CN104816825A - Telescopic foldable rotor wing - Google Patents
Telescopic foldable rotor wing Download PDFInfo
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- CN104816825A CN104816825A CN201510172816.7A CN201510172816A CN104816825A CN 104816825 A CN104816825 A CN 104816825A CN 201510172816 A CN201510172816 A CN 201510172816A CN 104816825 A CN104816825 A CN 104816825A
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- roundel
- blade
- big disk
- chute
- fairing
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Abstract
The invention discloses a telescopic foldable rotor wing. The telescopic foldable rotor wing comprises outer blade sections, inner blade sections, a big disc, internal stoppers of a small disc, the small disc, slide grooves, propeller hubs, sliding blocks, a main shaft, steering engines, a cowling, a motor, limit rollers and plug pins. According to the telescopic foldable rotor wing disclosed by the invention, the function of perpendicularly ascending and descending is well realized, the time for extending and retracting is short, the speed of level flight is high, and the big disc can generate ascending force during the level flight. The telescopic foldable rotor wing disclosed by the invention conforms to the requirements for the strength, the rigidness, the air operation, the weight, the fatigue life and the like of the structural design of an aircraft rotor wing, and does not generate negative influences on the use and the maintenance of aircrafts.
Description
Technical field
The invention belongs to composite aircraft rotor structure design field, be specifically related to the design that composite aircraft rotor shrinks fold mechanism.
Background technology
The proposition of composite aircraft concept is the high performance in order to comprehensive helicopter and fixed wing aircraft, but the common existence of rotor and fixed-wing generally larger aerodynamic interference can occur.Generally, composite aircraft pursues hanging down of helicopter to fall the high-performance cruise performance with fixed-wing, according to this thinking, and generally can in the aerodynamic drag of high-performance cruise stage attenuating rotor in the design of composite aircraft.The interference problem of rotor and fixed-wing is the problem that composite aircraft high-performance cruise must overcome.
At present, composite aircraft design is also in the exploratory stage, and the interference problem of rotor is never well answered.The rotor of present composite aircraft is all generally locked in downwind position or unsettledly not retrain.Thus and thus, no small interference drag can be produced in flight course.
In addition, rotor size issue when carrier-based helicopter is received into hangar is also comparatively outstanding, and some helicopter can not take in hangar because rotor radius is excessive.
Outstanding composite aircraft design, when being parked in hangar, aircraft takes 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, there will be the problem of some row, as rotative speed is high.Do not reduce rotor radius, but locked for rotor downwind position or unsettled aerodynamic interference larger again.This just requires that designer considers the telescopic folding problem of rotor.
Summary of the invention
The object of the invention is to solve the problem, all weak points that designing requirement and rotor interference for combined type aircraft exist, proposing a kind of flexible folding exhibition rotor.
A kind of flexible folding exhibition rotor, comprises the outer section of blade, blade inner segment, big disk, roundel inner link stopper, roundel, chute, propeller hub, slide block, main shaft, steering wheel, fairing, motor, spacing roller, latch;
The outer section one end of blade is connected with blade inner segment, the other end of blade inner segment connects propeller hub, propeller hub is by latch connection sliding block, the outer section of blade can deflect 135 ° relative to blade inner segment, the outer section of blade and blade inner segment junction are provided with locking mechanism, under blade is in full extension state, it is locked that the outer section of blade and blade inner segment pass through locking mechanism;
Be provided with recessed in big disk, roundel is positioned at recessed, roundel and big disk are respectively equipped with chute, chute is divided into inside and outside two sections, lays respectively on roundel and big disk, is also provided with chute in fairing, corresponding with the chute on big disk and roundel, upper end of slide block connects fairing chute, and lower end connects big disk and roundel upper hopper chute, and slide block can slide on chute;
Gap is provided with between the bottom of roundel and the recessed bottom surface of big disk, big disk and roundel are coaxially arranged, main shaft one end connects the fairing center of circle by bearing, the other end connects the center of circle of big disk by power-transfer clutch, the center of circle of roundel also connects main shaft by power-transfer clutch, roundel is provided with limited post, the bottom of big disk is provided with deep-slotted chip breaker, limited post is positioned at deep-slotted chip breaker, roundel can around main axis 90 ° relative to big disk, be provided with four pieces of inner link stoppers above roundel, four pieces of inner link stoppers are arranged around main shaft, are axial symmery shape; Four pieces of link stopper one end are fixedly connected with roundel, the other end is fixedly connected with fairing, motor is fixed between chute and main shaft, motor output shaft connection sliding block, the edge of big disk, the both sides of chute are respectively equipped with a spacing roller, and the two ends of spacing roller connect big disk and fairing respectively by bearing.
The invention has the advantages that:
(1) flexible folding exhibition rotor provided by the invention well can not only realize the function of vertical takeoff and landing, and the telescopic process used time is few, and design level speed is high, and big disk can produce lift flat flying in journey;
(2) flexible folding exhibition rotor provided by the invention meets the requirements such as the intensity of aircraft rotary wing structure design, rigidity, pneumatic, weight and fatigue life, does not have a negative impact to the use of aircraft, maintainability simultaneously.
Accompanying drawing explanation
Fig. 1 is that flexible folding exhibition rotor blade launches schematic diagram completely;
Fig. 2 is that flexible folding exhibition rotor blade shrinks schematic diagram completely;
Fig. 3 is the completely folding schematic diagram of flexible folding exhibition rotor blade;
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 connecting device;
In figure:
1, blade outer section 2, blade inner segment 3, big disk
4, roundel inner link stopper 5, roundel 6, propeller hub and slide block
7, chute 8, propeller hub 9, slide block
10, main shaft 11, steering wheel 12, fairing
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.
One of the present invention flexible folding exhibition rotor, as shown in Figures 1 to 7, the outer section 1 of blade, blade inner segment 2, big disk 3, roundel inner link stopper 4, roundel 5, chute 7, propeller hub 8, slide block 9, main shaft 10, steering wheel 11, fairing 12, motor 13, spacing roller 14, latch 15 is comprised.
As shown in Figure 1, the outer section 1 of blade is connected with pin by horizontal auricle with blade inner segment 2, and the outer section 1 of blade can deflect 135 ° relative to blade inner segment 2, and the details of link place is see Fig. 6.Under the full extension state shown in Fig. 1, the outer section 1 of blade and blade inner segment 2 locked by locking mechanism at the rear portion of junction.Locking mechanism details are see Fig. 6, and the trailing edge of the outer section 1 of blade stretches out a vertical auricle, auricle have the latch of level empty, have a steering wheel 11 control the insertion of latch and extract in blade inner segment 2.
As shown in Figure 1, blade inner segment 1 is connected by propeller hub 8 with slide block 9, and details is see Fig. 7, and slide block 9 is connected by latch 15 with propeller hub 8.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 relative sliding relative to chute 7, thus realizes the flexible of blade (blade inner segment 1 and outer section 2 general name of blade).Chute 7 is divided into inside and outside two sections, and lay respectively on roundel 5 and big disk 3, roundel 5 and big disk 3 can relatively rotate.Chute 7 has four roads, and cross is in the center of disk.Here it should be noted that, also there is chute the below of fairing 12, and this chute is corresponding with the inner segment of the chute 7 on roundel 5, and keeps relative position constant.Namely the top of slide block 9 and the chute of fairing 12 connect, and bottom is connected with chute 7.
Be the detailed construction of roundel 5 shown in Fig. 5, roundel 5 is positioned at the inside of big disk 3.As previously mentioned, roundel 5 can relatively rotate with big disk 3, big disk 3 inside has recessed, the annular arrangement slightly larger than roundel 5, just in time can place roundel 5, their center is all connected with main shaft 10, is connected all respectively by power-transfer clutch (market can be bought), can realize disengagement and the joint of they and main shaft 10.Some gap between the bottom surface of the bottom of roundel 5 and the recessed annulus of big disk 3, also has position limiting structure, namely roundel 5 bottom can stretch out one piece not at the cylinder in the center of circle, the deep-slotted chip breaker around main shaft that one is only had 90 ° can be driven in the bottom of corresponding big disk 3, cylinder can only move in deep-slotted chip breaker, thus limits the angle in relative rotation of large roundel.They can relatively rotate 90 °.
Can see in Fig. 2 and Fig. 3 that the top of roundel 5 also has four pieces of inner link stoppers, 4, four pieces of link stoppers to arrange around main shaft, be axisymmetric form.Four pieces of link stoppers 4 and roundel 5 are welding (or bonding) relations, and being connected, no longer including relative motion, is fairing 12 above four pieces of link stoppers, and fairing 12 is also connected with inner link stopper and glues dead.The center of fairing 12 is connected by bearing with main shaft 10.
According to Fig. 5, motor 13 is arranged in the inside of roundel, and between chute 7 and main shaft 10, one has two.Represent with cylinder in Figure 5, they are connected with slide block 9 by cable wire, and tractive controls the contraction of relative slide block respectively, to shrink blade.Motor adopts direct driving motor, and it has many good qualities, and can meet operating needs.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, and the both sides of chute 7 have 8.Connect big disk 5 and fairing 12 down through bearing, the motion of outer section blade can be limited, thus make roundel 3 and big disk 5 differential time blade (blade inner segment 2, the outer section 1 of blade) can fold, receive fairing 12 li.Spacing roller is not display in other figure, is the relation in order to see miscellaneous part clearly.
Design point of the present invention is mainly that rotor blade (1 and 2) shrinks and folding realization.In order to make the object such as compact conformation, expendable weight, the scheme that the formal character slide block 9 of contraction combines with chute 7.Propeller hub 8 being fixedly connected on slide block 9, namely realizing the folding and unfolding of rotor by controlling the motion of slide block 9 on chute 7.In order to reduce space occupancy rate, the actuating device of slide block 9, select to rotate to be wound around with motor drive cable wire thus pull the form of slide block 9 straight-line motion, rotor blade launches then to skid off by the centnifugal force of rotation, simple and reliablely in turn saves large quantity space and weight.Folding design is mainly the connectivity problem of internal and external section blade and the accurate control of folding angles.Internal and external section blade adds auricle in the place near leading edge and connects, and the second half section arranges lock and connects, and in folding and unfolding process, internal and external section blade relatively rotates angle is 135 °, and design in realization simultaneously in relative rotation, can avoid space interference problem to greatest extent like this.When internal and external section blade arrives the end position in roundel 5 with slide block 9, inner segment blade portion is stuck in roundel 5, being rotated by roundel 5 drives inner segment blade to rotate, the lock of simultaneously throwing off internal and external section blade connects, by means of the spacing roller 14 of big disk 3 rim track both sides, outer section of blade can be taken in fairing 12.
Fall for realizing hanging down, the aircraft of assembling mechanism is taking off and in descent, rotor blade is in full extension state, and all parts of mechanism all rotate around main shaft 10.After having taken off, aircraft converts to put down and flies state, or storehouse received by the complete aircraft that facilitates that lands, and rotor blade will first carry out shrinking folding again; Reverse situation, rotor blade first turns back flat, then is extended by the effect of centnifugal force.Large and small disk is connected by power-transfer clutch with main shaft 10, utilizes aircraft relative control apparatus control clutch to carry out stable joint accurately at any time and controls with disengagement.Between large and small disk, be provided with position limiting structure, roundel 5 can be blocked afterwards just relative to big disk 3 conter clockwise and clickwise 90 ° and together with move.Now by reference to the accompanying drawings by as follows for whole folding and unfolding process prescription:
Fig. 1 is mechanism's rotor full extension state.Helicopter main shaft 10 hand of rotation is conter clockwise, and in take-off process, large roundel all engages with main shaft and keeps synchronous axial system.When shrinking rotor blade, first open motor 13, drive slide block 9 and propeller hub 8 travelling backwards, by four blade folding and unfoldings to fixed position, as shown in Figure 2.Next roundel 5 and main shaft 10 are thrown off, due to friction eceleration, it just can produce rotating clockwise relative to big disk 3, roundel 5 is with movable slider 9 and propeller hub 6, blade inner segment 2 to rotate simultaneously, the lock decontroling blade internal and external section connects, the outer section 1 of blade and blade inner segment 2 separately, put in place until blade is folding.Just locked with big disk 3 after roundel 5 half-twist, slowly slow down until stop, disk is fixed, and is accomplished to the flat conversion flying pattern, as shown in Figure 3.
When reverse situation releases rotor, big disk 3 and main shaft 10 are thrown off, keep the state that roundel 5 engages with main shaft 10, accelerate gradually, namely roundel 5 produces rotating counterclockwise relative to big disk 3, relatively rotate and to block with big disk 3 after 90 ° and locked, afterwards big disk 3 is engaged with main shaft 10, the expansion of internal and external section blade can be controlled in line.Blade throws away and snaps into relevant position and namely completes by recycling rotary centrifugal force.
Fig. 4 is overall appearance figure, and big disk 3 bottom is designed for approximate slab, and fairing 12 is circular arc, aircraft is flat fly time, rotor profile is a kind of pattern of lifting body generally, providing unit can divide lift.Roundel 5 outward appearance is cylindrical profile design, and Side symmetrical four openings, inside establish chute 7, chute 7 Central Symmetry, right-angled crossing.
Fig. 6 is blade folded part, and the outer section 1 of blade is the complete blade with joint, connects blade inner segment 2 by attachment lug.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, comprises the outer section of blade, blade inner segment, big disk, roundel inner link stopper, roundel, chute, propeller hub, slide block, main shaft, steering wheel, fairing, motor, spacing roller, latch;
The outer section one end of blade is connected with blade inner segment, the other end of blade inner segment connects propeller hub, propeller hub is by latch connection sliding block, the outer section of blade can deflect 135 ° relative to blade inner segment, the outer section of blade and blade inner segment junction are provided with locking mechanism, under blade is in full extension state, it is locked that the outer section of blade and blade inner segment pass through locking mechanism;
Be provided with recessed in big disk, roundel is positioned at recessed, roundel and big disk are respectively equipped with chute, chute is divided into inside and outside two sections, lays respectively on roundel and big disk, is also provided with chute in fairing, corresponding with the chute on big disk and roundel, upper end of slide block connects fairing chute, and lower end connects big disk and roundel upper hopper chute, and slide block can slide on chute;
Gap is provided with between the bottom of roundel and the recessed bottom surface of big disk, big disk and roundel are coaxially arranged, main shaft one end connects the fairing center of circle by bearing, the other end connects the center of circle of big disk by power-transfer clutch, the center of circle of roundel also connects main shaft by power-transfer clutch, roundel is provided with limited post, the bottom of big disk is provided with deep-slotted chip breaker, limited post is positioned at deep-slotted chip breaker, roundel can around main axis 90 ° relative to big disk, be provided with four pieces of inner link stoppers above roundel, four pieces of inner link stoppers are arranged around main shaft, are axial symmery shape; Four pieces of link stopper one end are fixedly connected with roundel, the other end is fixedly connected with fairing, motor is fixed between chute and main shaft, motor output shaft connection sliding block, the edge of big disk, the both sides of chute are respectively equipped with a spacing roller, and the two ends of spacing roller connect big disk and fairing respectively by bearing.
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 |
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| 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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| CN104816825A true CN104816825A (en) | 2015-08-05 |
| CN104816825B CN104816825B (en) | 2016-08-31 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2017097021A1 (en) * | 2015-12-10 | 2017-06-15 | 江苏唯天智能无人机研发有限公司 | Wearable unmanned aerial vehicle |
| CN106915460A (en) * | 2017-02-22 | 2017-07-04 | 北京航空航天大学 | One kind 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 |
| CN108382487A (en) * | 2018-04-09 | 2018-08-10 | 洛阳理工学院 | A kind of bio-robot having both flight and function of creeping |
| WO2019033691A1 (en) * | 2017-08-15 | 2019-02-21 | 罗琮贵 | High-speed flying method and ring wing aircraft |
| CN110081001A (en) * | 2018-01-26 | 2019-08-02 | 兰永庆 | A kind of mechanical-stretching stealth fan |
| CN112173098A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Novel control system and method for electric folding and unfolding of rotor wing |
| CN113386957A (en) * | 2021-07-29 | 2021-09-14 | 天马国际集团有限公司 | Pull formula rotor and aircraft |
| CN114275913A (en) * | 2021-12-28 | 2022-04-05 | 宜兴市惠众环保设备有限公司 | Low-power-consumption aeration oxygenation device for integrated sewage treatment |
| WO2022146286A1 (en) * | 2020-12-30 | 2022-07-07 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | Rotary wing air vehicle |
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| 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 |
| US7475847B2 (en) * | 2002-09-09 | 2009-01-13 | Gerbino Allen J | Retractable lifting blades for aircraft |
| US8784057B2 (en) * | 2011-02-28 | 2014-07-22 | The Boeing Company | Disc rotor retraction system |
| CN103723272B (en) * | 2014-01-05 | 2019-01-29 | 曹乃承 | The method of Flight Vehicle Structure modality conversion when aircraft and 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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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017097021A1 (en) * | 2015-12-10 | 2017-06-15 | 江苏唯天智能无人机研发有限公司 | Wearable unmanned aerial vehicle |
| CN106915460A (en) * | 2017-02-22 | 2017-07-04 | 北京航空航天大学 | One kind folding exhibition rotor mechanism |
| 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 |
| US11472547B2 (en) | 2017-08-15 | 2022-10-18 | Luo Conggui | High-speed flight method and coleopter |
| CN110081001A (en) * | 2018-01-26 | 2019-08-02 | 兰永庆 | A kind of mechanical-stretching stealth fan |
| CN108382487A (en) * | 2018-04-09 | 2018-08-10 | 洛阳理工学院 | A kind of bio-robot having both flight and function of creeping |
| CN112173098A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Novel control system and method for electric folding and unfolding of rotor wing |
| WO2022146286A1 (en) * | 2020-12-30 | 2022-07-07 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | Rotary wing air vehicle |
| CN113386957A (en) * | 2021-07-29 | 2021-09-14 | 天马国际集团有限公司 | Pull formula rotor and aircraft |
| CN114275913A (en) * | 2021-12-28 | 2022-04-05 | 宜兴市惠众环保设备有限公司 | Low-power-consumption aeration oxygenation device for integrated sewage treatment |
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| CN104816825B (en) | 2016-08-31 |
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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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