CN104816825B - A kind of flexible folding exhibition rotor - Google Patents
A kind of flexible folding exhibition rotor Download PDFInfo
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- CN104816825B CN104816825B CN201510172816.7A CN201510172816A CN104816825B CN 104816825 B CN104816825 B CN 104816825B CN 201510172816 A CN201510172816 A CN 201510172816A CN 104816825 B CN104816825 B CN 104816825B
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Abstract
The invention discloses a kind of flexible folding exhibition rotor, including the outer section of blade, blade inner segment, big disk, roundel internal link stopper, roundel, chute, propeller hub, slide block, main shaft, steering wheel, trousers, motor, spacing roller, latch；The flexible folding exhibition rotor that the present invention provides can not only well realize the function of VTOL, and the telescopic process used time is few, and design level speed is high, and big disk can produce lift during flat flying；The flexible folding exhibition rotor that the present invention provides meets the requirements such as intensity, rigidity, pneumatic, weight and the fatigue life of aircraft rotary wing structure design, does not has a negative impact use, the maintainability of aircraft simultaneously.
Description
Technical field
The invention belongs to composite aircraft rotor structure design field, be specifically related to composite aircraft rotor and shrink setting of fold mechanism
Meter.
Background technology
The superior function being proposed to comprehensive helicopter and fixed wing airplane of composite aircraft concept, but, rotor is with fixing
The common existence of the wing typically can occur bigger aerodynamic interference.Generally, composite aircraft is to pursue hanging down of helicopter
Fall and the high-performance cruise performance of fixed-wing, according to this thinking, typically can subtract in the high-performance cruise stage in the design of composite aircraft
The aerodynamic drag of low rotor.The interference problem of rotor and fixed-wing is the problem that composite aircraft high-performance cruise be must pull against.
At present, composite aircraft designed also in the exploratory stage, and the interference problem of rotor is the most well answered.Existing
Rotor at composite aircraft is typically all locked in downwind position or unsettled do not retrain.Thus and thus, meeting in flight course
Produce no small interference drag.
It addition, rotor size issue when carrier-based helicopter is received into hangar is the most prominent, some helicopter is due to rotor radius
Excessive can not take in hangar.
Outstanding composite aircraft design, when being parked in hangar, aircraft is taken up space little, and during high-performance cruise, aerodynamic interference is little.
But, only reduce rotor radius and the rotor disk loading of aircraft can be made excessive, it may appear that the problem of some row, such as rotary speed
High.Do not reduce rotor radius, but locked for rotor the biggest in downwind position or unsettled aerodynamic interference.This just requires design
Person considers the telescopic folding problem of rotor.
Summary of the invention
The invention aims to solve the problems referred to above, the kind that the design for combined type aircraft requires and rotor interference exists
Plant weak point, propose the flexible folding of one and open up rotor.
A kind of flexible folding exhibition rotor, including the outer section of blade, blade inner segment, big disk, roundel internal link stopper, roundel, cunning
Groove, propeller hub, slide block, main shaft, steering wheel, trousers, motor, spacing roller, latch；
The outer section one end of blade is connected with blade inner segment, and the other end of blade inner segment connects propeller hub, and propeller hub passes through latch connection sliding block,
The outer section of blade can deflect 135 ° relative to blade inner segment, and the outer section of blade is provided with locking mechanism with blade inner segment junction, works as oar
Leaf is under the fully extended state, and the outer section of blade is locked by locking mechanism with blade inner segment；
Being provided with recessed in big disk, roundel is positioned at recessed, and roundel and big disk are respectively equipped with chute, in chute is divided into
Outer two sections, lay respectively on roundel and big disk, in trousers, also be provided with chute, with the chute phase on big disk and roundel
Correspondence, upper end of slide block connects trousers chute, and lower end connects big disk and roundel upper hopper chute, and slide block can slide on chute；
Being provided with gap between bottom and the recessed bottom surface of big disk of roundel, big disk is coaxially disposed with roundel, main shaft one end
Connecting the trousers center of circle by bearing, the other end connects the center of circle of big disk by clutch, and the center of circle of roundel is also by clutch
Device connects main shaft, and roundel is provided with limited post, and the bottom of big disk is provided with arcuate groove, and limited post is positioned at arcuate groove, roundel
Can be around main axis 90 ° relative to big disk, roundel is arranged over four pieces of internal link stoppers, and four pieces of internal link stoppers are around main shaft
Arrange, for axial symmery shape；The four pieces of fixing connection in link stopper one end roundels, the other end is fixing connects trousers, and motor is fixed on
Between chute and main shaft, motor output shaft connection sliding block, the edge of big disk, chute be respectively provided on two sides with a spacing roller,
The two ends of spacing roller connect big disk and trousers by bearing respectively.
It is an advantage of the current invention that:
(1) the flexible folding exhibition rotor that the present invention provides can not only well realize the function of VTOL, and the telescopic process used time
Few, design level speed is high, and big disk can produce lift during flat flying；
(2) present invention provide flexible folding exhibition rotor meet aircraft rotary wing structure design intensity, rigidity, pneumatic, weight and
The requirements such as fatigue life, do not have a negative impact to use, the maintainability of aircraft simultaneously.
Accompanying drawing explanation
Fig. 1 is the flexible folding exhibition fully deployed schematic diagram of rotor blade；
Fig. 2 is that flexible folding exhibition rotor blade shrinks schematic diagram completely；
Fig. 3 is that flexible folding exhibition rotor blade folds schematic diagram completely；
Fig. 4 is flexible folding exhibition rotor overall appearance figure；
Fig. 5 is rotary-wing root section schematic enlarged-scale view；
Fig. 6 is that rotor folds position enlarged drawing；
Fig. 7 is propeller hub and attachment means；
In figure:
1, blade outer section 2, blade inner segment 3, big disk
4, the internal link stopper 5 of roundel, roundel 6, propeller hub and slide block
7, chute 8, propeller hub 9, slide block
10, main shaft 11, steering wheel 12, trousers
13, motor 14, spacing roller 15, latch
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is described in further detail.
The one of the present invention flexible folding exhibition rotor, as shown in Figures 1 to 7, including blade outer section 1, blade inner segment 2, great circle
Dish 3, roundel internal link stopper 4, roundel 5, chute 7, propeller hub 8, slide block 9, main shaft 10, steering wheel 11, trousers
12, motor 13, spacing roller 14, latch 15.
As it is shown in figure 1, the outer section 1 of blade is connected with pin by horizontal auricle with blade inner segment 2, the outer section 1 of blade is relative to oar
Deflectable 135 ° of leaf inner segment 2, the details at link sees Fig. 6.Under the fully extended state shown in Fig. 1, the outer section of blade
1 and blade inner segment 2 locked by locking mechanism at the rear portion of junction.Locking mechanism details see Fig. 6, after the outer section 1 of blade
Edge stretches out a vertical auricle, and the latch that auricle has level is empty, has a steering wheel 11 to control latch in blade inner segment 2
Into and out.
As it is shown in figure 1, blade inner segment 1 is connected by propeller hub 8 with slide block 9, details sees Fig. 7, slide block 9 and propeller hub
8 are connected by latch 15.The type of attachment of propeller hub 8 and blade inner segment 1 is the propeller hub on-link mode (OLM) of common general helicopter.
In FIG, slide block 9 is connected with chute 7, and slide block 9 can do slip relatively relative to chute 7, thus realizes blade
Stretching of (blade inner segment 1 and outer section 2 general name of blade).Chute 7 is divided into inside and outside two sections, lays respectively at roundel 5 and great circle
On dish 3, roundel 5 and big disk 3 can relatively rotate.Chute 7 has four roads, and cross is in the center of disk.This
In it should be noted that also there is chute the lower section of trousers 12, this chute is corresponding with the inner segment of the chute 7 on roundel 5,
And keep relative invariant position.The i.e. top of slide block 9 and the chute of trousers 12 connects, and bottom is connected with chute 7.
Being the detailed construction of roundel 5 shown in Fig. 5, roundel 5 is positioned at the inside of big disk 3.As it was previously stated, roundel 5
Can relatively rotate with big disk 3, big disk 3 inside has recessed, is the annular more slightly larger than roundel 5, just can put
Putting roundel 5, their center is all connected with main shaft 10, is connected by clutch (market can be bought) the most respectively, it is possible to achieve it
And the disengagement of main shaft 10 and joint.Some gap between the bottom surface of the bottom of roundel 5 and the recessed annulus of big disk 3,
Also having position limiting structure, i.e. roundel 5 bottom can stretch out one piece not at the cylinder in the center of circle, the bottom of corresponding big disk 3 can be held
The arcuate groove around main shaft of one only 90 °, cylinder can only move in arcuate groove, thus limits relatively turning of big roundel
Dynamic angle.They can relatively rotate 90 °.
Also there are four pieces of internal link stoppers 4 in Fig. 2 and Fig. 3 it can be seen that the top of roundel 5, and four pieces of link stoppers are arranged around main shaft,
It it is axisymmetric form.Four pieces of link stoppers 4 and roundel 5 are welding (or bonding) relations, are connected, and no longer have fortune relatively
Dynamic, it is trousers 12 above four pieces of link stoppers, trousers 12 is also connected with internal link stopper and glues dead.The center of trousers 12 and
Main shaft 10 is connected by bearing.
According to Fig. 5, motor 13 is arranged in the inside of roundel, and between chute 7 and main shaft 10, one has two.?
Representing with cylinder in Fig. 5, they are connected by cable wire and slide block 9, and tractive controls the contraction of relative slide block respectively, to shrink
Blade.Motor uses direct driving motor, and it has many good qualities, and can meet use requirement.Cable wire and slide block 9 are directly welded.
As shown in Figure 4, spacing roller 14 is arranged in the edge of big disk, the both sides of chute 7, has 8.Down through
Bearing connects big disk 5 and trousers 12, can limit the motion of outer section blade, so that roundel 3 and big disk 5
Time differential, blade (blade inner segment 2, the outer section 1 of blade) can fold, and receives in trousers 12.Spacing roller is in other figures
Display, is not the relation in order to see miscellaneous part clearly.
The design point of the present invention essentially consists in the realization that rotor blade (1 and 2) shrinks and folds.In order to make compact conformation, alleviate
The purposes such as weight, the scheme that the formal character slide block 9 of contraction combines with chute 7.Propeller hub 8 is fixedly connected on slide block 9,
The folding and unfolding of rotor can be realized by controlling the slide block 9 motion on chute 7.In order to reduce space occupancy rate, slide block 9
Driving means, selects to rotate with motor to be wound around the form driving cable wire thus pull slide block 9 to move along a straight line, and rotor blade launches then
Centrifugal force by rotating skids off, and simple and reliable saves again big quantity space and weight.The design folded essentially consists in internal and external section blade
The accurate control of connectivity problem and folding angles.Internal and external section blade adds auricle in the place near leading edge and connects, and the second half section sets
Putting lock to connect, during folding and unfolding, internal and external section blade relatively rotates angle is 135 °, and so design can realize in relative rotation
Meanwhile, space interference problem is avoided to greatest extent.When internal and external section blade arrives the limit position in roundel 5 with slide block 9
When putting, inner segment blade portion is stuck in roundel 5, is rotated by roundel 5 and drives inner segment blade to rotate, disengages inside and outside simultaneously
The lock of section blade connects, and by means of the spacing roller 14 of big disk 3 rim track both sides, outer section of blade can take in trousers
In 12.
For realizing fall of hanging down, the aircraft of assembling mechanism is during takeoff and landing, and rotor blade is in the fully extended state,
The all of parts of mechanism all rotate around main shaft 10.After having taken off, aircraft is converted into put down and flies state, or it is complete to land
Facilitating aircraft to receive storehouse, rotor blade first to carry out shrinking folding again；Reverse situation, rotor blade first turns back flat, then
Extended by the effect of centrifugal force.Large and small disk is connected by clutch with main shaft 10, utilizes aircraft relevant control to fill
Put control clutch to carry out at any time stablizing engaging accurately and disengaging control.Between large and small disk, it is provided with position limiting structure, makes
Roundel 5 relative to big disk 3 counterclockwise and turn clockwise 90 ° can just block afterwards and together with move.Now tie
Close accompanying drawing by as follows for whole folding and unfolding process prescription:
Fig. 1 is mechanism's rotor the fully extended state.Helicopter main shaft 10 direction of rotation is counterclockwise, big roundlet in take-off process
Dish all engages holding synchronous axial system with main shaft.When shrinking rotor blade, it is first turned on motor 13, drives slide block 9 and propeller hub 8
Return, by four blade folding and unfoldings to fixed position, as shown in Figure 2.Next roundel 5 is disengaged with main shaft 10, due to
Friction eceleration, it will produce rotating clockwise relative to big disk 3, simultaneously roundel 5 band movable slider 9 and propeller hub 6,
Blade inner segment 2 rotates, and the lock decontroling blade internal and external section connects, and the outer section 1 of blade and blade inner segment 2 separate, until blade
Folding puts in place.After roundel 5 half-twist just locked with big disk 3, slowly slow down until stopping, disk is fixed, and completes
To the flat conversion flying pattern, as shown in Figure 3.
When reverse situation releases rotor, big disk 3 disengages with main shaft 10, keeps the state that roundel 5 engages with main shaft 10,
Ramping up, roundel 5 i.e. produces rotating counterclockwise relative to big disk 3, with big disk 3 after relatively rotating 90 °
Block and locked, afterwards big disk 3 is engaged with main shaft 10, internal and external section blade can be controlled and launch in line.Recycling
Blade is thrown away and snaps into relevant position and i.e. completes by rotary centrifugal force.
Fig. 4 is overall appearance figure, and big disk 3 bottom is designed for approximate slab, and trousers 12 is circular arc, puts down at aircraft and flies
Time, rotor profile is generally the pattern of a kind of lifting body, it is provided that part lift.Roundel 5 outward appearance is cylindrical shape
Shape designs, symmetrical four openings in side, inside sets chute 7, chute 7 centrosymmetry, decussation.
Fig. 6 is blade folded portion, and the outer section 1 of blade is the complete blade with joint, connects blade inner segment by attachment lug
2.Blade inner segment 2 is provided with locking mechanism, is used for controlling the folding of rotor.
Claims (1)
1. a flexible folding exhibition rotor, including the outer section of blade, blade inner segment, big disk, the internal block of roundel, roundel,
Chute, propeller hub, slide block, main shaft, steering wheel, trousers, motor, spacing roller, latch；
The outer section one end of blade is connected with blade inner segment one end, and the other end of blade inner segment connects propeller hub, and propeller hub connects sliding by latch
Block, the outer section of blade can deflect 135 ° relative to blade inner segment, and the outer section of blade is provided with locking mechanism with blade inner segment junction,
Under blade is in the fully extended state, the outer section of blade is locked by locking mechanism with blade inner segment；One is had in blade inner segment
Servos control latch into and out；
Being provided with recessed in big disk, roundel is positioned at recessed, and roundel and big disk are respectively equipped with chute, in chute is divided into
Outer two sections, lay respectively on roundel and big disk, in trousers, also be provided with chute, with the chute phase on big disk and roundel
Correspondence, upper end of slide block connects trousers chute, and lower end connects big disk and roundel upper hopper chute, and slide block can slide on chute；
Being provided with gap between bottom and the recessed bottom surface of big disk of roundel, big disk is coaxially disposed with roundel, main shaft one end
Connecting the trousers center of circle by bearing, the other end connects the center of circle of big disk by clutch, and the center of circle of roundel is also by clutch
Device connects main shaft, and roundel is provided with limited post, and the bottom of big disk is provided with arcuate groove, and limited post is positioned at arcuate groove, roundel
Can be around main axis 90 ° relative to big disk, roundel is arranged over four pieces of internal blocks, and four pieces of internal blocks are around main shaft
Arrange, for axial symmery shape；The four pieces of fixing connection in block one end roundels, the other end is fixing connects trousers, and motor is fixed on
Between chute and main shaft, motor output shaft connection sliding block, the edge of big disk, chute be respectively provided on two sides with a spacing roller,
The two ends of spacing roller connect big disk and trousers by bearing respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510172816.7A CN104816825B (en) | 2015-04-13 | 2015-04-13 | A kind of flexible folding exhibition rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510172816.7A CN104816825B (en) | 2015-04-13 | 2015-04-13 | A kind of flexible folding exhibition rotor |
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| Publication Number | Publication Date |
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| CN104816825A CN104816825A (en) | 2015-08-05 |
| CN104816825B true CN104816825B (en) | 2016-08-31 |
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| CN106915460B (en) * | 2017-02-22 | 2019-04-26 | 北京航空航天大学 | A kind of folding exhibition rotor mechanism |
| CN106986018A (en) * | 2017-05-12 | 2017-07-28 | 西华酷农无人机产业园运营有限公司 | A kind of telescopic unmanned plane of propeller |
| WO2019033691A1 (en) * | 2017-08-15 | 2019-02-21 | 罗琮贵 | High-speed flying method and ring wing aircraft |
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| TR202022410A1 (en) * | 2020-12-30 | 2022-07-21 | Tusas Tuerk Havacilik Ve Uzay Sanayii Anonim Sirketi | Rotary wing aircraft. |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4573871A (en) * | 1984-08-29 | 1986-03-04 | The United States Of America As Represented By The Secretary Of The Army | X-Wing aircraft circulation control |
| US5211538A (en) * | 1991-11-27 | 1993-05-18 | Bell Helicopter Textron Inc. | Method for folding helicopter main rotor blades |
| CN101384480A (en) * | 2005-12-22 | 2009-03-11 | 艾伦·J·杰贝诺 | Retractable lifting blades for aircraft |
| EP2492192A2 (en) * | 2011-02-28 | 2012-08-29 | The Boeing Company | Disc rotor retraction system |
| CN103723272A (en) * | 2014-01-05 | 2014-04-16 | 曹乃承 | Aircraft and transformation method for structural morphology of aircraft in flight |
| CN104260878A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Four-rotor aircraft rack with capacity of automatic folding and spreading |
-
2015
- 2015-04-13 CN CN201510172816.7A patent/CN104816825B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4573871A (en) * | 1984-08-29 | 1986-03-04 | The United States Of America As Represented By The Secretary Of The Army | X-Wing aircraft circulation control |
| US5211538A (en) * | 1991-11-27 | 1993-05-18 | Bell Helicopter Textron Inc. | Method for folding helicopter main rotor blades |
| CN101384480A (en) * | 2005-12-22 | 2009-03-11 | 艾伦·J·杰贝诺 | Retractable lifting blades for aircraft |
| EP2492192A2 (en) * | 2011-02-28 | 2012-08-29 | The Boeing Company | Disc rotor retraction system |
| CN103723272A (en) * | 2014-01-05 | 2014-04-16 | 曹乃承 | Aircraft and transformation method for structural morphology of aircraft in flight |
| CN104260878A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Four-rotor aircraft rack with capacity of automatic folding and spreading |
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| CN104816825A (en) | 2015-08-05 |
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Inventor after: Bao Rui Inventor after: Wan Zhiqiang Inventor after: Wang Qianwei Inventor after: Gao Yuan Inventor after: Yan De Inventor after: Jiang Chongwen Inventor after: Wang Yaokun Inventor after: Li Daochun Inventor before: Li Daochun Inventor before: Wan Zhiqiang Inventor before: Wang Qianwei Inventor before: Gao Yuan |
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