is socketed on the outer wall of bearing, to realize inclination；Flexible connector can be spring or elastic washer etc..
In the optinal plan of the present embodiment, 2 intelligent battery groups are separately positioned on the top and bottom of fuselage 000；Position
Intelligent battery group in 000 top of fuselage is that the rotor brushless motor 140 of top and wing drop pitch-changing mechanism 200 are powered, position
Intelligent battery group in 000 bottom of fuselage is that the rotor brushless motor 140 of lower section and wing drop pitch-changing mechanism 200 are powered.
In the present embodiment, 2 intelligent battery groups are provided separately up and down, enhance the structural symmetry of aircraft entirety,
It is beneficial to the stabilized flight of aircraft, and simplifies line configuring, is also convenient for detecting respectively, replace.
It should be noted that this aircraft further includes gondola installing mechanism；Gondola installing mechanism includes load portion, for hanging
Connect gondola, wherein gondola can be modularization freight house, be convenient for quick despatch.
Also, SOS alarm is installed on gondola installing mechanism, is made a sound when beyond specified counterweight and optical alert.
Finally, it should be noted that the above various embodiments is only to illustrate the technical solution of the utility model, rather than it is limited
System；Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should
Understand: it is still possible to modify the technical solutions described in the foregoing embodiments, or to some or all of
Technical characteristic is equivalently replaced；And these are modified or replaceed, it does not separate the essence of the corresponding technical solution, and this is practical new
The range of each embodiment technical solution of type.
Claims (10)
1. a kind of aircraft rotor rotary folding structure, which is characterized in that including rotor holder and limiting fixed seat；
For being rotatablely connected rotor blade, the rotor blade can be relative to the rotor for one end of the rotor holder
Holder rotation, the folding for realizing rotor blade relative to fuselage；
The other end of the rotor holder is connected on the limiting fixed seat, and the rotor holder can be relative to described
Limiting fixed seat sliding and rotation, for realizing the pose adjustment of rotor blade.
2. aircraft rotor rotary folding structure according to claim 1, which is characterized in that the rotor holder it is another
One end is connected on the limiting fixed seat by sliding bearing.
3. aircraft rotor rotary folding structure according to claim 2, which is characterized in that the rotor holder and institute
It states and is provided with retaining spring between limiting fixed seat；
The retaining spring is used to limit the relative position of the rotor holder and the limiting fixed seat.
4. aircraft rotor rotary folding structure according to claim 3, which is characterized in that the retaining spring is socketed in
On the sliding bearing；
One end of the retaining spring is connect with the rotor holder, and the other end of the retaining spring and the limit are fixed
Seat connection.
5. aircraft rotor rotary folding structure according to claim 1, which is characterized in that the rotor holder includes
Limiting slot and rotating base；
One end of the rotating base is arranged in the limiting slot；
The rotating base is socketed on the limiting fixed seat.
6. aircraft rotor rotary folding structure according to claim 5, which is characterized in that the rotating base passes through cunning
Dynamic bearing is socketed on the limiting fixed seat, and the rotating base can be slided and be rotated relative to the limiting fixed seat.
7. aircraft rotor rotary folding structure according to claim 5, which is characterized in that the rotor holder also wraps
Include position limit arm；
The other end of the rotating base is arranged in the position limit arm, and the position limit arm is for limiting the rotating base described
Range on limiting fixed seat.
8. aircraft rotor rotary folding structure according to claim 1, which is characterized in that the rotor holder it is another
One end is connected on the limiting fixed seat, and the limiting fixed seat is connected on propeller hub.
9. aircraft rotor rotary folding structure according to claim 8, which is characterized in that the propeller hub passes through central axis
It is arranged on fuselage, the propeller hub can rotate on the central axis.
10. aircraft rotor rotary folding structure according to claim 9, which is characterized in that be arranged on the central axis
There is rotor brushless motor；
The rotor brushless motor for driving the propeller hub to rotate on the central axis, realize the rotor blade relative to
Fuselage rotation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822213022.2U CN209427022U (en) | 2018-12-26 | 2018-12-26 | Rotatory beta structure of aircraft rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822213022.2U CN209427022U (en) | 2018-12-26 | 2018-12-26 | Rotatory beta structure of aircraft rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209427022U true CN209427022U (en) | 2019-09-24 |
Family
ID=67974043
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822213022.2U Expired - Fee Related CN209427022U (en) | 2018-12-26 | 2018-12-26 | Rotatory beta structure of aircraft rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209427022U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111806679A (en) * | 2020-06-19 | 2020-10-23 | 中国科学院地理科学与资源研究所 | Unmanned aerial vehicle re-flying method |
| CN111806681A (en) * | 2020-06-19 | 2020-10-23 | 中国科学院地理科学与资源研究所 | Unmanned aerial vehicle device and unmanned aerial vehicle fly back |
| CN112173098A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Novel control system and method for electric folding and unfolding of rotor wing |
-
2018
- 2018-12-26 CN CN201822213022.2U patent/CN209427022U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111806679A (en) * | 2020-06-19 | 2020-10-23 | 中国科学院地理科学与资源研究所 | Unmanned aerial vehicle re-flying method |
| CN111806681A (en) * | 2020-06-19 | 2020-10-23 | 中国科学院地理科学与资源研究所 | Unmanned aerial vehicle device and unmanned aerial vehicle fly back |
| CN111806681B (en) * | 2020-06-19 | 2022-03-22 | 中国科学院地理科学与资源研究所 | Unmanned aerial vehicle device and unmanned aerial vehicle fly back |
| CN112173098A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Novel control system and method for electric folding and unfolding of rotor wing |
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| 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: 20190924 Termination date: 20201226 |