CN105523181A - Diameter variable rotor and aircraft - Google Patents
Diameter variable rotor and aircraft Download PDFInfo
- Publication number
- CN105523181A CN105523181A CN201610031890.1A CN201610031890A CN105523181A CN 105523181 A CN105523181 A CN 105523181A CN 201610031890 A CN201610031890 A CN 201610031890A CN 105523181 A CN105523181 A CN 105523181A
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- China
- Prior art keywords
- rotor
- propeller hub
- swinging block
- blade
- diameter
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/37—Rotors having articulated joints
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/48—Root attachment to rotor head
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
The invention relates to a diameter variable rotor and an aircraft. The rotor comprises a driving shaft, a propeller hub and at least two blades, wherein the propeller hub is mounted at the top end of the driving shaft; the blades are uniformly mounted on the periphery of the propeller hub; oscillating blocks are hinged on the propeller hub; and an elastic biasing device for defining deflection oscillating quantity to control a diameter variation amount range of each blade is also connected with each oscillating block in the propeller hub. Therefore, when the propeller hub rotates under the driving of the driving shaft, the propeller hub can move outwards in a radial direction of the propeller hub under the effect of a centrifugal force so that the diameter of the rotor is increased; the higher the speed is, the larger the centrifugal force is; and the greater the outwardly opening degree is, the greater the power generated by the rotor is. When the speeds of the blades are reduced, the blades retract inwards under the effect of returning forces of the elastic biasing devices so that the smaller the diameter of the rotor is, the smaller the power generated by the rotor is; therefore, the diameter of the rotor is also adjusted while the speeds of the blades are adjusted so that the speed of the reaction of the rotor to power adjustment is increased and the adjustable range of the power is enlarged.
Description
[technical field]
The present invention relates to aircraft rotor interconnection technique, particularly relate to a kind of rotor of variable-diameter.
[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, in rotor geometrical property, most important parameter is its diameter, and namely blade tip rotates the circle diameter scanned; The size of rotor diameter, is usually calculated by aerodynamics and more comprehensively determines, the diameter of rotor and the power of driving engine and rotating speed, command speed and flying height, blade number and width all have direct relation.According to rotor qigong theory, along with the increase/reduction of rotor blade diameter, not only can increase or reduce pulling force or the thrust of rotor, also can improve or reduce rotor efficiency; Manufacture and assembly difficulty for reducing, when other geometrical properties of rotor are constant, altitude air density is low, and in order to provide enough thrust, rotor diameter is the bigger the better; Low latitude density of air is large, and cause rotor qigong hydraulic performance decline in order to avoid producing unnecessary thrust, rotor diameter relative high-altitude rotor diameter suitably reduces.
At present, the paddle of most of existing rotor is fixed on propeller hub, and the adjustment of aircraft power can only be undertaken by regulating blade rotating speed, not only can increase power consumption and the heating of motor, and rotor speed of response is comparatively slow and the adjustable extent of power is limited.Also some aircraft are had to regulate the power of aircraft by the method for feather, existing feather method is according to height or thrust requirements adjustment pitch, then pitch is locked, these need displacement control apparatus and pitch blocking device to carry out closed loop control, these regulating mechanisms are usually structurally independent of rotor drive device, so not only increase the complexity of rotor control system, but also add the overall weight of rotor.
[summary of the invention]
In order to realize foregoing invention object, the technical solution used in the present invention is:
The invention provides a kind of structure simple, control convenient, reaction speed is fast, power adjustable extent is wide, the rotor of self adaptation self-align variable-diameter and aircraft thereof.
A rotor for variable-diameter, comprise the blade of axle drive shaft, propeller hub and at least two, propeller hub is installed on the top of axle drive shaft, and blade well-distributed is installed on propeller hub outside; Described propeller hub is hinged with and is fixedly connected with respectively with each blade and deflects the swinging block of each blade rotating diameter of weave control, each swinging block in described propeller hub is also connected with and limits the elastic biasing arrangement that deflection oscillating quantity size controls each diameter of propeller blade variation scope.
Further, described elastic biasing arrangement comprises extensible member, extension spring and two articulation pieces, extensible member is made up of the expansion link and sleeve being mutually socketed bearing fit, the expansion link of mutual socket and the outer end of sleeve are connected to is convenient to hinged fixing articulation piece, and described extension spring to be installed between two articulation pieces and to limit on extensible member expansion link relative to the telescopic extensions of sleeve.
Further, a connected blade is installed outside each swinging block, an articulation piece on described elastic biasing arrangement is fixed on swinging block and propeller hub and deflects on the rotating shaft core that is fixedly connected with, another articulation piece on elastic biasing arrangement is installed on the free end of adjacent swinging block, the articulation piece on the free end that two adjacent swinging blocks are corresponding and the articulation piece on rotating shaft core hinged with the two ends of extensible member and extension spring respectively.
Further, each swinging block and propeller hub deflect on the rotating shaft core that is fixedly connected with and are also provided with a miniature gears, and the center of described propeller hub is provided with a big gear wheel simultaneously engaged with miniature gears on all swinging blocks.
Further, the blade on described swinging block be with swinging block outside the collapsible blade that is articulated and connected.
Further, a connected blade is installed outside each swinging block, be provided with between this swinging block and propeller hub and be convenient to the fixing rotating shaft core of swinging block deflection, an articulation piece on described elastic biasing arrangement is fixed on free end corresponding to swinging block rotating shaft core, another articulation piece on elastic biasing arrangement is mounted on propeller hub, and the two ends of described extensible member and extension spring are articulated with on the articulation piece on propeller hub and swinging block respectively.
Further, the fairing be mated also is fixedly connected with on the upside of described propeller hub, described fairing inside top is also provided with the swinging block be connected with each blade and coordinates the position-limited trough limiting each diameter of propeller blade variation scope, and articulation piece top fixing on described swinging block free end is connected with the slide post with position-limited trough bearing fit.
Further, the circular arc swinging block of described swinging block to be one end be free end.
A kind of aircraft, this aircraft adopts the rotor of above-mentioned variable-diameter.
The invention has the beneficial effects as follows:
The present invention is arranged on the hinged swinging block of Yu Jiang Grains by blade, when Jiang Grains is rotated under the driving of axle drive shaft, all blades radially outward can open along propeller hub by centrifugal action, thus make rotor diameter become large, the higher then centnifugal force suffered by it of paddle speed is larger, the degree that blade outwards rotates is larger, and the power that rotor produces is larger; When paddle speed diminishes, blade inwardly shrinks under the extension spring restoring force effect of elastic biasing arrangement, rotor diameter is diminished, the power that rotor produces diminishes, thus realize regulating rotor diameter reaching while paddle speed adjustment simultaneously, rotor is accelerated the speed of response of power adjustment, and the adjustable extent of power increases.
[accompanying drawing explanation]
Fig. 1 is the perspective view of the embodiment of the present invention one;
Fig. 2 is the sectional structure schematic diagram of the embodiment of the present invention one;
Fig. 3 is the sectional structure schematic diagram of fairing in the embodiment of the present invention one;
Fig. 4 is that when removing fairing in the embodiment of the present invention one, rotor diameter becomes large rear spatial structure enlarged diagram;
Spatial structure enlarged diagram when Fig. 5 is elastic biasing arrangement retracted for clearance when removing fairing in the embodiment of the present invention one;
Fig. 6 is the spatial structure enlarged diagram removing fairing in the embodiment of the present invention two;
Fig. 7 is the spatial structure enlarged diagram removing fairing in the embodiment of the present invention three.
[detailed description of the invention]
Embodiment one
A kind of rotor of variable-diameter, be applied on aircraft, as shown in Figures 1 to 5, comprise axle drive shaft 1, blade 4 that propeller hub 2, fairing 3 and three are evenly laid in propeller hub 2 outside, fairing 3 is fixedly connected on the upside of propeller hub 2, and propeller hub 2 is installed on axle drive shaft 1 top of aircraft motor 5, propeller hub 2 is hinged with and is fixedly connected with respectively with each blade 4 and deflects the swinging block 6 of weave control each blade 4 rotating diameter, swinging block 6 is for being fixed on the circular arc swinging block that the other end on propeller hub 2 is free end in one end, and this blade 4 is folding to be articulated and connected outside swinging block 6, each swinging block 6 in propeller hub 2 is also connected with the elastic biasing arrangement 7 limiting its deflection oscillating quantity size and then control each blade 4 variation in diameter weight range, this elastic biasing arrangement 7 comprises extensible member 70, extension spring 71 and two jointed shafts 72, extensible member 70 is made up of the expansion link 70a and sleeve 70b being mutually socketed bearing fit, the expansion link 70a of mutual socket and the outer end of sleeve 70b are connected to is convenient to the jointed shaft 72 hinged with it, described extension spring two ends to be installed between two jointed shafts 72 and to limit on extensible member 7 expansion link 70a relative to the telescopic extensions of sleeve 70b.
Continue as shown in Figures 1 to 5, a jointed shaft 72 on elastic biasing arrangement 7 is fixed on swinging block 6 and propeller hub 2 and deflects on the rotating shaft core that is fixedly connected with, another articulation piece on elastic biasing arrangement 7 is installed on the free end of adjacent swinging block 6, jointed shaft 72 on the free end of two adjacent swinging block 6 correspondences and the jointed shaft 72 on rotating shaft core hinged with the two ends of extensible member 70 and extension spring 71 respectively, elastic biasing arrangement 7 on all swinging blocks 6 successively head and the tail connects and composes the blade interlock body of a Coupled motion, effectively ensure that the diameter of all blades 4 synchronously becomes large or diminishes.
Continue as shown in Figures 1 to 5, also be provided with in fairing 3 inside top the swinging block 6 be connected with each blade 4 and coordinate the position-limited trough 30 being convenient to limit each diameter of propeller blade variation scope, jointed shaft 72 top fixing on swinging block 6 free end is connected with the slide post 720 with position-limited trough 30 bearing fit, by the bearing fit of slide post 720 with position-limited trough 30, except making position-limited trough 30 pairs of blades 4 of fairing 3 carry out except directional tagging, the synchronous axial system of fairing 3 Yu Jiang Grains 2 can be realized simultaneously.
Embodiment two
As shown in Figure 6, the difference of this embodiment and embodiment one is, this blade 4 is not folding to be fixedly connected on outside swinging block 6, each swinging block 6 and the jointed shaft 72 of propeller hub 2 rotating shaft core are also fixedly connected with a miniature gears 8, one big gear wheel 9 simultaneously engaged with miniature gears 8 on all swinging blocks 6 is installed at the center of propeller hub 2, like this, engaged by big gear wheel 9 and the miniature gears 8 on each swinging block 6 simultaneously and control all blades and link simultaneously, further ensure that the diameter of all blades 4 synchronously becomes and diminish greatly or synchronously.
Embodiment three
As shown in Figure 7, the difference of this embodiment and embodiment one is, this blade 4 is not folding to be fixedly connected on outside swinging block 6, and the mode that is connected and fixed of elastic biasing arrangement 7 is also obviously different from embodiment one; Namely in this embodiment, between each swinging block 6 and propeller hub 2, independent being provided with is convenient to swinging block 6 and is deflected fixing rotating shaft core, a jointed shaft 72 on elastic biasing arrangement 7 is fixed on free end corresponding to swinging block 6 rotating shaft core, another jointed shaft 72 on elastic biasing arrangement 7 is mounted on propeller hub 2, and the two ends of extensible member 70 and extension spring 71 are articulated with on the jointed shaft 73 on propeller hub 2 and swinging block free end respectively.
By above embodiment, during work, when Jiang Grains is rotated under the driving of axle drive shaft, all blades radially outward can open along propeller hub by centrifugal action, thus make rotor diameter become large, the higher then centnifugal force suffered by it of paddle speed is larger, and the degree that blade outwards rotates is larger, and the power that rotor produces is larger; When paddle speed diminishes, blade inwardly shrinks under the extension spring restoring force effect of elastic biasing arrangement, rotor diameter is diminished, the power that rotor produces diminishes, thus realize regulating rotor diameter reaching while paddle speed adjustment simultaneously, rotor is accelerated the speed of response of power adjustment, and the adjustable extent of power increases.
The above embodiment is just preferred embodiment of the present invention, not limits practical range of the present invention with this, the equivalence change that all shapes according to the present invention, structure and principle are done, and all should be covered by protection scope of the present invention.
Claims (9)
1. a rotor for variable-diameter, comprise the blade of axle drive shaft, propeller hub and at least two, propeller hub is installed on the top of axle drive shaft, and blade well-distributed is installed on propeller hub outside; It is characterized in that:
Described propeller hub is hinged with and is fixedly connected with respectively with each blade and deflects the swinging block of each blade rotating diameter of weave control, each swinging block in described propeller hub is also connected with and limits the elastic biasing arrangement that deflection oscillating quantity size controls each diameter of propeller blade variation scope.
2. the rotor of a kind of variable-diameter according to claim 1, it is characterized in that, described elastic biasing arrangement comprises extensible member, extension spring and two articulation pieces, extensible member is made up of the expansion link and sleeve being mutually socketed bearing fit, the expansion link of mutual socket and the outer end of sleeve are connected to is convenient to hinged fixing articulation piece, and described extension spring to be installed between two articulation pieces and to limit on extensible member expansion link relative to the telescopic extensions of sleeve.
3. the rotor of a kind of variable-diameter according to claim 1 and 2, it is characterized in that, a connected blade is installed outside each swinging block, an articulation piece on described elastic biasing arrangement is fixed on swinging block and propeller hub and deflects on the rotating shaft core that is fixedly connected with, another articulation piece on elastic biasing arrangement is installed on the free end of adjacent swinging block, the articulation piece on the free end that two adjacent swinging blocks are corresponding and the articulation piece on rotating shaft core hinged with the two ends of extensible member and extension spring respectively.
4. the rotor of a kind of variable-diameter according to claim 3, it is characterized in that, each swinging block and propeller hub deflect on the rotating shaft core that is fixedly connected with and are also provided with a miniature gears, and the center of described propeller hub is provided with a big gear wheel simultaneously engaged with miniature gears on all swinging blocks.
5. the rotor of a kind of variable-diameter according to claim 3, is characterized in that, the blade on described swinging block be with swinging block outside the collapsible blade that is articulated and connected.
6. the rotor of a kind of variable-diameter according to claim 1 and 2, it is characterized in that, a connected blade is installed outside each swinging block, be provided with between this swinging block and propeller hub and be convenient to the fixing rotating shaft core of swinging block deflection, an articulation piece on described elastic biasing arrangement is fixed on free end corresponding to swinging block rotating shaft core, another articulation piece on elastic biasing arrangement is mounted on propeller hub, and the two ends of described extensible member and extension spring are articulated with on the articulation piece on propeller hub and swinging block respectively.
7. the rotor of a kind of variable-diameter according to claim 2, it is characterized in that, the fairing be mated also is fixedly connected with on the upside of described propeller hub, described fairing inside top is also provided with the swinging block be connected with each blade and coordinates the position-limited trough limiting each diameter of propeller blade variation scope, and articulation piece top fixing on described swinging block free end is connected with the slide post with position-limited trough bearing fit.
8. the rotor of a kind of variable-diameter according to claim 1, is characterized in that, the circular arc swinging block of described swinging block to be one end be free end.
9. an aircraft, is characterized in that, this aircraft adopts the rotor of a kind of variable-diameter described in any one of claim 1 to 8 claims.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610031890.1A CN105523181B (en) | 2016-01-15 | 2016-01-15 | The rotor and its aircraft of a kind of variable-diameter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610031890.1A CN105523181B (en) | 2016-01-15 | 2016-01-15 | The rotor and its aircraft of a kind of variable-diameter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105523181A true CN105523181A (en) | 2016-04-27 |
| CN105523181B CN105523181B (en) | 2017-12-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610031890.1A Active CN105523181B (en) | 2016-01-15 | 2016-01-15 | The rotor and its aircraft of a kind of variable-diameter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105523181B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105799930A (en) * | 2016-05-12 | 2016-07-27 | 谭圆圆 | Rotor-wing fixing structure of multi-rotor-wing type unmanned aerial vehicle |
| CN109278985A (en) * | 2018-11-20 | 2019-01-29 | 西安君晖航空科技有限公司 | A kind of variable propeller pitch device and its installation method |
| CN111844680A (en) * | 2020-07-23 | 2020-10-30 | 安徽省力天新材料股份有限公司 | Feed inlet anti-blocking device of extruder |
| CN112623211A (en) * | 2020-12-28 | 2021-04-09 | 桂林航天工业学院 | Unmanned aerial vehicle for mapping aerial photography |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3256938A (en) * | 1964-03-28 | 1966-06-21 | Bolkow Gmbh | Helicopter rotor construction and improved rotor blade therefor having a retractible trailing portion |
| US5620304A (en) * | 1995-12-11 | 1997-04-15 | Sikorsky Aircraft Corporation | Rotor system having alternating length rotor blades and positioning means therefor for reducing blade-vortex interaction (BVI) noise |
| US20060140769A1 (en) * | 2004-12-23 | 2006-06-29 | Frampton Thomas C | Ceiling fan with retractable fan blades |
| US20070059175A1 (en) * | 2005-04-27 | 2007-03-15 | Eurocopter | Rotocraft rotor with hinged blades and lockable retractable flapping abutments |
| CN102935890A (en) * | 2012-09-21 | 2013-02-20 | 中国空间技术研究院 | Variable diameter screw propeller |
| CN104943853A (en) * | 2015-04-27 | 2015-09-30 | 西北工业大学 | Propeller with variable pitch |
-
2016
- 2016-01-15 CN CN201610031890.1A patent/CN105523181B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3256938A (en) * | 1964-03-28 | 1966-06-21 | Bolkow Gmbh | Helicopter rotor construction and improved rotor blade therefor having a retractible trailing portion |
| US5620304A (en) * | 1995-12-11 | 1997-04-15 | Sikorsky Aircraft Corporation | Rotor system having alternating length rotor blades and positioning means therefor for reducing blade-vortex interaction (BVI) noise |
| US20060140769A1 (en) * | 2004-12-23 | 2006-06-29 | Frampton Thomas C | Ceiling fan with retractable fan blades |
| US20070059175A1 (en) * | 2005-04-27 | 2007-03-15 | Eurocopter | Rotocraft rotor with hinged blades and lockable retractable flapping abutments |
| CN102935890A (en) * | 2012-09-21 | 2013-02-20 | 中国空间技术研究院 | Variable diameter screw propeller |
| CN104943853A (en) * | 2015-04-27 | 2015-09-30 | 西北工业大学 | Propeller with variable pitch |
Non-Patent Citations (1)
| Title |
|---|
| 《武器百科》编委会编: "《武器百科》", 31 August 2013, 中国华侨出版社 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105799930A (en) * | 2016-05-12 | 2016-07-27 | 谭圆圆 | Rotor-wing fixing structure of multi-rotor-wing type unmanned aerial vehicle |
| CN109278985A (en) * | 2018-11-20 | 2019-01-29 | 西安君晖航空科技有限公司 | A kind of variable propeller pitch device and its installation method |
| CN109278985B (en) * | 2018-11-20 | 2023-09-29 | 西安君晖航空科技有限公司 | Pitch variable device and installation method thereof |
| CN111844680A (en) * | 2020-07-23 | 2020-10-30 | 安徽省力天新材料股份有限公司 | Feed inlet anti-blocking device of extruder |
| CN112623211A (en) * | 2020-12-28 | 2021-04-09 | 桂林航天工业学院 | Unmanned aerial vehicle for mapping aerial photography |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105523181B (en) | 2017-12-26 |
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