CN205499338U - Self -adaptation variable -pitch propeller oar and aircraft - Google Patents
Self -adaptation variable -pitch propeller oar and aircraft Download PDFInfo
- Publication number
- CN205499338U CN205499338U CN201620217092.3U CN201620217092U CN205499338U CN 205499338 U CN205499338 U CN 205499338U CN 201620217092 U CN201620217092 U CN 201620217092U CN 205499338 U CN205499338 U CN 205499338U
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- China
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- main shaft
- rotor head
- connecting rod
- oar
- pitch propeller
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
Abstract
The utility model discloses a self -adaptation variable -pitch propeller oar and aircraft, wherein the screw includes main shaft, paddle, rotor head, spring, oar clamp, connecting rod and connecting rod mounting, and the rotor headgear connects on the main shaft and can follow its and slide, and the tip at the main shaft is installed to the connecting rod mounting, and the spring is located between rotor head and the connecting rod mounting, it is fixed with the paddle that the oar presss from both sides one end, and the other end rotates with the rotor head to be connected, and the connecting rod presss from both sides to rotate with connecting rod mounting and oar respectively to be connected, the oar clamp can drive paddle sliding along the main shaft along with the first body of rotor to the living rotation of relative rotor hair is in order to adjust the angle between paddle and the rotation plane by rod drive at the slip in -process, and the spring can take place deformation along with the axial motion of rotor head. The utility model discloses can change the screw pitch in self -adaptation ground along with the change of flying speed to make the aircraft can both have higher efficiency in the friction speed, through the automatic displacement of mechanical structure completion, need not control system and extra drive arrangement.
Description
Technical field
This utility model relates to propeller field, especially relates to a kind of variable-pitch propeller, and this utility model further relates to a kind of aircraft.
Background technology
The propeller of fixed wing airplane is divided into spacing and displacement two class, as its name suggests, the pitch of constant pitch airscrew is fixing, different pitches can only adapt to the rotating speed of different range, as the pitch of applicable low speed is difficult in adapt at a high speed (efficiency is low), otherwise, it is suitable for pitch at a high speed and is also difficult in adapt to low speed (efficiency is low), so constant pitch airscrew can only just have higher efficiency in selected velocity interval.Corresponding, pitch then can be adjusted by variable-pitch propeller, so that propeller has greater efficiency under different rotating speeds, after variable-pitch propeller of the prior art usually first passes through control system computational analysis, then realize displacement by driving means, but this mode needs control system and the driving means of complexity, cost is big, and technology requires height, and mechanism is complicated, maintenance difficult, reliability is low.
Utility model content
In order to overcome the deficiencies in the prior art, this utility model provides a kind of self adaptation variable-pitch propeller, and it can change airscrewpiston adaptively with the change of flight speed, so that aircraft can have higher efficiency in friction speed；Completing automatic adjustable-pitch by frame for movement, it is not necessary to control system and extra driving means, cost requires low with technology, and mechanism is simple, and reliability is high.
This utility model provides a kind of aircraft.
This utility model solves its technical problem and be the technical scheme is that
A kind of self adaptation variable-pitch propeller, including main shaft and at least two blade, also includes rotor head, spring, oar folder, connecting rod and linkage fasteners, wherein,
Rotor head is socketed on main shaft and can slide along, and linkage fasteners is arranged on main shaft, and spring is located between rotor head and linkage fasteners；
Oar presss from both sides one end to be fixed with blade, and the other end is rotationally connected with rotor head, and connecting rod presss from both sides with linkage fasteners and oar respectively and is rotationally connected；
Oar folder can drive blade sliding along main shaft with rotor head one, and is driven by connecting rod in sliding process and relatively rotor head rotates the angle adjusting between blade and Plane of rotation, and spring can deform upon with the axially-movable of rotor head.
As the further improved procedure of such scheme, blade is two, the symmetrical both sides being located at main shaft.
As the further improved procedure of such scheme, rotor head includes a cylinder, and the middle part of cylinder is provided with a through hole radially, and it is socketed on main shaft by this through hole.
As the further improved procedure of such scheme, the head end of oar folder is provided with a rotating part, and this rotating part is provided with an axial via, and an attachment screw screws in the end of cylinder after passing this via, be provided with thrust bearing between rotating part and the end of cylinder.
As the further improved procedure of such scheme, the tail end of oar folder is provided with the clamping limb of two panels level, and the tail end of blade is fixed between clamping limb and by one vertically through the screw of this clamping limb with blade.
As the further improved procedure of such scheme, linkage fasteners is arranged on the top of main shaft, and spring supports with linkage fasteners and rotor head respectively.
As the further improved procedure of such scheme, the outside of oar folder is extended with a rotating shaft being perpendicular to main shaft, and connecting rod includes the body of rod and is located at post and perpendicular axle sleeve, and the top of the body of rod is hinged with linkage fasteners, and bottom is hinged with rotating shaft by axle sleeve.
A kind of aircraft, including above-mentioned self adaptation variable-pitch propeller.
The beneficial effects of the utility model are:
Airscrewpiston can be changed adaptively, so that aircraft can have higher efficiency in friction speed with the change of flight speed；Completing automatic adjustable-pitch by frame for movement, it is not necessary to control system and extra driving means, cost requires low with technology, and mechanism is simple, and reliability is high.
Accompanying drawing explanation
With embodiment, this utility model is further illustrated below in conjunction with the accompanying drawings.
Fig. 1 is the overall schematic of one embodiment of this utility model；
Fig. 2 is the decomposing schematic representation of one embodiment of this utility model；
Fig. 3 is the schematic diagram of the little pitch of this utility model；
Fig. 4 is the schematic diagram of the big pitch of this utility model.
Detailed description of the invention
Below with reference to embodiment and accompanying drawing, the technique effect of design of the present utility model, concrete structure and generation is carried out clear, complete description, to be completely understood by the purpose of this utility model, scheme and effect.It should be noted that in the case of not conflicting, the embodiment in the application and the feature in embodiment can be mutually combined.
It should be noted that if no special instructions, when a certain feature is referred to as " fixing ", " connection " in another feature, and it can directly be fixed, be connected in another feature, it is also possible to indirectly fixes, be connected in another feature.Additionally, the upper and lower, left and right etc. used in this utility model describe and are only for the mutual alignment relation of each ingredient of this utility model in accompanying drawing.
Additionally, unless otherwise defined, all of technology used herein is identical with the implication that scientific terminology is generally understood that with those skilled in the art.Term the most used in the description is intended merely to describe specific embodiment rather than in order to limit the present invention.Term as used herein " and/or " include that the arbitrary of one or more relevant Listed Items combines.
With reference to Fig. 1, Fig. 2, it is shown that the accompanying drawings of one embodiment of this utility model, including main shaft 1 and at least two blade 2, and rotor head 3, spring 4, oar folder 5, connecting rod 6 and linkage fasteners 7.
The critical piece that main shaft 1 rotates as blade, is preferably mounted on a base 101, and base 101 is provided with the hole for being connected with other parts.Rotor head 3 is socketed on main shaft 1 and can slide along the axial reciprocating of main shaft, linkage fasteners 7 is arranged on main shaft 1, being provided with spring 4 between rotor head 3 and linkage fasteners 7, linkage fasteners 7 one aspect is used for installing connecting rods, on the other hand can be used for carrying out spacing to spring.
Oar folder 5 is for realizing the connection between blade 2 and rotor head 3, its one end is fixed with blade 2, the other end is rotationally connected with rotor head 3, connecting rod 6 presss from both sides 5 with linkage fasteners 7 and oar respectively and is rotationally connected, so, rotation along with blade 2, oar folder 5 can drive blade 2 sliding along main shaft 1 with rotor head 3 one, and driven by connecting rod 6 in sliding process and rotor head 3 relatively rotates to adjust the angle between blade 2 and Plane of rotation, and then adjust the pitch of propeller, in this process, spring 4 can deform upon with the axially-movable of rotor head 3, lower combination Fig. 3, Fig. 4 illustrates the displacement process that the present embodiment is concrete:
1, aircraft is when ground is not actuated, and revolution speed of propeller is zero, and flight speed V is equal to zero, and propeller is positioned at the bottom (initial position) of main shaft, and now pitch is maximum (as shown in Figure 4).
2, aircraft is when ground run, revolution speed of propeller increases to maximum, flight speed V is still equal to zero, due to square being directly proportional of pulling force and rotating speed, during so rotating speed increases, the pulling force that propeller produces increases, and along with the increase of pulling force, rotor head 3 will rise and compression spring 4 along main shaft 1, the decrement of the biggest then spring 4 of pulling force is the biggest, simultaneously because the driving of connecting rod 6, oar folder 5 makes blade 2 pitch being fixed on oar folder 5 diminish (as shown in Figure 3) by deflecting under the drive of rotor head 3, the restoring force balance that the pulling force finally making propeller produce produces with spring 4, now pitch is minimum.
3, aircraft is awing, the pitch of propeller can be automatically adjusted along with rotating speed and the change of flight speed, as a example by increasing rotating speed, when revolution speed of propeller (tangential velocity) rapidly increases to certain value, propeller pulling force increases, on the one hand flight speed is increased, on the other hand oar folder 5 is also caused to rise along main shaft and reduce pitch, and then cause pulling force to be gradually lowered, aircraft drag is gradually increased, the increase trend of speed also will slow down gradually, in above process, spring will be in compressive state, give the restoring force that rotor head is downward, after pulling force is reduced to a certain degree (i.e. pulling force is equal to resistance), also dynamic equilibrium is formed between spring and rotor head, now, the flight speed of aircraft, rotating speed, the blade angle of attack and propeller pulling force are the most constant, aircraft is i.e. fixed in a speed flight.And when the flight speed of aircraft changes, oar is clipped in spring and can automatically adjust its position on main shaft under the effect of pulling force, and then change pitch again to reach balance, it is ensured that aircraft all can have higher efficiency under different flight speeds.
As a kind of preferred implementation of the present embodiment, blade is two, the symmetrical both sides being located at main shaft, it is to be understood that blade can also be three or more than three, only need to simply adjust rotor head, oar folder and the shape of linkage and/or quantity.
Further, rotor head 3 includes a cylinder 31, and the middle part of cylinder is provided with a through hole radially, and it is socketed on main shaft by this through hole, and the two ends of cylinder have groove, and the center of groove is provided with screwed hole.
The head end of oar folder 5 is provided with a rotating part 51, the end of this rotating part 51 is again provided with groove, the center of groove is provided with an axial via, one attachment screw 501 screws in the screwed hole of barrel end after passing this via, thus ensure oar folder 5 can with rotor head 3 one along main shaft move up and down, can rotate around screw 501 relative to rotor head 3 again, additionally, be provided with thrust bearing 8 in the groove between rotating part and barrel end.
The tail end of oar folder 5 is provided with the clamping limb 52 of two panels level, and the tail end of blade 2 is fixed between clamping limb 52 and by one vertically through the screw 502 of this clamping limb with blade.
As connecting rod and the preferred mounting means of linkage fasteners, linkage fasteners 7 is arranged on the top of main shaft 1, and spring 4 supports with linkage fasteners 7 and rotor head 3 respectively.
The outside of oar folder 5 is extended with a rotating shaft 53 being perpendicular to main shaft, connecting rod 6 includes the body of rod 61 and is located at the body of rod bottom 61 and perpendicular axle sleeve 62, the top of the body of rod 61 is hinged with linkage fasteners 7, bottom is then hinged with rotating shaft 53 by axle sleeve 62, thus forms linkage between linkage fasteners 7, connecting rod 6 and rotor head 3.
The invention also discloses a kind of aircraft, it includes above-mentioned self adaptation variable-pitch propeller.
It is above preferable enforcement of the present utility model is illustrated, but the invention is not limited to described embodiment, those of ordinary skill in the art it may also be made that all equivalent variations or replacement on the premise of this utility model spirit, and deformation or the replacement of these equivalents are all contained in the application claim limited range.
Claims (8)
1. a self adaptation variable-pitch propeller, including main shaft and at least two blade, it is characterised in that: also include rotor head, spring, oar folder, connecting rod and linkage fasteners, wherein,
Described rotor head is socketed on described main shaft and can slide along, and described linkage fasteners is arranged on described main shaft, and described spring is located between described rotor head and linkage fasteners；
Described oar presss from both sides one end to be fixed with described blade, and the other end is rotationally connected with described rotor head, and described connecting rod presss from both sides with described linkage fasteners and oar respectively and is rotationally connected；
Described oar folder can drive described blade sliding along described main shaft with described rotor head one, and driven by described connecting rod in sliding process and the most described rotor head rotates to adjust the angle between described blade and Plane of rotation, described spring can deform upon with the axially-movable of described rotor head.
Self adaptation variable-pitch propeller the most according to claim 1, it is characterised in that: described blade is two, the symmetrical both sides being located at described main shaft.
Self adaptation variable-pitch propeller the most according to claim 2, it is characterised in that: described rotor head includes that a cylinder, the middle part of described cylinder are provided with a through hole radially, and it is socketed on described main shaft by this through hole.
Self adaptation variable-pitch propeller the most according to claim 3, it is characterized in that: the head end of described oar folder is provided with a rotating part, this rotating part is provided with an axial via, one attachment screw screws in the end of described cylinder after passing this via, be provided with thrust bearing between described rotating part and the end of cylinder.
Self adaptation variable-pitch propeller the most according to claim 3, it is characterised in that: the tail end of described oar folder is provided with the clamping limb of two panels level, and the tail end of described blade is fixed between described clamping limb and by one vertically through the screw of this clamping limb with blade.
Self adaptation variable-pitch propeller the most according to any one of claim 1 to 5, it is characterised in that: described linkage fasteners is arranged on the top of described main shaft, and described spring supports with described linkage fasteners and rotor head respectively.
Self adaptation variable-pitch propeller the most according to claim 6, it is characterized in that: the outside of described oar folder is extended with a rotating shaft being perpendicular to described main shaft, described connecting rod includes the body of rod and is located at post and perpendicular axle sleeve, the top of the described body of rod is hinged with described linkage fasteners, and bottom is hinged with described rotating shaft by described axle sleeve.
8. an aircraft, it is characterised in that: include the self adaptation variable-pitch propeller described in claim 7.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620217092.3U CN205499338U (en) | 2016-03-21 | 2016-03-21 | Self -adaptation variable -pitch propeller oar and aircraft |
| PCT/CN2016/085192 WO2017161700A1 (en) | 2016-03-21 | 2016-06-08 | Adaptive variable-pitch propeller, and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620217092.3U CN205499338U (en) | 2016-03-21 | 2016-03-21 | Self -adaptation variable -pitch propeller oar and aircraft |
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| CN205499338U true CN205499338U (en) | 2016-08-24 |
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| CN201620217092.3U Active CN205499338U (en) | 2016-03-21 | 2016-03-21 | Self -adaptation variable -pitch propeller oar and aircraft |
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| WO (1) | WO2017161700A1 (en) |
Cited By (11)
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| CN106915437A (en) * | 2017-04-14 | 2017-07-04 | 西安天问智能科技有限公司 | Pulp distance varying mechanism and rotor craft in rotor craft |
| CN108438210A (en) * | 2017-12-07 | 2018-08-24 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of piston aviation engine Propeller variable pitch method |
| CN109050884A (en) * | 2018-06-21 | 2018-12-21 | 深圳市龙云创新航空科技有限公司 | A kind of the proprotor head and unmanned plane of automatic adjustable-pitch |
| 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 |
| CN109466749A (en) * | 2018-11-06 | 2019-03-15 | 珠海隆华直升机科技有限公司 | Helicopter displacement drive assembly and helicopter |
| CN109677602A (en) * | 2018-12-26 | 2019-04-26 | 张耀天 | A kind of unmanned plane wing |
| CN109835468A (en) * | 2019-01-03 | 2019-06-04 | 上海歌尔泰克机器人有限公司 | A kind of pitch-changing mechanism and displacement paddle with flying height automatic adjustable-pitch |
| CN110040240A (en) * | 2019-05-24 | 2019-07-23 | 安阳市豪克航空科技有限公司 | Single driving Propeller variable pitch, feathering, dead stick position locking system |
| CN110254694A (en) * | 2019-07-25 | 2019-09-20 | 埃游科技（深圳）有限公司 | A kind of propeller automatic torque-changing mechanism |
| CN110834717A (en) * | 2019-11-21 | 2020-02-25 | 北京航空航天大学 | Self-adaptive propeller device |
| WO2023171872A1 (en) * | 2022-03-08 | 2023-09-14 | 에어 앤드 에이치 에어로스페이스 인크 | Cyclic swing rotor assembly |
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| CN100337023C (en) * | 2003-02-27 | 2007-09-12 | 哈尔滨工程大学 | Self-adaptable straight-vaned pitch variable water turbine for tidal energy conversion |
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- 2016-06-08 WO PCT/CN2016/085192 patent/WO2017161700A1/en active Application Filing
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106915437A (en) * | 2017-04-14 | 2017-07-04 | 西安天问智能科技有限公司 | Pulp distance varying mechanism and rotor craft in rotor craft |
| CN108438210A (en) * | 2017-12-07 | 2018-08-24 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of piston aviation engine Propeller variable pitch method |
| CN108438210B (en) * | 2017-12-07 | 2022-03-15 | 中国航空工业集团公司西安航空计算技术研究所 | Piston type aircraft engine propeller pitch changing method |
| CN109050884B (en) * | 2018-06-21 | 2022-02-18 | 深圳市龙云创新航空科技有限公司 | Automatic variable-pitch propeller rotor head and unmanned aerial vehicle |
| CN109050884A (en) * | 2018-06-21 | 2018-12-21 | 深圳市龙云创新航空科技有限公司 | A kind of the proprotor head and unmanned plane of automatic adjustable-pitch |
| CN109466749A (en) * | 2018-11-06 | 2019-03-15 | 珠海隆华直升机科技有限公司 | Helicopter displacement drive assembly and helicopter |
| 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 |
| CN109677602B (en) * | 2018-12-26 | 2020-08-07 | 张耀天 | Unmanned aerial vehicle wing |
| CN109677602A (en) * | 2018-12-26 | 2019-04-26 | 张耀天 | A kind of unmanned plane wing |
| CN109835468A (en) * | 2019-01-03 | 2019-06-04 | 上海歌尔泰克机器人有限公司 | A kind of pitch-changing mechanism and displacement paddle with flying height automatic adjustable-pitch |
| CN110040240A (en) * | 2019-05-24 | 2019-07-23 | 安阳市豪克航空科技有限公司 | Single driving Propeller variable pitch, feathering, dead stick position locking system |
| CN110040240B (en) * | 2019-05-24 | 2023-09-22 | 安阳市豪克航空科技有限公司 | Single-drive propeller pitch-changing, feathering and stopping position locking system |
| CN110254694A (en) * | 2019-07-25 | 2019-09-20 | 埃游科技（深圳）有限公司 | A kind of propeller automatic torque-changing mechanism |
| CN110834717A (en) * | 2019-11-21 | 2020-02-25 | 北京航空航天大学 | Self-adaptive propeller device |
| WO2023171872A1 (en) * | 2022-03-08 | 2023-09-14 | 에어 앤드 에이치 에어로스페이스 인크 | Cyclic swing rotor assembly |
| KR20230132180A (en) * | 2022-03-08 | 2023-09-15 | 에어 앤드 에이치 에어로스페이스 인크 | Cyclic swing rotor assembly |
| KR102641056B1 (en) | 2022-03-08 | 2024-02-28 | 에어 앤드 에이치 에어로스페이스 인크 | Cyclic swing rotor assembly |
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| Publication number | Publication date |
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| WO2017161700A1 (en) | 2017-09-28 |
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