CN104816825B - A kind of flexible folding exhibition rotor - Google Patents

A kind of flexible folding exhibition rotor Download PDF

Info

Publication number
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
Authority
CN
China
Prior art keywords
blade
roundel
big disk
chute
segment
Prior art date
Application number
CN201510172816.7A
Other languages
Chinese (zh)
Other versions
CN104816825A (en
Inventor
鲍蕊
万志强
王乾威
高源�
严德
蒋崇文
王耀坤
李道春
Original Assignee
北京航空航天大学
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 北京航空航天大学 filed Critical 北京航空航天大学
Priority to CN201510172816.7A priority Critical patent/CN104816825B/en
Publication of CN104816825A publication Critical patent/CN104816825A/en
Application granted granted Critical
Publication of CN104816825B publication Critical patent/CN104816825B/en

Links

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

A kind of flexible folding exhibition rotor

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.
CN201510172816.7A 2015-04-13 2015-04-13 A kind of flexible folding exhibition rotor CN104816825B (en)

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

Publications (2)

Publication Number Publication Date
CN104816825A CN104816825A (en) 2015-08-05
CN104816825B true CN104816825B (en) 2016-08-31

Family

ID=53727357

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201510172816.7A CN104816825B (en) 2015-04-13 2015-04-13 A kind of flexible folding exhibition rotor

Country Status (1)

Country Link
CN (1) CN104816825B (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105416578B (en) * 2015-12-10 2017-04-12 江苏唯天智能无人机研发有限公司 wearable unmanned aerial vehicle
CN106915460B (en) * 2017-02-22 2019-04-26 北京航空航天大学 A kind of folding exhibition rotor mechanism
CN110282133A (en) * 2017-08-15 2019-09-27 郑小燕 The flat winged method of flying saucer and wing ring machine
CN110081001B (en) * 2018-01-26 2020-08-07 兰永庆 Mechanical telescopic invisible fan

Citations (6)

* Cited by examiner, † Cited by third party
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

Patent Citations (6)

* Cited by examiner, † Cited by third party
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

Also Published As

Publication number Publication date
CN104816825A (en) 2015-08-05

Similar Documents

Publication Publication Date Title
US10538321B2 (en) Tri-rotor aircraft capable of vertical takeoff and landing and transitioning to forward flight
US10556700B2 (en) Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades
US20180065737A1 (en) Personal aircraft
JP6191039B2 (en) VTOL machine
US20180072413A1 (en) Rotating wing assemblies for tailsitter aircraft
US10625852B2 (en) Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades
US20170144746A1 (en) Tiltrotor Aircraft having Rotary and Non Rotary Flight Modes
US10144509B2 (en) High performance VTOL aircraft
US4469294A (en) V/STOL Aircraft
US4116405A (en) Airplane
US3592412A (en) Convertible aircraft
US7267300B2 (en) Aircraft capable of vertical and short take-off and landing
US9387929B2 (en) Vertical takeoff and landing (“VTOL”) aircraft
CN104369635B (en) A kind of air-ground amphibious vehicles
CN105882959A (en) Aircraft capable of vertical takeoff
CN103144769B (en) Pneumatic layout of vertical taking-off and landing aircraft with tilted duct
EP3299290B1 (en) Rotating proprotor arrangement for a tiltrotor aircraft
US6086016A (en) Gyro stabilized triple mode aircraft
US6974105B2 (en) High performance VTOL convertiplanes
CN103318407B (en) A kind of discrete control system of coaxial rotor depopulated helicopter steerable system
US8733690B2 (en) Lightweight vertical take-off and landing aircraft and flight control paradigm using thrust differentials
US20060016930A1 (en) Sky hopper
US5240204A (en) Lift generating method and apparatus for aircraft
US7946527B2 (en) Aircraft with fixed, swinging and folding wings
US8511603B2 (en) Roadable aircraft with collapsible wings and ductless fan

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
EXSB Decision made by sipo to initiate substantive examination
SE01 Entry into force of request for substantive examination
COR Change of bibliographic data
CB03 Change of inventor or designer information

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

C14 Grant of patent or utility model
GR01 Patent grant