CN205076046U - Rotor, oar press from both sides and aircraft - Google Patents
Rotor, oar press from both sides and aircraft Download PDFInfo
- Publication number
- CN205076046U CN205076046U CN201520633292.2U CN201520633292U CN205076046U CN 205076046 U CN205076046 U CN 205076046U CN 201520633292 U CN201520633292 U CN 201520633292U CN 205076046 U CN205076046 U CN 205076046U
- Authority
- CN
- China
- Prior art keywords
- propeller hub
- blade
- rotor
- motor
- sliding bar
- Prior art date
- 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.)
- Withdrawn - After Issue
Links
- 238000009434 installation Methods 0.000 claims abstract description 10
- 230000001360 synchronised effect Effects 0.000 claims description 7
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 230000001737 promoting effect Effects 0.000 claims description 2
- 230000001105 regulatory effect Effects 0.000 description 6
- 230000033001 locomotion Effects 0.000 description 5
- 230000036632 reaction speed Effects 0.000 description 3
- 238000000354 decomposition reaction Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000003292 diminished effect Effects 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 239000013536 elastomeric material Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229920002635 polyurethane Polymers 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
- 230000000153 supplemental effect Effects 0.000 description 1
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model provides a (B, ) rotor, oar press from both sides and aircraft (b). The utility model provides a rotor includes propeller hub and two at least paddles, and the paddle is installed on the propeller hub to the common rotation under first motor drives. Be provided with on the propeller hub along its radial set up slide the passageway, the installation end of paddle is provided with and penetrates the slide bar that slides the passageway, provides the elasticity bias voltage device of bias voltage power to the paddle, makes the paddle be close to the axis of propeller hub. The utility model has the advantages of adjustable rotor diameter makes the rotor accelerate the reaction rate that power was adjusted, and the tuning range of power increases.
Description
Technical field
The utility model relates to aircraft field, specifically, relates to a kind of aircraft with rotor.
Background technology
Rotor is the core component that aircraft flight produces lift and actuating force.Rotor is made up of the two panels be connected on propeller hub or multi-disc blade.Blade keeps rotary motion by the moment of torsion from driving engine.Rotor produces the necessary lift of aircraft flight, pulling force and actuating force.The power of aircraft is relevant to blade rotating speed, the blade angle of attack and blade quantity and rotor diameter.
The paddle of existing rotor is fixed on propeller hub, and the adjustment of aircraft power can only be undertaken by regulating blade rotating speed, and rotor speed of response is comparatively slow and the adjustable extent of power is limited.
Summary of the invention
Main purpose of the present utility model is to provide a kind of fast to reaction speed, the rotor that power adjustable extent increases;
Another object of the present utility model is to provide a kind of fast to reaction speed, the oar folder that power adjustable extent increases;
It is fast to reaction speed that another object of the present utility model is to provide a kind of rotor, the aircraft that power adjustable extent increases.
For realizing above-mentioned main purpose, the utility model provides rotor, can be mounted in the frame of aircraft, and comprise propeller hub and at least two blades, blade is arranged on propeller hub, and under the first driven by motor common rotation.Propeller hub is provided with the sliding channel radially arranged, the installation end of blade is provided with the sliding bar penetrating sliding channel, provides the elastic biasing arrangement of biasing force to blade, makes blade near the axis of propeller hub.
From above scheme, when blade rotates, by centrifugal forces affect, blade radially outward can slide along propeller hub, thus makes rotor diameter become large, and the higher then centnifugal force suffered by it of paddle speed is larger, and the degree that blade outwards slides is larger, and the power that rotor produces is larger; When paddle speed diminishes, blade inwardly slides under the partial pressure of elastic biasing arrangement, rotor diameter is diminished, the power that rotor produces diminishes, thus while paddle speed is regulated, rotor diameter is also regulated, rotor is accelerated the speed of response of power adjustment, and the adjustable extent of power increases.
More concrete scheme is, in the end of sliding bar near axis, is provided with scroll wheel, and the axes normal of scroll wheel is in the radial direction of propeller hub, and when sliding bar slides along sliding channel, scroll wheel rolls on propeller hub.
From above scheme, the setting of scroll wheel makes blade have supplemental support, thus the slip of sliding bar in sliding channel is more smooth and easy, accelerates rotor further to the speed of response regulated.
Preferably, propeller hub and blade are provided with the synchronization-moving synchronous device of radial direction making blade along propeller hub.From above scheme, synchronous device can make plural blade simultaneous equal radially outward or move inward, and is conducive to the kinetic balance of rotor.
More particularly, synchronous device is pinion and rack, and its middle gear is arranged on propeller hub, the axis of gear and the dead in line of propeller hub, and the installation end of blade arranges the tooth bar with gears meshing.From above scheme, the movement radially of blade is subject to the restriction of gear and tooth bar engagement, to ensure that blade simultaneous equal moves.
More specifically, the quantity of blade is even number, and blade is provided with the guide frame guiding it along propeller hub blade diametrically, rotor comprises the fairing be arranged on above described propeller hub.From above scheme, blade can be guided by blade corresponding thereto when radially moving, and is conducive to the steady movement of blade further, reduces air-flow resistance.
Another more particularly, rotor also comprises the guide cover be arranged on above propeller hub, and guide cover is provided with the taper inner face in the face of propeller hub, and along propeller hub radial taper inner face gradually near propeller hub, the installation end of blade is provided with the surface that mutually can abut with taper inner face.From above scheme, the restriction moved radially by guide cover of blade, when guide cover is near propeller hub, this surface of blade abuts with the part of the close propeller hub axis of taper inner face, and blade is in curling position, when guide cover is away from propeller hub, this surface of blade abuts with the part away from propeller hub axle of taper inner face, blade is in extended position, and the inclined degree of the taper inner face of guide cover radially relative axis is identical, can ensure each blade radially synchronous equal amount move.
More specifically, guide cover is connected with the second motor, and the second electric machine rotation promotion guide cover moves along the axis of propeller hub.From above scheme, by the distance between the controlled guide cover processed of the second motor and propeller hub, and then the moving radially of adjustable blade, make the stretching, extension of blade and draw in by the second electric machine control, making the adjustment of rotor power more flexible.
Further more specifically, the first motor is hollow shaft motor, and the second motor moves by promoting guide cover through the adapter shaft of the first motor.As seen from the above, by arranging hollow shaft motor, the second motor can be arranged on the below of the first motor and be arranged in frame, makes the flight of the aircraft with this rotor more steady.
For realizing another object, oar folder of the present utility model, can be mounted in the frame of aircraft, comprise propeller hub.Propeller hub, for installing blade, rotates under the first driven by motor.Propeller hub is provided with the sliding channel radially arranged, propeller hub is provided with sliding bar, sliding bar can slide in sliding channel.Elastic biasing arrangement, provides biasing force to sliding bar, makes sliding bar near the axis of propeller hub.As can be seen here, rotor can load and unload on oar folder, and oar folder can install multiple rotor, improves transmission of power performance simultaneously, and power adjustment speed of response is fast, and power adjustable extent increases.
For realizing another object, the utility model provides aircraft, comprises frame and rotor, and rotor is arranged in frame, and wherein rotor is the rotor with said structure.
From above scheme, in aircraft flight process, the rotating speed of its rotor and the length of blade all adjustable, make when carrying out aircraft power and regulating, rotor speed of response is accelerated, and the adjustable extent of power increases.
Accompanying drawing explanation
Fig. 1 is the constructional drawing of the utility model rotor first embodiment;
Fig. 2 is the constructional drawing that the utility model rotor first embodiment blade is in extended configuration, wherein eliminates fairing;
Fig. 3 is the constructional drawing that the utility model rotor first embodiment blade is in rounding state, wherein eliminates fairing;
Fig. 4 is the STRUCTURE DECOMPOSITION figure of the utility model rotor first embodiment, wherein not shown fairing;
Fig. 5 is the constructional drawing of blade in the utility model rotor first embodiment;
Fig. 6 is the STRUCTURE DECOMPOSITION figure of blade in the utility model rotor first embodiment;
Fig. 7 is the constructional drawing of the utility model rotor second embodiment;
Fig. 8 is the constructional drawing of the utility model rotor second embodiment, wherein eliminates fairing;
Fig. 9 is the constructional drawing of the utility model rotor second embodiment, wherein eliminates fairing and spring.
Figure 10 is the constructional drawing of the utility model rotor the 3rd embodiment, wherein eliminates fairing and spring.
Detailed description of the invention
Below in conjunction with drawings and Examples, the utility model is described in further detail.
Rotor first embodiment
As shown in Figure 1, rotor 10 comprises fairing 11, blade 12 and propeller hub 13, motor 14(first motor) be connected with propeller hub 13 and propeller hub 13 can be driven to rotate, fairing 11 and blade 12 are arranged on propeller hub 13, and rotate together with propeller hub 13.Blade 12 is set to two, and along the diametrically setting of propeller hub 13, fairing 11 is arranged on above propeller hub 13.Direction as referred to herein is described according to the frame of reference of schematic structure, namely with the first type surface of propeller hub 13 for horizontal surface, it is direction upwards perpendicular to propeller hub 13 first type surface and away from the direction of the motor driving propeller hub 13 to rotate, in fact this frame of reference can not be united with gravitational frame of reference and be overlapped, when being mounted to frame as faced down when rotor 10, in fact fairing 11 is in the below of gravitational frame of reference.
See Fig. 2 to Fig. 7, the blade 121 that blade 12 comprises sheet, the sliding bar 122 being positioned at blade 12 installation end are fixed with blade 121 through the sliding channel 131 of propeller hub 13, sliding bar 122 is arranged with the spring 123(elastic biasing arrangement that can be a stage clip), one end of spring 123 and sliding bar 122 are near the end abutment of propeller hub axis, the other end abuts with sliding channel 131, thus applies to make blade 12 to the biasing force of propeller hub 13 axis movement to blade 12.Sliding bar 122 is provided with scroll wheel 124 near the end of propeller hub axis, and this scroll wheel 124 freely can rotate around its axis, thus when blade 12 moves radially along propeller hub 13, scroll wheel 124 rolls on the first type surface of propeller hub 13.
Guide cover 15 is arranged on the top of propeller hub 13, propeller hub 13 is provided with four guide rods 132, guide cover 15 is provided with corresponding hole 151 to pass for guide rod 132, thus when guide cover 15 is promoted to move along the axis direction of propeller hub 13 by axle 16, can not produces relative to propeller hub 13 and rotate.Guide cover 15 upper end is provided with erecting stage 152, for being connected with fairing.Guide cover 15 is also provided with the taper inner face 153 for abutting with blade 12, taper inner face 153 shown in figure is circular conical surface, be understandable that, in other embodiments, this taper inner face 153 can be corresponding with blade quantity or is multiple inclined-planes of blade quantity integral multiple, and the plurality of inclined-plane is consistent relative to the angle of inclination of propeller hub 13.
The sliding bar 122 of blade 12 is set near the end of propeller hub axis vertical with sliding bar 122 and divides the vertical rod 125 standing in sliding bar both sides, and the end face of vertical rod 125 is inclined-plane, and can abut with the taper inner face 153 of guide cover 15.Blade 121 is fixed together with sliding bar 122 by laying respectively at the fixed leg 127,128 at sliding bar 122 two ends.
Guide cover 15 is connected with the upper end 161 of axle 16, the lower end of axle 16 is provided with threaded interior hole 162, can with motor 17(second motor) drive rotating screw bolt (not shown) to engage, and these threaded interior hole 162 both sides are provided with fluting, this fluting can engage with a position limiting structure, and during to make bolt rotary, impeller-hub 161 moves axially and can not with bolt rotary.Wherein motor 14 is set to hollow shaft motor, and axle 16 or screw rod can through the centers of motor 14.
Before rotor 10 works, due to the partial pressure of spring 123, blade 12 is in curling position, and now, inclined-plane 126 can not abut with the taper inner face 153 of guide cover 15.When rotor 10 works, motor 14 drives blade 12 and propeller hub 13 to rotate, blade 12 is outwards stretched from curling position by the biasing force overcoming spring 123 under centrifugal action, until inclined-plane 126 abuts with taper inner face 153, taper inner face 153 limits moving radially of blade 12, and make blade 12 remain on this position, when making guide cover 15 move up by motor 17 adjustment, blade 12 radially outward slides, blade 12 is stretched further, until inclined-plane 126 again abut with taper inner face 153 and limit it and stretch further.Regulated by motor 17 guide cover 15 is moved down time, taper inner face 153 keeps abutting with inclined-plane 126 and promotes inclined-plane 126 and radially-inwardly moves.When rotor 10 stops operating, under the partial pressure of spring 123, blade 12 returns back to curling position.
In its variants: the first motor can not be hollow shaft motor, and now the second motor can be arranged on the top of propeller hub; It is plane that the top of vertical rod also can be set to cambered surface, as long as can ensure that this surface is smoothly mobile along taper inner face; The quantity of blade can be and is different from two multiple; The quantity of guide rod also can be different from four multiple; Also can without the need to arranging scroll wheel; Elastic biasing arrangement can be other spring installations etc.
Rotor second embodiment
As shown in Figure 7 to 9, rotor 20 comprises fairing 21, blade 22 and propeller hub 23, motor 24(first motor) be connected with propeller hub 23 and propeller hub 23 can be driven to rotate, fairing 21 and blade 22 are arranged on propeller hub 23, and rotate together with propeller hub 23.Blade 22 is set to two, and along the diametrically setting of propeller hub 23, fairing 21 is arranged on above propeller hub 23.
The blade 221 that blade 22 comprises sheet, the sliding bar 222 being positioned at blade 22 installation end are fixed with blade 221 through the sliding channel 231 of propeller hub 23, the two ends that can be the spring 223 of an extension spring are connected with two blades 22 respectively, thus apply to make blade 22 to the biasing force of propeller hub 23 axis movement to blade 22.Sliding bar 222 is provided with scroll wheel 224 near the end of propeller hub 23 axis, and this scroll wheel 224 freely can rotate around its axis, thus when blade 22 moves radially along propeller hub, scroll wheel 224 rolls on the first type surface of propeller hub 23.
The center of propeller hub 23 is provided with the gear 232 that freely can rotate around axis, the end of sliding bar 222 is provided with horizontal fixed link 225, the side of horizontal fixed link 225 is provided with the tooth bar 226 stretched out to opposite blade 22 and the guide rod 227 being positioned at tooth bar 226 top, and opposite side is provided with the through hole of guide rod 227 insertion for opposite blade 22.Two tooth bars 226 are all meshed with gear 232.Thus ensure the synchronism that two tooth bars 226 move radially along propeller hub, namely simultaneously inside or simultaneously outside.
Before rotor 20 works, due to the partial pressure of spring 223, blade 22 is in curling position.When rotor 20 works, motor 24 drives blade 22 and propeller hub 23 to rotate, blade 22 is outwards stretched from curling position by the biasing force overcoming spring 223 under centrifugal action, the engagement of gear 232 and tooth bar 226 makes two blade 22 synchronous equal amounts radially outward move, the rotating speed of rotor 20 is larger, and the extension degree of blade 22 is larger, when the rotating speed of rotor 20 diminishes, blade 22 radially-inwardly moves under spring 223 partial pressure, until the biasing force of spring 223 and centnifugal force balance.When rotor 20 stops operating, under the partial pressure of spring 223, blade 22 returns back to curling position.
In its variants: gear by the second electric machine control its rotate, with realize to blade move radially from main regulation; The quantity of blade can be and is different from two multiple, and gear is meshed to prevent each tooth bar from being formed interferes with the tooth bar being positioned at different level; Guide rod can be fixed on horizontal fixed link, and in section of rack providing holes, guide rod is penetrated; Also can without the need to arranging scroll wheel or guide rod; Etc..
Rotor the 3rd embodiment:
As shown in Figure 10, the present embodiment is substantially identical with other example structure, difference is: minimumly at the two ends, left and right of sliding channel 231 be respectively equipped with a bumpar post 301, and bumpar post 301 is arranged with cushion collar 302, this cushion collar 302 is made up of rubber or polyurethane elastomeric material.
Aircraft embodiment
Aircraft comprises frame and rotor, and rotor is arranged in frame, and rotates to provide power to aircraft under driven by motor, and wherein rotor can have the structure in above-mentioned rotor embodiment.
Claims (10)
1. rotor, can be mounted in the frame of aircraft, comprises the blade of propeller hub and at least two, and described blade is arranged on described propeller hub, and under the first driven by motor common rotation;
It is characterized in that:
Described propeller hub is provided with the sliding channel radially arranged, the installation end of described blade is provided with the sliding bar penetrating described sliding channel;
Elastic biasing arrangement, provides biasing force to described blade, makes described blade near the axis of described propeller hub.
2. rotor according to claim 1, is characterized in that:
In the end of described sliding bar near described axis, be provided with scroll wheel, the axes normal of described scroll wheel is in the radial direction of described propeller hub, and when described sliding bar slides along described sliding channel, described scroll wheel rolls on described propeller hub.
3. rotor according to claim 1 and 2, is characterized in that:
Described propeller hub and described blade are provided with the synchronization-moving synchronous device of radial direction making described blade along described propeller hub.
4. rotor according to claim 3, is characterized in that:
Described synchronous device is pinion and rack, and its middle gear is arranged on described propeller hub, the axis of described gear and the dead in line of described propeller hub, and the installation end of described blade arranges the tooth bar with described gears meshing.
5. rotor according to claim 4, is characterized in that:
The quantity of described blade is even number, described blade is provided with the guide frame guiding it along described propeller hub blade diametrically; Described rotor comprises the fairing be arranged on above described propeller hub.
6. rotor according to claim 3, is characterized in that:
Described rotor also comprises the guide cover be arranged on above described propeller hub, described guide cover is provided with the taper inner face in the face of described propeller hub, and it is radial along described propeller hub, described taper inner face is gradually near described propeller hub, and the installation end of described blade is provided with the surface that mutually can abut with described taper inner face.
7. rotor according to claim 6, is characterized in that:
Described guide cover is connected with the second motor, and described second electric machine rotation promotes described guide cover and moves along the axis of described propeller hub.
8. rotor according to claim 7, is characterized in that:
Described first motor is hollow shaft motor, and described second motor moves by promoting described guide cover through the adapter shaft of described first motor.
9. oar folder, can be mounted in the frame of aircraft, comprise propeller hub, described propeller hub, for installing blade, rotates under the first driven by motor;
It is characterized in that:
Described propeller hub is provided with the sliding channel radially arranged, described propeller hub is provided with sliding bar, described sliding bar can slide in described sliding channel;
Elastic biasing arrangement, provides biasing force to described sliding bar, makes described sliding bar near the axis of described propeller hub.
10. aircraft, comprises frame and rotor, and described rotor is arranged in described frame, it is characterized in that:
Described rotor is the rotor described in any one of claim 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520633292.2U CN205076046U (en) | 2015-08-20 | 2015-08-20 | Rotor, oar press from both sides and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520633292.2U CN205076046U (en) | 2015-08-20 | 2015-08-20 | Rotor, oar press from both sides and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205076046U true CN205076046U (en) | 2016-03-09 |
Family
ID=55428469
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520633292.2U Withdrawn - After Issue CN205076046U (en) | 2015-08-20 | 2015-08-20 | Rotor, oar press from both sides and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205076046U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105129083A (en) * | 2015-08-20 | 2015-12-09 | 何春旺 | Rotor, propeller clamp and aircraft |
| CN105799930A (en) * | 2016-05-12 | 2016-07-27 | 谭圆圆 | Rotor-wing fixing structure of multi-rotor-wing type unmanned aerial vehicle |
-
2015
- 2015-08-20 CN CN201520633292.2U patent/CN205076046U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105129083A (en) * | 2015-08-20 | 2015-12-09 | 何春旺 | Rotor, propeller clamp and aircraft |
| CN105129083B (en) * | 2015-08-20 | 2019-01-29 | 珠海磐磊智能科技有限公司 | Rotor, paddle folder and aircraft |
| CN105799930A (en) * | 2016-05-12 | 2016-07-27 | 谭圆圆 | Rotor-wing fixing structure of multi-rotor-wing type unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105129083A (en) | Rotor, propeller clamp and aircraft | |
| CN104369862B (en) | A kind of pilotless helicopter | |
| CN204310038U (en) | A kind of pilotless helicopter | |
| CN205076046U (en) | Rotor, oar press from both sides and aircraft | |
| CN105416582A (en) | Passive amplitude changing flapping mechanism and flapping method | |
| CN104554717B (en) | rotor drive system | |
| CN103803064A (en) | Belt-transmission four-rotor-wing aircraft | |
| CN105620728A (en) | Propeller with variable propeller diameter and variable propeller pitch | |
| CN104153940A (en) | Variable attack-angle device of vertical-shaft wind electric generator blade | |
| CA3080823A1 (en) | Pitch control system | |
| CN208358699U (en) | A kind of vehicular chela can rotate integrally pulley extractor | |
| CN204548496U (en) | Duct engine installation and aircraft | |
| CN110144670A (en) | A kind of regulating mechanism of Knitting Machinery pulling device | |
| CN205599860U (en) | Supporting mechanism in casing four corners | |
| KR101936154B1 (en) | Vertical axis wind power generato with lift-drag hybrid type blade | |
| CN205633018U (en) | Screw propeller | |
| CN208361654U (en) | Elevator fan assembly | |
| CN105485880A (en) | Swing structure of wind guide plates and air hose machine | |
| CN104494827A (en) | Asymmetric rotation flapping wing lift force generating device | |
| CN104405584B (en) | A kind of vertical axis windmill pitch-variable system and the wind energy ship with it | |
| DE102015105249B3 (en) | Rotor and method for adjusting a blade pitch of a rotor blade on the rotor | |
| CN104773286B (en) | A kind of mechanical transmission roller wing lift generating device | |
| CN204784219U (en) | Duplex bearing seat with adjustable | |
| CN209634712U (en) | A kind of mounting device of standard contained implement and the nonstandard track in military aircraft floor | |
| CN204310034U (en) | A kind of 4 passage Hybrid mode tilt table devices of pilotless helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170426 Address after: 519000 Guangdong city of Zhuhai province Hengqin Baohua Road No. 6, room 105 -14724 Patentee after: Zhuhai pan Lei Intelligent Technology Co Ltd Address before: 519000 Guangdong Province, Zhuhai city Xiangzhou District Road No. 2 Building 2 martyrs Tong En Culture Communication Co. Ltd. Patentee before: He Chunwang |
|
| TR01 | Transfer of patent right | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160309 Effective date of abandoning: 20190129 |
|
| AV01 | Patent right actively abandoned |