CN105292465B - Rigid rotor system for helicopter - Google Patents
Rigid rotor system for helicopter Download PDFInfo
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- CN105292465B CN105292465B CN201510741435.6A CN201510741435A CN105292465B CN 105292465 B CN105292465 B CN 105292465B CN 201510741435 A CN201510741435 A CN 201510741435A CN 105292465 B CN105292465 B CN 105292465B
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Abstract
The invention discloses a rigid rotor system for a helicopter. The rigid rotor system comprises a rigid rotor propeller hub, a rigid rotor pitch control mechanism and rigid rotor paddles, wherein the rigid rotor pitch control mechanism and the rigid rotor paddles are glued integrally and are connected with the rigid rotor propeller hub by virtue of bolts. According to the system disclosed by the invention, deep groove ball bearings and thrust bearings in the conventional teeterboard type propeller hub structure are replaced by joint bearings, so that a series of complex structures such as pitch change shafts, flapping hinges and vertical hinges are removed, and the problems such as complexity of the conventional teeterboard type propeller hub structure, heavy weight and short service life can be solved. Meanwhile, the problems that retreating paddleseasily enter an aerodynamic stalling state so as to reduce the aerodynamic efficiency due to swinging during high-speed forward flight and the like are solved, and the rigid rotor system has the advantages of simple structure, light weight, long service life, high maintainability and the like.
Description
Technical field
The present invention relates to technical field of aerospace, the rigid rotor system of more particularly to a kind of helicopter.
Background technology
Referring to Fig. 1 and Fig. 2, traditional form helicopter rotor system generally comprises three hinges (i.e. three rotary freedoms),
Respectively manipulate the traditional rotor pitch hinge 4 of the propeller pitch angle change of traditional rotor blade 1, it is allowed to which traditional rotor blade 1 is awing
Make the traditional rotor flapping hinge 3 of upper and lower flapping action and allow traditional rotor blade 1 awing to make the tradition for moving forward and backward
Rotor lead lag hinge 5.
When the main cause that the flapping action of traditional rotor blade 1 causes is flown before helicopter, the rotation of traditional rotor blade 1
Motion and front winged motion superposition, by taking top view rotate counterclockwise rotor as an example, advancing blade (when blade is rotated to right side) comes relatively
Flow velocity degree is more than and retreating blade (blade is rotated when side is sat), and the lift that advancing blade is produced will be more than retreating blade, i.e.,
Rotor right side lift is more than left side lift.When without traditional rotor flapping hinge 3, both sides blade lift differs in size and will constitute rolling
Torque makes helicopter turn on one's side to the left.When traditional rotor flapping hinge 3 is increased, advancing blade lift is big, just waves around traditional rotor
Dance hinge 3 is waved upwards；Retreating blade lift is little, just waves downwards around traditional rotor flapping hinge 3, so, unbalanced rolling power
Square cannot pass to fuselage, so as to avoid helicopter before fly in produce rolling.
Traditional rotor blade 1 waves when the main cause that the lagging motion of traditional rotor blade 1 causes is winged before helicopter
Motion causes its barycenter and is continually changing with flapping action with the distance of center of rotation, when such as traditional rotor blade 1 is waved upwards,
The distance of blade barycenter and center of rotation reduces, and vice versa, and the Coriolis force for thus bringing will be produced to larger reciprocal
Torque, acts on traditional rotor propeller hub 2, the problems such as causing the fatigue of rotor system and vibrate.Now, if in traditional rotor oar
The root of leaf 1 adds a traditional rotor lead lag hinge 5, that is, give the degree of freedom of one fore-and-aft direction of blade, can eliminate the torque, it is to avoid
It is delivered on traditional rotor propeller hub 2.
The shortcoming of traditional form helicopter rotor system has：
(1) complicated in mechanical structure, heavier-weight, the life-span is shorter and maintainability is poor；
(2) when front winged at a high speed, retreating blade waves the angle of attack compensating action of generation and makes it easier to enter aerodynamic stalling shape
State, so as to reduce its pneumatic efficiency.
The content of the invention
It is an object of the present invention to be directed to the problems referred to above, a kind of rigid rotor system of helicopter is proposed, it has structure
Simply, the advantages of lightweight, life-span length, maintainability are good and postpone front winged retreating blade stall at a high speed.
For achieving the above object, the technical solution adopted in the present invention is：A kind of rigid rotor system of helicopter, mainly
Including rigid rotor propeller hub, rigid rotor pitch-changing mechanism and rigid rotor blade.Position annexation between them is：Rigidity
Rotor pitch-changing mechanism and rigid rotor blade are glued into an entirety, and are bolted with rigid rotor propeller hub.
The rigid rotor propeller hub, is installed on rigid rotor axle, and rigid rotor blade bushing is located at rigid rotor propeller hub
Interior, rigid rotor propeller hub connects rotor rigid rotor pitch-changing mechanism by rigid rotor propeller hub pin.
The rigid rotor pitch-changing mechanism, including solidify the rigid rotor blade built-in fitting being installed on inside blade, and
Rigid rotor oscillating bearing inside rigid rotor blade built-in fitting, rigid rotor oscillating bearing passes through rigid rotor blade
Carrying out for bushing is spacing, and rigid rotor propeller hub-blade connecting pin is used to fix rigid rotor oscillating bearing, while bearing rigidity
Centrifugal force when rotor blade works, rigid rotor distance-variable rocker arm connection rigid rotor blade built-in fitting, for displacement to be moved
It is delivered on rigid rotor blade, rigid rotor blade bushing is used to limit rigid rotor pitch-changing mechanism in the space of rotor system
Position, the rigid rotor blade built-in fitting is the ellipsoidal structures part which is provided with three through holes；Rigid rotor pitch-changing mechanism
It act as the displacement motion passed over from rigid rotor distance-variable rocker arm to be delivered on rigid rotor blade, realizes rigid rotation
The pitch control of wing blade.
The rigid rotor blade is string configuration of the cross section with aerofoil profile, and the more conventional rotor blade of rigidity is high, can
Flapping motion when flying before eliminating, so as to postpone the stall of retreating blade.
Compared with prior art, the invention has the beneficial effects as follows overcome helicopter routine seesaw type propeller hub complex structure,
The problems such as heavier-weight and short life, while retreating blade easily enters pneumatic mistake due to waving when flying before avoiding at a high speed
The problems such as fast state is so as to reduce pneumatic efficiency, has the advantages that simple structure, lightweight, life-span length and maintainability are good.
Description of the drawings
Fig. 1 traditional rotor system construction drawings.
Fig. 2 traditional rotor system pitch-changing mechanism structure charts.
Fig. 3 rigid rotor system construction drawings.
Fig. 4 rigid rotor pitch-changing mechanism structure charts.
Fig. 5 is outline drawing of the present invention.
Reference is as follows：
1- traditional rotor blades；2- traditional rotor propeller hubs；3- traditional rotor flapping hinges；4- traditional rotor pitch hinges；5-pass
System rotor lead lag hinge.6- rigid rotor blades；7- rigid rotor propeller hubs；8- rigid rotor blade built-in fittings；9- rigid rotors are closed
Bearings；10- rigid rotor blade bushings；11- rigid rotors propeller hub-blade connecting pin；12- rigid rotor distance-variable rocker arms.
Specific embodiment
See Fig. 1-Fig. 5, below in conjunction with the accompanying drawings the present invention is further described.
In order to overcome the deficiencies in the prior art, according to embodiments of the present invention, referring to Fig. 3-Fig. 5, there is provided a kind of helicopter
Rigid rotor system, the problems such as it overcomes helicopter routine seesaw type propeller hub complex structure, heavier-weight and short life,
Retreating blade easily enters aerodynamic stalling state due to waving so as to reduce pneumatic efficiency etc. when flying avoid at a high speed simultaneously before
Problem, has the advantages that simple structure, lightweight, life-span length and maintainability are good.
See Fig. 3-Fig. 5, a kind of rigid rotor system of helicopter of the present embodiment, it mainly include rigid rotor propeller hub 7,
Rigid rotor pitch-changing mechanism and rigid rotor blade 6.Position annexation between them is：Connect each other between three
Connect, rigid rotor pitch-changing mechanism and rigid rotor blade 6 are glued into an entirety, and are connected by bolt with rigid rotor propeller hub 7
Connect.
Wherein, rigid rotor propeller hub 7, by rigid rotor propeller hub pin 11 rigid rotor pitch-changing mechanism is connected.
See Fig. 4, a kind of rigid rotor pitch-changing mechanism of helicopter of the present embodiment is mainly consisted of：
Rigid rotor blade built-in fitting 8 and the rigid rotor oscillating bearing 9 inside rigid rotor blade built-in fitting 8,
Rigid rotor blade bushing 10 is located in rigid rotor propeller hub 7, for the spacing of rigid rotor oscillating bearing 9, rigid rotor oar
Hub-blade connecting pin 11 is used to fix rigid rotor oscillating bearing 9, while bearing centrifugation when rigid rotor blade 6 works
Power, the connection rigid rotor blade of rigid rotor distance-variable rocker arm 12 built-in fitting 8, for displacement motion to be delivered to into rigid rotor blade
On 6.Rigid rotor blade 6 also differ in that with traditional rotor blade 1, due to shape and structure difference, rigid rotor oar
Leaf 6 waves that rigidity is very high, along with rigid rotor system removes in itself the restriction after flapping hinge to waving, essentially eliminates
Its flapping action, so as to also eliminate the lagging motion for being produced by waving accordingly.Fly when institute for helicopter is front at a high speed
The rollover torque problem that the rotor for facing is produced because left and right lift is asymmetric, several allusion quotations of above-described embodiment rigid rotor system
Type controls case, is specifically described as follows：
(1) control of single-rotor helicopter
It is similar with traditional form helicopter rotor system by taking top view rotate counterclockwise rotor as an example, rigid rotor system
Rollover torque to the left will be produced.Now, using actively providing the manipulation that rotor system is tilted to the right by control system, produce to
Right rolling moment is balancing left side-turning torque.
(2) with regard to the symmetrical multi-rotor aerocraft of body (such as side-by-side helicopter, coaxal helicopter or many rotors
Helicopter) control
Due to the rigid rotor blade direction of rotation in symmetric position conversely, its rollover torque can be balanced mutually, therefore
Active control is provided without the need for control system to manipulate, further simplify total system complexity.Simultaneously as eliminating waving for rotor
Dance, for retreating blade, compensates without the angle of attack produced because waving, and its rotor load and the relative angle of attack are less, postpone
Its stall, advantageously in the forward flight speed for improving helicopter.
In sum, the helicopter rigid rotor system and control method of each example of the invention, its major advantage is：
(1) the problems such as overcoming helicopter routine seesaw type propeller hub complex structure, heavier-weight and short life；
(2) retreating blade is easily pneumatic so as to reduce into aerodynamic stalling state due to waving when flying before avoiding at a high speed
Efficiency；
(3) have the advantages that simple structure, lightweight, life-span length and maintainability are good.
Claims (1)
1. the rigid rotor system of a kind of helicopter, it is characterised in that：It includes rigid rotor propeller hub, rigid rotor pitch-changing mechanism
With rigid rotor blade；Rigid rotor pitch-changing mechanism and rigid rotor blade are glued into an entirety, and with rigid rotor propeller hub
It is bolted；
The rigid rotor propeller hub, is installed on rigid rotor axle, and rigid rotor blade bushing is located in rigid rotor propeller hub, just
Property rotor hub by rigid rotor propeller hub pin connect rotor rigid rotor pitch-changing mechanism；
The rigid rotor pitch-changing mechanism, including solidify the rigid rotor blade built-in fitting being installed on inside blade, and be located at
Rigid rotor oscillating bearing inside rigid rotor blade built-in fitting, rigid rotor oscillating bearing passes through rigid rotor blade bushing
Carry out it is spacing, rigid rotor propeller hub-blade connecting pin be used for fix rigid rotor oscillating bearing, while bearing rigid rotor oar
Centrifugal force when leaf works, rigid rotor distance-variable rocker arm connection rigid rotor blade built-in fitting, for displacement motion to be delivered to
On rigid rotor blade, rigid rotor blade bushing is used to limit rigid rotor pitch-changing mechanism in the locus of rotor system；
The rigid rotor blade built-in fitting is the ellipsoidal structures part which is provided with three through holes；Rigid rotor pitch-changing mechanism act as
The displacement motion passed over from rigid rotor distance-variable rocker arm is delivered on rigid rotor blade, rigid rotor blade is realized
Pitch control；
The rigid rotor blade is string configuration of the cross section with aerofoil profile, and the more conventional rotor blade of rigidity is high, can eliminate
Flapping motion when front winged, so as to postpone the stall of retreating blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510741435.6A CN105292465B (en) | 2015-11-04 | 2015-11-04 | Rigid rotor system for helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510741435.6A CN105292465B (en) | 2015-11-04 | 2015-11-04 | Rigid rotor system for helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105292465A CN105292465A (en) | 2016-02-03 |
| CN105292465B true CN105292465B (en) | 2017-05-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510741435.6A Active CN105292465B (en) | 2015-11-04 | 2015-11-04 | Rigid rotor system for helicopter |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620742B (en) * | 2016-03-17 | 2018-06-29 | 中国直升机设计研究所 | A kind of Helicopter Rotor Flap hinge |
| CN106741887B (en) * | 2017-01-13 | 2023-12-26 | 重庆星环航空科技有限公司 | Multi-blade rotor head structure with external swing hinge damping sleeve |
| CN107140202B (en) * | 2017-05-12 | 2023-06-20 | 郑可为 | Centrifugal swing hinge rotor head |
| CN107719661A (en) * | 2017-11-08 | 2018-02-23 | 沈阳旋飞航空技术有限公司 | A kind of unmanned plane rotor pulp distance varying mechanism |
| CN107985586A (en) * | 2017-12-29 | 2018-05-04 | 江苏方阔航空科技有限公司 | A kind of life-cycle pulp hub structure |
| CN109484637A (en) * | 2018-12-24 | 2019-03-19 | 沈阳旋飞航空技术有限公司 | A kind of rotor pulp distance varying mechanism of the dynamic unmanned plane of improved oil |
| CN109677601B (en) * | 2019-02-22 | 2024-05-28 | 一飞智控(天津)科技有限公司 | Teeterboard type unmanned aerial vehicle rotor wing and unmanned aerial vehicle |
| CN112046739B (en) * | 2020-08-06 | 2022-03-18 | 中国人民解放军总参谋部第六十研究所 | Rigid rotor hub of helicopter |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2927881B1 (en) * | 2008-02-27 | 2010-10-29 | Eurocopter France | HELICOPTER WITH A PLURALITY OF SUSTAINING ELEMENTS TO ORDER THE IMPACT OF ITS BLADES |
| CN102272002B (en) * | 2009-01-19 | 2014-05-07 | 贝尔直升机泰克斯特龙公司 | Yoke and bearing fitting assembly for rotors |
| CN201923318U (en) * | 2010-10-18 | 2011-08-10 | 南京航空航天大学 | Hingeless rotor hub support arm for helicopter |
| US9169010B2 (en) * | 2012-02-24 | 2015-10-27 | Bell Helicopter Textron Inc. | Offset stacked yoke hub for tiltrotor aircraft |
| CN103754363B (en) * | 2014-02-11 | 2015-10-14 | 谷梦若 | Rotor wingtip not displacement and the helicopter rotor system of lift-rising |
| CN104029815B (en) * | 2014-06-18 | 2016-06-08 | 江苏诺华视创电影数字科技有限公司 | Take photo by plane vertiplane adjustable tail displacement structure |
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Effective date of registration: 20200605 Address after: Room 108, science and technology entrepreneurship research incubation complex building (Building 5), Baixia high tech Industrial Park, No. 5 Yongzhi Road, Qinhuai District, Nanjing, Jiangsu Province, 210001 Patentee after: Vito (Nanjing) Intelligent Technology Co., Ltd Address before: 100191, Haidian District, Xueyuan Road, Beijing No. 35, Nanjing Ning building, 14 floor Patentee before: ZHONGHAN WEITUO (BEIJING) TECHNOLOGY Co.,Ltd. |
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