CN201472667U - Dual pitch main rotor structure of helicopter - Google Patents
Dual pitch main rotor structure of helicopter Download PDFInfo
- Publication number
- CN201472667U CN201472667U CN2009202336435U CN200920233643U CN201472667U CN 201472667 U CN201472667 U CN 201472667U CN 2009202336435 U CN2009202336435 U CN 2009202336435U CN 200920233643 U CN200920233643 U CN 200920233643U CN 201472667 U CN201472667 U CN 201472667U
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- tilting frame
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Abstract
A dual pitch main rotor structure of helicopter comprises two groups of same rotors, a main shaft and a blade pitch control device. Each group of rotor comprises n blades. The angle between each two blades is same and n is a natural number larger than 2. Each blade is rotatably connected with the main shaft. Two kinds of blade pitch control devices are provided. Each group of rotor is respectively connected with a blade pitch control device. The dual pitch main rotor structure of helicopter can be widely used for the main rotor structure of helicopter, helicopter model, unmanned helicopter, aerial helicopter, toy helicopter, etc. The structure causes the helicopter to obtain high stability and reliability through a simple structure.
Description
Technical field:
The utility model belongs to rotor craft control technology field, specifically is the dual pitch main rotor of a kind of autogyro structure.
Background technology:
Each blade in the world today in the main rotor structure of autogyro is controlled by same structure all respectively, and through adjusting meticulously, makes each blade state consistency in the running, and the blade of rotation remains in the plane.Autogyro is according to the direction of the variation change of flight on this plane and stablizing of maintenance flight.But the problem that this mode is brought is, in order to tackle the air dynamic behaviour of air-flow in the flight course and rotor itself, and the design of control structure and adjust can be very complicated.And rely on the flight stability that complicated electronic equilibrium system stablizes autogyro.
Summary of the invention:
In order to solve the above-mentioned problems in the prior art, the utility model proposes the dual pitch main rotor of a kind of new autogyro structure, concrete technical scheme is as follows:
The dual pitch main rotor of a kind of autogyro structure comprises 2 groups of identical rotors, main shaft and blade pitch control setup; Every group of rotor comprises n blade, and angulation is identical between every blade, is
N is a natural number, and n 〉=2 (this structure is applicable to four or the above rotors of four blades, and as n=2, then angulation is 90 degree between two groups of blades); Each blade and main shaft are rotationally connected; Blade pitch control setup has two kinds, and every group of rotor connects a kind of blade pitch control setup respectively.Described blade pitch control setup is respectively flight stability pitch control setup and flight maneuver pitch control setup.Described flight stability pitch control setup is the physical construction of Bel's effect; Described flight maneuver pitch control setup is the uncommon physical construction of effect that draws.
The physical construction of Bel's effect comprises bob-weight and balance plumb bob head connecting rod; One end of bob-weight ball head connecting rod is connected with bob-weight, and the other end is connected with the blade of corresponding rotor; The point of connection of bob-weight ball head connecting rod and blade departs from the pivot center of blade and main shaft.Described bob-weight has n only, is located between adjacent two blades, becomes with adjacent blades
Angle.A described n bob-weight is identical to the distance of spindle axis.
Described wishing draws the physical construction of effect to comprise tilting frame and tilting frame ball head connecting rod, and tilting frame is provided with bulb; One end of tilting frame ball head connecting rod is connected by bulb with tilting frame, and the other end is connected with the blade of corresponding rotor; The point of connection of tilting frame ball head connecting rod and blade departs from the pivot center of blade and main shaft; Described tilting frame is provided with and helicopter control system bonded assembly connecting device.
Also comprise the oar folder; Oar presss from both sides an end and is connected with blade, and the other end and main shaft are rotationally connected; Described bob-weight ball head connecting rod is connected with blade by the oar folder; Described tilting frame ball head connecting rod is connected with blade by the oar folder.
The physical construction of described Bel's effect is connected with the physical construction of Xi La effect, constitutes synchronous mixing displacement structure; Mixing displacement structure is to be provided with n connecting rod between the described n bob-weight synchronously, one section of connecting rod is connected with bob-weight, the other end and other connecting rod are connected on the axial location of main shaft, each rod connection point place is provided with bulb, and this bulb is connected by bulb on the tilting frame and ball head connecting rod with tilting frame.
The utility model can be widely used in the main rotor structure of autogyro, model autogyro, unmanned helicopter, take photo by plane autogyro and toy helicopter etc., this novel mechanical structure is equivalent to adorn the flight that individual mechanical gyro makes that autogyro can be highly stable in the main rotor structure, just make autogyro reach the stability and the reliability of height with simple structure.
Description of drawings:
Fig. 1 is the utility model front view;
Fig. 2 is the utility model birds-eye view;
Fig. 3 is synchronous mixing displacement structural representation.
The specific embodiment:
Is that example is described as follows below in conjunction with accompanying drawing with four blade rotor group physical constructions:
The dual pitch main rotor of a kind of autogyro structure comprises 2 groups of identical rotors, main shaft 6 and blade pitch control setup; Every group of rotor comprises n blade, and angulation is identical between every blade, is
In this example, n is 2.Each blade and main shaft 6 are rotationally connected; Blade pitch control setup has two kinds, and every group of rotor connects a kind of blade pitch control setup respectively.Described blade pitch control setup is respectively the physical construction of Bel's effect and the physical construction of Xi La effect.
The physical construction of Bel's effect comprises bob-weight 2 and balance plumb bob head connecting rod 4; One end of bob-weight ball head connecting rod 4 is connected with bob-weight 2, and the other end is connected with A2 with the blade A1 of corresponding rotor; The point of connection of bob-weight ball head connecting rod 4 and blade A1 and A2 departs from the pivot center of blade and main shaft 6.Described bob-weight 2 has 2, is located between adjacent two blades (as A1 and B1), with adjacent blades angle at 45.Described 2 bob-weights 2 are identical to the distance in main shaft 6 axle center.
Described wishing draws the physical construction of effect to comprise tilting frame 1 and tilting frame ball head connecting rod 3, and 1 is provided with bulb on the tilting frame; One end of tilting frame ball head connecting rod 3 and tilting frame 1 are connected by bulb, and the other end is connected with B2 with the blade B1 of corresponding rotor; The point of connection of tilting frame ball head connecting rod 3 and blade B1 and B2 departs from the pivot center of blade B1 and B2 and main shaft 6; Described tilting frame 1 is provided with and helicopter control system bonded assembly connecting device.
Also comprise oar folder 5; Oar presss from both sides 5 one ends and is connected with blade, and the other end and main shaft 6 are rotationally connected; Described bob-weight ball head connecting rod 4 is connected with A2 with blade A1 by oar folder 5; Described tilting frame ball head connecting rod 3 is connected with B2 with blade B1 by oar folder 5.
This is Fig. 1,2 for example, among the figure, and double-type blade A1 and A2, double-type blade B1 and B2, tilting frame 1, bob-weight 2, tilting frame ball head connecting rod 3, bob-weight ball head connecting rod 4, oar folder 5, main shaft 6.
Two bob-weights 2 and the physical construction (equalizing gear) that connects the balance pole composition Bel effect of bob-weight 2, directly by connecting the pitch of pole bulb control A1 and A2 two blades, the gyro effect that equalizing gear forms when main shaft 6 rotations makes autogyro remain flight stability.
By the uncommon physical construction (control mechanism) that draws effect that tilting frame 1 is formed, directly by connecting the pitch of pole bulb control B1, B2 two blades, the direction skew that helicopter is handled to tilting frame 1 realizes the motor-driven control to helicopter.Tilting frame 1 is subjected to helicopter Flight By Wire mechanism controls.
Dual pitch main rotor structure of the present utility model is that the pitch with each blade in the main rotor structure is subjected to two different structure controls respectively; the formed plane of blade of rotation; only when keeping a stable flare maneuver (as hover or stable before fly; side flies etc.) blade of rotation can remain on same plane; when unsure state occurring; or during the change of flight attitude; two plane of rotations will appear in the blade of rotation, and the immixture power of two plane of rotations makes the corresponding change of flight attitude of autogyro.
This mechanism is that each main wing of same main shaft 6 and the synchronous rotation of equidirectional is the angle by each rotor of two same rotor groups of control system difference direct control of different nature, thereby produces different pitch.As two groups of rotors of four blades in this example, blade pitch control setup has two kinds, and every group of blade pitch control setup connects wherein one group of opposed two blade of control respectively; For in eight blade rotor groups, every group of blade pitch control setup connects wherein one group of opposed four blade of control respectively; For six blade rotor groups, every group of blade pitch control setup connects wherein one group of opposed three blade of control respectively.
Two group blade pitch control setups are made up of different control structures respectively, representative type, and as in this example, the physical construction with Bel's effect then its objective is autogyro is tended towards stability under the control of Bel's effect automatically; Another draws the physical construction of effect with uncommon, its objective is that then to make autogyro handle autogyro by effector's requirement under uncommon control of drawing effect motor-driven.
When the uncommon physical construction that draws effect is done flight maneuver, the physical construction of Bel's effect can produce acting in opposition and offset the motor-driven component of part, make motor-driven slowing up, can do soft airline operation, but in the occasion that requires to do fast reserve, then realize by the distance of adjusting bob-weight 2 and main shaft 6 axis, when bob-weight 2 apart from the very near position of main shaft 6 axis, can do the high-speed maneuver of aircraft; Extreme case is that bob-weight 2 is zero with the distance of main shaft 6 axis, does not then have Bel's effect.
Rotor can be installed in same plane of rotation, also can be distributed in two plane of rotations up and down of same axle, is coaxial equidirectional synchronous rotation.
The physical construction of described Bel's effect is connected with the physical construction of Xi La effect, constitutes synchronous mixing displacement structure; Mixing displacement structure is to be provided with n connecting rod between the described n bob-weight synchronously, one section of connecting rod is connected with bob-weight, the other end and other connecting rod are connected on the axial location of main shaft, each rod connection point place is provided with bulb, and this bulb is connected by bulb on the tilting frame and ball head connecting rod with tilting frame.In this example, link to each other with ball head connecting rod C3 with bulb C2 on the tilting frame 1 as the bulb C1 at the connecting rod C4 center of bob-weight among Fig. 32, connecting rod C4 is moved up and down with tilting frame 1, the positive and negative pitch of two groups of blades was changed synchronously, the independence that keep two groups of controls simultaneously make autogyro finish the 3D action of stable inverted flight etc.Adjust the position of bob-weight on connecting rod C4 pole,, can make the 3D high-speed maneuver of aircraft when bob-weight 2 is placed on the position that connecting rod C4 leans on main shaft most.
Claims (10)
1. the dual pitch main rotor of an autogyro structure comprises rotor, main shaft and blade pitch control setup; Described rotor has identical 2 groups, and every group of rotor comprises n blade, and angulation is identical between every blade, is
N is natural number and n 〉=2; Each blade and main shaft are rotationally connected; It is characterized in that blade pitch control setup has two kinds, every group of rotor connects a kind of blade pitch control setup respectively.
2. the dual pitch main rotor of autogyro according to claim 1 structure is characterized in that described blade pitch control setup is respectively flight stability pitch control setup and flight maneuver pitch control setup.
3. the dual pitch main rotor of autogyro according to claim 2 structure is characterized in that described flight stability pitch control setup is the physical construction of Bel's effect; Described flight maneuver pitch control setup is the uncommon physical construction of effect that draws.
4. the dual pitch main rotor of autogyro according to claim 3 structure is characterized in that the physical construction of described Bel's effect comprises bob-weight and balance plumb bob head connecting rod; One end of bob-weight ball head connecting rod is connected with bob-weight, and the other end is connected with the blade of corresponding rotor; The point of connection of bob-weight ball head connecting rod and blade departs from the pivot center of blade and main shaft.
5. the dual pitch main rotor of autogyro according to claim 4 structure is characterized in that described bob-weight has n only, is located between adjacent two blades, becomes with adjacent blades
Angle.
6. the dual pitch main rotor of autogyro according to claim 5 structure is characterized in that a described n bob-weight is identical to the distance of spindle axis.
7. according to the dual pitch main rotor of the arbitrary described autogyro of claim 2～5 structure, it is characterized in that describedly uncommonly drawing the physical construction of effect to comprise tilting frame and tilting frame ball head connecting rod, tilting frame is provided with bulb; One end of tilting frame ball head connecting rod is connected by bulb with tilting frame, and the other end is connected with the blade of corresponding rotor; The point of connection of tilting frame ball head connecting rod and blade departs from the pivot center of blade and main shaft; Described tilting frame is provided with and helicopter control system bonded assembly connecting device.
8. the dual pitch main rotor of autogyro according to claim 7 structure is characterized in that also comprising the oar folder; Oar presss from both sides an end and is connected with blade, and the other end and main shaft are rotationally connected.
9. the dual pitch main rotor of autogyro according to claim 8 structure is characterized in that described bob-weight ball head connecting rod is connected with blade by the oar folder; Described tilting frame ball head connecting rod is connected with blade by the oar folder.
10. the dual pitch main rotor of autogyro according to claim 7 structure is characterized in that the physical construction of described Bel's effect and the physical construction of Xi La effect are connected, and constitute synchronous mixing displacement structure; Mixing displacement structure is to be provided with n connecting rod between the described n bob-weight synchronously, one section of connecting rod is connected with bob-weight, the other end and other connecting rod are connected on the axial location of main shaft, each rod connection point place is provided with bulb, and this bulb is connected by bulb on the tilting frame and ball head connecting rod with tilting frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202336435U CN201472667U (en) | 2009-07-31 | 2009-07-31 | Dual pitch main rotor structure of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202336435U CN201472667U (en) | 2009-07-31 | 2009-07-31 | Dual pitch main rotor structure of helicopter |
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| Publication Number | Publication Date |
|---|---|
| CN201472667U true CN201472667U (en) | 2010-05-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202336435U Expired - Fee Related CN201472667U (en) | 2009-07-31 | 2009-07-31 | Dual pitch main rotor structure of helicopter |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104494810A (en) * | 2014-12-14 | 2015-04-08 | 惠阳航空螺旋桨有限责任公司 | Coaxial contra-rotating type propeller pitch-varying device |
| CN104527968A (en) * | 2014-12-14 | 2015-04-22 | 惠阳航空螺旋桨有限责任公司 | Coaxial contra-rotation type screw propeller |
| CN105059536A (en) * | 2015-08-07 | 2015-11-18 | 胡家祺 | Rotor wing device with variable pitch and multi-rotor-wing aircraft |
| CN106005389A (en) * | 2016-05-27 | 2016-10-12 | 燕山大学 | Helicopter rotor wing compound motion parallel driving device |
| CN111332462A (en) * | 2020-02-24 | 2020-06-26 | 北京理工大学 | Portable small-sized cylinder type coaxial reverse-propeller three-blade rotor type unmanned aerial vehicle |
-
2009
- 2009-07-31 CN CN2009202336435U patent/CN201472667U/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN104494810A (en) * | 2014-12-14 | 2015-04-08 | 惠阳航空螺旋桨有限责任公司 | Coaxial contra-rotating type propeller pitch-varying device |
| CN104527968A (en) * | 2014-12-14 | 2015-04-22 | 惠阳航空螺旋桨有限责任公司 | Coaxial contra-rotation type screw propeller |
| CN104494810B (en) * | 2014-12-14 | 2018-02-06 | 惠阳航空螺旋桨有限责任公司 | A kind of coaxial contrarotating Propeller variable pitch device |
| CN104527968B (en) * | 2014-12-14 | 2018-02-06 | 惠阳航空螺旋桨有限责任公司 | A kind of coaxial contrarotating propeller |
| CN105059536A (en) * | 2015-08-07 | 2015-11-18 | 胡家祺 | Rotor wing device with variable pitch and multi-rotor-wing aircraft |
| CN105059536B (en) * | 2015-08-07 | 2018-01-02 | 胡家祺 | Varying pitch rotor driver and multi-rotor aerocraft |
| CN106005389A (en) * | 2016-05-27 | 2016-10-12 | 燕山大学 | Helicopter rotor wing compound motion parallel driving device |
| CN106005389B (en) * | 2016-05-27 | 2018-01-23 | 燕山大学 | Lifting airscrew compound motion parallel drive unit |
| CN111332462A (en) * | 2020-02-24 | 2020-06-26 | 北京理工大学 | Portable small-sized cylinder type coaxial reverse-propeller three-blade rotor type unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100519 Termination date: 20120731 |