CN105292465A - Rigid rotor system for helicopter - Google Patents
Rigid rotor system for helicopter Download PDFInfo
- Publication number
- CN105292465A CN105292465A CN201510741435.6A CN201510741435A CN105292465A CN 105292465 A CN105292465 A CN 105292465A CN 201510741435 A CN201510741435 A CN 201510741435A CN 105292465 A CN105292465 A CN 105292465A
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- rigid rotor
- rigid
- blade
- rotor
- propeller hub
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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, particularly relate to a kind of rigid rotor system of helicopter.
Background technology
See Fig. 1 and Fig. 2, traditional form helicopter rotor system generally comprises three hinges (i.e. three rotary freedoms), be respectively the traditional rotor pitch hinge 4 handling the change of traditional rotor blade 1 propeller pitch angle, allow traditional rotor blade 1 make the traditional rotor flapping hinge 3 of upper and lower flapping action awing and allow traditional rotor blade 1 to make the traditional rotor lead lag hinge 5 seesawed awing.
The major cause that traditional rotor blade 1 flapping action causes is when flying before helicopter, the rotary motion of traditional rotor blade 1 and before fly motion superposition, for top view left-hand revolution rotor, advancing blade (when blade rotates to right side) is greater than and retreating blade (blade rotates to when sitting side) relative to speed of incoming flow, the lift that advancing blade produces will be greater than retreating blade, and namely on the right side of rotor, lift is greater than left side lift.When not having traditional rotor flapping hinge 3, both sides blade lift differs in size and helicopter is turned on one's side formation rolling moment left.When increasing traditional rotor flapping hinge 3, advancing blade lift is large, just upwards waves around traditional rotor flapping hinge 3; Retreating blade lift is little, just waves downwards around traditional rotor flapping hinge 3, and like this, unbalanced rolling moment cannot pass to fuselage, thus flies middle generation rolling before avoiding helicopter.
The major cause that traditional rotor blade 1 lagging motion causes is that the distance that the flapping action of traditional rotor blade 1 when flying before helicopter causes its barycenter and centre of gration constantly changes with flapping action, as traditional rotor blade 1 upwards wave time, the distance of blade barycenter and centre of gration reduces, vice versa, the coriolis force brought thus will produce larger reciprocal moment, act on traditional rotor propeller hub 2, cause the problem such as fatigue and vibration of rotor system.Now, if add a traditional rotor lead lag hinge 5 at traditional rotor blade 1 root, namely give the degree of freedom of a blade fore-and-aft direction, this moment can be eliminated, avoid it to be 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 flying before high speed, the angle of attack compensating action that retreating blade waves generation makes it more easily enter aerodynamic stalling state, thus reduces its pneumatic efficiency.
Summary of the invention
The object of the invention is to, for the problems referred to above, propose a kind of rigid rotor system of helicopter, it has, and structure is simple, lightweight, the life-span is long, maintainability is good and fly the advantages such as retreating blade stall before postponing 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 comprises rigid rotor propeller hub, rigid rotor pitch-changing mechanism and rigid rotor blade.Position annexation between them is: rigid rotor pitch-changing mechanism and rigid rotor blade glued joint into an entirety, and is bolted with rigid rotor propeller hub.
Described rigid rotor propeller hub, is installed on rigid rotor axle, and rigid rotor blade lining is positioned at rigid rotor propeller hub, and rigid rotor propeller hub connects rotor rigid rotor pitch-changing mechanism by rigid rotor propeller hub pin.
Described rigid rotor pitch-changing mechanism, comprise the rigid rotor blade built-in fitting that solidification is installed on blade inside, and be positioned at the rigid rotor oscillating bearing of rigid rotor blade built-in fitting inside, rigid rotor oscillating bearing by rigid rotor blade lining carry out spacing, rigid rotor propeller hub-blade connects pin and is used for fixing rigid rotor oscillating bearing, bear the centnifugal force during work of rigid rotor blade simultaneously, rigid rotor distance-variable rocker arm connects rigid rotor blade built-in fitting, for by displacement Movement transmit to rigid rotor blade, rigid rotor blade lining is for limiting the locus of rigid rotor pitch-changing mechanism at rotor system, this rigid rotor blade built-in fitting which is provided with three through hole Elliptical round shape framing members, rigid rotor pitch-changing mechanism to act as the displacement Movement transmit passed over from rigid rotor distance-variable rocker arm on rigid rotor blade, achieve the pitch control of rigid rotor blade.
Described rigid rotor blade is the string configuration of cross-sectional plane with aerofoil profile, and the more conventional rotor blade of rigidity is high, flapping motion when flying before can eliminating, thus postpones the stall of retreating blade.
Compared with prior art, the invention has the beneficial effects as follows and overcome the problems such as helicopter conventional seesaw type propeller hub complex structure, heavier-weight and life-span be short, when avoiding flying at a high speed, retreating blade more easily enters aerodynamic stalling state owing to waving thus reduces the problems such as pneumatic efficiency simultaneously, the advantage such as have that structure is simple, lightweight, the life-span long and maintainability is good.
Accompanying drawing explanation
Fig. 1 traditional rotor system construction drawing.
Fig. 2 traditional rotor system pitch-changing mechanism constructional drawing.
Fig. 3 rigid rotor system construction drawing.
Fig. 4 rigid rotor pitch-changing mechanism constructional drawing.
Fig. 5 is outside drawing of the present invention.
Reference numeral is as follows:
1-traditional rotor blade; 2-traditional rotor propeller hub; 3-traditional rotor flapping hinge; 4-traditional rotor pitch hinge; 5 – traditional rotor lead lag hinge.6-rigid rotor blade; 7-rigid rotor propeller hub; 8-rigid rotor blade built-in fitting; 9-rigid rotor oscillating bearing; 10-rigid rotor blade lining; 11-rigid rotor propeller hub-blade connects pin; 12-rigid rotor distance-variable rocker arm.
Detailed description of the invention
See Fig. 1-Fig. 5, below in conjunction with accompanying drawing, the present invention is further described.
In order to overcome the deficiencies in the prior art, according to the embodiment of the present invention, referring to Fig. 3-Fig. 5, provide a kind of rigid rotor system of helicopter, it overcomes the problems such as helicopter conventional seesaw type propeller hub complex structure, heavier-weight and life-span be short, when avoiding flying at a high speed, retreating blade more easily enters aerodynamic stalling state owing to waving thus reduces the problems such as pneumatic efficiency simultaneously, the advantage such as have that structure is simple, lightweight, the life-span long and maintainability is good.
See Fig. 3-Fig. 5, the rigid rotor system of a kind of helicopter of the present embodiment, it mainly comprises rigid rotor propeller hub 7, rigid rotor pitch-changing mechanism and rigid rotor blade 6.Position annexation between them is: be interconnected with one another between three, and rigid rotor pitch-changing mechanism and rigid rotor blade 6 glued joint into an entirety, and is bolted with rigid rotor propeller hub 7.
Wherein, rigid rotor propeller hub 7, connects rigid rotor pitch-changing mechanism by rigid rotor propeller hub pin 11.
See Fig. 4, the rigid rotor pitch-changing mechanism of a kind of helicopter of the present embodiment, main composition is as follows:
Rigid rotor blade built-in fitting 8 and be positioned at the rigid rotor oscillating bearing 9 of rigid rotor blade built-in fitting 8 inside, rigid rotor blade lining 10 is positioned at rigid rotor propeller hub 7, spacing for rigid rotor oscillating bearing 9, rigid rotor propeller hub-blade connects pin 11 for fixing rigid rotor oscillating bearing 9, bear centnifugal force when rigid rotor blade 6 works simultaneously, rigid rotor distance-variable rocker arm 12 connects rigid rotor blade built-in fitting 8, for by displacement Movement transmit to rigid rotor blade 6.Rigid rotor blade 6 and traditional rotor blade 1 difference are also, due to shape and structure difference, rigid rotor blade 6 to wave rigidity very high, add rigid rotor system itself remove flapping hinge after to the restriction of waving, essentially eliminate its flapping action, thus also eliminate the lagging motion produced by waving accordingly.For the rollover moment problem that the rotor faced when flying before helicopter high speed produces because left and right lift is asymmetric, several typical cases of above-described embodiment rigid rotor system control cases, are specifically described as follows:
(1) control of single-rotor helicopter
For top view left-hand revolution rotor, and traditional form helicopter rotor system is similar, the rollover moment that rigid rotor system also will produce left.Now, adopt and initiatively provide by control system the manipulation that rotor system is tilted to the right, the rolling moment produced to the right balances left side-turning moment.
(2) about the control of the symmetrical multi-rotor aerocraft of body (as side-by-side helicopter, coaxal helicopter or multirotor helicopter)
Because the rigid rotor blade hand of rotation being in symmetric position is contrary, its rollover moment can balance mutually, therefore provides ACTIVE CONTROL without the need to control system and handles, further simplify total system complexity.Meanwhile, owing to eliminating waving of rotor, for retreating blade, the angle of attack do not produced because waving compensates, and its rotor load is less with the relative angle of attack, has postponed its stall, advantageously in the forward flight speed improving helicopter.
In sum, the helicopter rigid rotor system of each example of the present invention and control method, its major advantage is:
(1) problems such as helicopter conventional seesaw type propeller hub complex structure, heavier-weight and life-span be short are overcome;
(2) when avoiding flying at a high speed, retreating blade more easily enters aerodynamic stalling state owing to waving thus reduces pneumatic efficiency;
(3) advantage such as have that structure is simple, lightweight, life-span long and maintainability is good.
Claims (1)
1. a rigid rotor system for helicopter, is characterized in that: it comprises rigid rotor propeller hub, rigid rotor pitch-changing mechanism and rigid rotor blade; Rigid rotor pitch-changing mechanism and rigid rotor blade glued joint into an entirety, and are bolted with rigid rotor propeller hub;
Described rigid rotor propeller hub, is installed on rigid rotor axle, and rigid rotor blade lining is positioned at rigid rotor propeller hub, and rigid rotor propeller hub connects rotor rigid rotor pitch-changing mechanism by rigid rotor propeller hub pin;
Described rigid rotor pitch-changing mechanism, comprise the rigid rotor blade built-in fitting that solidification is installed on blade inside, and be positioned at the rigid rotor oscillating bearing of rigid rotor blade built-in fitting inside, rigid rotor oscillating bearing is undertaken spacing by rigid rotor blade lining, rigid rotor propeller hub-blade connects pin and is used for fixing rigid rotor oscillating bearing, bear the centnifugal force during work of rigid rotor blade simultaneously, rigid rotor distance-variable rocker arm connects rigid rotor blade built-in fitting, for by displacement Movement transmit to rigid rotor blade, rigid rotor blade lining is for limiting the locus of rigid rotor pitch-changing mechanism at rotor system, this rigid rotor blade built-in fitting which is provided with three through hole Elliptical round shape framing members, rigid rotor pitch-changing mechanism to act as the displacement Movement transmit passed over from rigid rotor distance-variable rocker arm on rigid rotor blade, realize the pitch control of rigid rotor blade,
Described rigid rotor blade is the string configuration of cross-sectional plane with aerofoil profile, and the more conventional rotor blade of rigidity is high, flapping motion when flying before eliminating, thus postpones 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 |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510741435.6A CN105292465B (en) | 2015-11-04 | 2015-11-04 | Rigid rotor system for helicopter |
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| Publication Number | Publication Date |
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| CN105292465A true CN105292465A (en) | 2016-02-03 |
| CN105292465B CN105292465B (en) | 2017-05-03 |
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| CN201510741435.6A Active CN105292465B (en) | 2015-11-04 | 2015-11-04 | Rigid rotor system for helicopter |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620742A (en) * | 2016-03-17 | 2016-06-01 | 中国直升机设计研究所 | Helicopter rotor flapping hinge |
| CN106741887A (en) * | 2017-01-13 | 2017-05-31 | 必扬星环（北京）航空科技有限公司 | Many blade rotor header structures of external flapping hinge shock-absorbing sleeve |
| CN107140202A (en) * | 2017-05-12 | 2017-09-08 | 上海寅翅智能科技有限公司 | A kind of centrifugal flapping 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 |
| CN109677601A (en) * | 2019-02-22 | 2019-04-26 | 一飞智控(天津)科技有限公司 | Seesaw type unmanned plane rotor and unmanned plane |
| CN112046739A (en) * | 2020-08-06 | 2020-12-08 | 中国人民解放军总参谋部第六十研究所 | Rigid rotor hub of helicopter |
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| US20090214340A1 (en) * | 2008-02-27 | 2009-08-27 | Eurocopter | Helicopter provided with a plurality of lift elements for controlling the angles of incidence of its blades |
| CN201923318U (en) * | 2010-10-18 | 2011-08-10 | 南京航空航天大学 | Hingeless rotor hub support arm for helicopter |
| US20110274550A1 (en) * | 2009-01-19 | 2011-11-10 | Stamps Frank B | Yoke and Bearing Fitting Assembly for Rotors |
| US20130224025A1 (en) * | 2012-02-24 | 2013-08-29 | Bell Helicopter Textron Inc. | Offset Stacked Yoke Hub for Tiltrotor Aircraft |
| CN103754363A (en) * | 2014-02-11 | 2014-04-30 | 谷梦若 | Helicopter rotor wing system with non-variable-pitch and lift-rising rotor wingtips |
| CN104029815A (en) * | 2014-06-18 | 2014-09-10 | 江苏泓雅集文化传播有限公司 | Adjustable tail variable pitch structure of helicopter for aerial photography |
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- 2015-11-04 CN CN201510741435.6A patent/CN105292465B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090214340A1 (en) * | 2008-02-27 | 2009-08-27 | Eurocopter | Helicopter provided with a plurality of lift elements for controlling the angles of incidence of its blades |
| US20110274550A1 (en) * | 2009-01-19 | 2011-11-10 | Stamps Frank B | 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 |
| US20130224025A1 (en) * | 2012-02-24 | 2013-08-29 | Bell Helicopter Textron Inc. | Offset Stacked Yoke Hub for Tiltrotor Aircraft |
| CN103754363A (en) * | 2014-02-11 | 2014-04-30 | 谷梦若 | Helicopter rotor wing system with non-variable-pitch and lift-rising rotor wingtips |
| CN104029815A (en) * | 2014-06-18 | 2014-09-10 | 江苏泓雅集文化传播有限公司 | Adjustable tail variable pitch structure of helicopter for aerial photography |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620742A (en) * | 2016-03-17 | 2016-06-01 | 中国直升机设计研究所 | Helicopter rotor flapping hinge |
| CN106741887A (en) * | 2017-01-13 | 2017-05-31 | 必扬星环（北京）航空科技有限公司 | Many blade rotor header structures of external flapping hinge shock-absorbing sleeve |
| 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 |
| CN107140202A (en) * | 2017-05-12 | 2017-09-08 | 上海寅翅智能科技有限公司 | A kind of centrifugal flapping hinge rotor head |
| 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 |
| CN109677601A (en) * | 2019-02-22 | 2019-04-26 | 一飞智控(天津)科技有限公司 | Seesaw type unmanned plane rotor and unmanned plane |
| CN112046739A (en) * | 2020-08-06 | 2020-12-08 | 中国人民解放军总参谋部第六十研究所 | Rigid rotor hub of helicopter |
| 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 |
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| CN105292465B (en) | 2017-05-03 |
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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. |