CN102431646A - Dual-whirl wing tilting mechanism of single-engine tilting whirl wing aerocraft - Google Patents
Dual-whirl wing tilting mechanism of single-engine tilting whirl wing aerocraft Download PDFInfo
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- CN102431646A CN102431646A CN2011103856176A CN201110385617A CN102431646A CN 102431646 A CN102431646 A CN 102431646A CN 2011103856176 A CN2011103856176 A CN 2011103856176A CN 201110385617 A CN201110385617 A CN 201110385617A CN 102431646 A CN102431646 A CN 102431646A
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- power transmission
- transmission gear
- verts
- tilting
- axle sleeve
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- 230000005540 biological transmission Effects 0.000 claims abstract description 48
- 238000005461 lubrication Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 6
- 210000001624 Hip Anatomy 0.000 description 2
- 230000001429 stepping Effects 0.000 description 2
- 241000893018 Armeria Species 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000000875 corresponding Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000001050 lubricating Effects 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 230000001360 synchronised Effects 0.000 description 1
Abstract
The invention discloses a dual-whirl wing tilting mechanism of a single-engine tilting whirl wing aerocraft. The mechanism comprises a power transmission gear box and two nacelle gear boxes, wherein the power transmission gear box is provided with a power input end and two power output ends; each nacelle gear box is provided with an input end and an output end; the two power output ends of the power transmission gear box are respectively connected with the input ends of two nacelles; a tilting shaft sleeve is respectively connected to the two sides of the power transmission gear box and is fixedly connected with a tilting connecting rod; the tilting connecting rod is fixedly connected with the nacelles; a turbine is fixed on a shell of the power transmission gear box; and a worm rod matched with the turbine is arranged at the front end of the power transmission gear box. The problem on the design of a tilting mechanism of a tilting whirl wing aerocraft of which the single engine power is transferred through the power transmission gear box that is arranged in the middle is solved through the dual-whirl wing tilting mechanism; and the dual-whirl wing tilting mechanism is of a crafty and simple structure and has a self-locking function. The dual-whirl wing tilting mechanism is driven through a motor, and is convenient to mechanically design and control; and inconvenience caused by hydraulic drive can be overcome.
Description
Technical field
The present invention relates to a kind of monomotor tiltrotor aircraft bispin wing inclining rotary mechanism, belong to tiltrotor aircraft inclining rotary mechanism technical field.
Background technology
Tiltrotor aircraft is a kind of aircraft of unique properties, and it can carry out VTOL or hover as conventional helicopters, also can high-performance cruise flight as the screw propeller fixed wing aircraft.This aircraft has VTOL, hovers, low-latitude flying, high-performance cruise, big load, and than the ability of oceangoing voyage journey, the specific effect of performance in fields such as troops' deployment fast, landing operations and the civilian disaster relief/speedily carry out rescue work has broad application prospects.
Current tiltrotor aircraft adopts double-engined drive more, and inclining rotary mechanism can directly design in nacelle, and the synchronized operation of two cover mechanisms realizes that nacelle verts; Also can design within fuselage, realize that through the pipe link that verts the both sides nacelle verts.Small-sized tiltrotor aircraft adopts a kind of design in back more, can make Flight Vehicle Structure compact, simple, helps expendable weight and reduces the influence to the pneumatic external form of wing.
Yet when using separate unit engine drive tiltrotor aircraft; Be installed on the inclining rotary mechanism design within the fuselage like employing; Because engine in front of rear wheel mid-engine, the power transmission gear case generally is positioned at waist, and this makes inclining rotary mechanism and Power train be on the same axis; Inclining rotary mechanism has increased design difficulty in need the power transmission gear case being contained in.
Summary of the invention
Goal of the invention: based on single-engined tiltrotor aircraft; Its power transmission gear case is mid-; The present invention proposes a kind of inclining rotary mechanism that drives twin rotor system, relate to vert bindiny mechanism and driver train, power transmission gear case and transmission device are included in its inside; The simplified structure design can be practiced thrift cost and can conveniently be controlled again.
For realizing above-mentioned purpose, technical scheme of the present invention is:
A kind of monomotor tiltrotor aircraft bispin wing inclining rotary mechanism comprises power transmission gear case and two nacelle gears case, and described power transmission gear case has a power intake and two clutch ends; Described nacelle gear case has an input end and a mouth, and two clutch ends of described power transmission gear case are connected with the input end of two nacelles respectively; It is characterized in that: connect the axle sleeve that verts respectively in described power transmission gear case both sides; The described axle sleeve that verts is fixedly linked with the pipe link that verts; The pipe link that verts is captiveed joint with nacelle; On described power transmission gear box casing, be fixed with a turbine, be provided with a worm screw that cooperates with described turbine at power transmission gear case front end.
Said worm gear is positioned at power transmission gear box casing outside center position; Two clutch ends at described power transmission gear case are respectively arranged with the takeoff output axle sleeve; One end of the described axle sleeve that verts links to each other with described takeoff output axle sleeve through sliding bearing sleeve, and the other end of the axle sleeve that verts is connected fixing with the pipe link that verts through key.
Described worm screw is arranged on the propeller shaft sleeve inside of verting, and the two ends of worm screw are provided for respectively locating and lubricated antifriction-bearing box, and the axle sleeve below of verting is fixed with motor; Described worm gear is half ring gear, and the power transmission gear box casing rotates with turbine, and the slewing area of power transmission gear box casing is-5 ° ~ 95 °.
The present invention is a kind of to relate to vert bindiny mechanism and driver train based on single-engined tiltrotor aircraft bispin wing inclining rotary mechanism, specifically comprises the axle sleeve that verts, the pipe link that verts, turbine and worm, vert driver train and fuselage support lubrication assembly.Driving engine transmits power within the gear case through connection power-transfer clutch, gear case power input shaft, and gear case is delivered to the two ends nacelle with power through gear wheel reversing again.The bindiny mechanism of verting is positioned at the Poewr transmission mechanism outside, and worm gear is positioned at power transmission gear case center position, and both sides are fixed with the axle sleeve that verts, and the axle sleeve that verts is connected with power transmission gear case takeoff output end cap through sliding bearing sleeve.The power transmission gear-box case is designed to circular-arc, makes things convenient for inclining rotary mechanism to rotate.The axle sleeve that verts is fixed with the pipe link that verts, and vert pipe link and nacelle are fixed, the motion of verting of realization nacelle and rotor.When the pipe link that verts passed the fuselage side plate, the supporting fuselage that is designed with supported lubrication assembly, in sliding bearing sleeve is arranged, realize that fuselage is to the support of the pipe link that verts, spacing and lubricating effect.The worm gear dead ahead is designed with the driver train that verts, in worm screw is arranged, with the worm gear routing motion.Worm screw is controlled by motor-driven.Worm-and-wheel gear has self-lock ability, need not to provide extra locking moment to realize the nacelle locking.Motor-driven control is relatively accurately simple, is convenient to control and realizes.
The invention has the beneficial effects as follows: monomotor tiltrotor aircraft bispin wing inclining rotary mechanism will combine with Power train and the bispin wing inclining rotary mechanism that mid-power transmission gear case is a core effectively; Simplified physical construction, the inclining rotary mechanism motor-driven has been simplified mode.
Description of drawings
Fig. 1 is for being equipped with tiltrotor aircraft work scheme drawing of the present invention;
Fig. 2 is a profile lateral plan of the present invention;
Fig. 3 is the bindiny mechanism's cutaway view that verts involved in the present invention;
Fig. 4 is the driver train cutaway view that verts involved in the present invention;
Fig. 5 is that the driver train that verts involved in the present invention cooperates scheme drawing.
The specific embodiment
Below in conjunction with accompanying drawing the present invention is done further detailed description.
Shown in Figure 1 is to fly view before this tiltrotor aircraft.Fuselage 1 is the main body of tiltrotor aircraft, and inside has comprised various machineries and electronic machine.Wing 2,5 is loaded on the fuselage 1, and nacelle 3,6 is equipped with at the two ends of wing 2,5 respectively, and nacelle is responsible for verting, and rotor 4,7 is installed on the nacelle 3,6, rotates with nacelle, realizes the conversion of flight mode.
Shown in Figure 2 is fuselage 1 inner structure scheme drawing.As shown in Figure 2; Driving engine 11 is fixed on the frame 10; Reinforce through engine supports 12, its mouth is connected with starter receiver 13 and power-transfer clutch 14, and power-transfer clutch connects output shaft to power transmission gear case (housing 26); The power transmission gear case cooperates through gear pair, outputs power within the nacelle gear case.The bindiny mechanism of verting is positioned at outside the Power train.Worm gear 21 is positioned at power transmission gear box casing 26 centers, and both sides connect the axle sleeve 19,22 that verts, and the axle sleeve 19,22 that verts links to each other with the pipe link 15,24 that verts respectively, and the pipe link 15,24 that verts links to each other with nacelle 3,6 respectively.Fuselage supports lubrication assembly 16 captive joint fuselage side plates 18 and wing side plate 17, in order to support the lubricated pipe link 15 that verts; Fuselage supports lubrication assembly 23 captive joint fuselage side plates 25 and wing side plate 27, in order to support the lubricated pipe link 24 that verts.The driver train 20 that verts is installed on the worm gear dead ahead, and its inner worm and wheel routing motion is realized the inclining rotary mechanism drive controlling.
The bindiny mechanism of verting is as shown in Figure 3; Need to prove; This patent is mainly introduced verting of tiltrotor aircraft and is connected and driver train; Power transmission is not an emphasis, therefore schemes medium power transmission gear case (housing 26) and gear case takeoff output end cap 45,46 and does not analyse and observe, and the gear case inner structure does not describe in detail yet.
As shown in Figure 3, the gear box casing 26 of power transmission gear case is positioned at waist, and its inside is equipped with the spiral bevel gear pair, and engine power is exported through deceleration and after turning to.Gear box casing 26 left sides are fixed with takeoff output axle sleeve 46, and gear case power take-off shaft 47 passes from power take-off shaft cover 46 centres and joins with coupler 48, and coupler 48 joins with power drive shaft 49, and power drive shaft 49 imports power within the nacelle 6 into.Worm gear 21 is positioned at gear box casing 26 outside center positions, and the left side is fixed with the axle sleeve 22 that verts, and the axle sleeve 22 that verts links to each other with takeoff output axle sleeve 46 through sliding bearing sleeve 33, plays the location, supports and lubricated effect.Axle sleeve 22 external forms of verting design according to Power train, and in coupler 48 was contained in, its terminal connection through key with the pipe link 24 that verts was fixed.The pipe link 24 that verts is captiveed joint with nacelle 6, can realize verting of nacelle 6.The pipe link 24 that verts is passing in the fuselage side plate 25, and fuselage supports lubrication assembly 23 and provides the support of the pipe link 24 that verts and lubricated.Fuselage supports lubrication assembly 23 and comprises fixed hub 29, sliding bearing sleeve 28, pad 30 and jam nut 31.Fixed hub 29 passes fuselage side plate 25 and wing side plate 27, and through jam nut 31 fixing and lockings, sliding bearing sleeve 29 is equipped with in its inside, links to each other with the pipe link 24 that verts, and pad 30 has the effect of protection fixed hub 29.Pipe link 24 relevant positions of verting have screw thread, cooperate with setscrew nut 32, the location of the pipe link 24 of realizing verting.
As shown in Figure 3; Gear box casing 26 right sides are fixed with takeoff output axle sleeve 45; Gear case power take-off shaft 44 passes from power take-off shaft cover 45 centres and joins with coupler 43, and coupler 43 joins with power drive shaft 44, and power drive shaft 42 imports power within the nacelle 3 into.Worm gear 21 is positioned at gear box casing 26 outside center positions, and the right side is fixed with the axle sleeve 19 that verts, and the axle sleeve 19 that verts links to each other with takeoff output axle sleeve 45 through sliding bearing sleeve 36, plays the location, supports and lubricated effect.Axle sleeve 19 external forms of verting design according to Power train, and in coupler 45 was contained in, its terminal connection through key with the pipe link 15 that verts was fixed.The pipe link 15 that verts is captiveed joint with nacelle 3, can realize verting of nacelle 3.The pipe link 15 that verts is passing in the fuselage side plate 18, and fuselage supports lubrication assembly 16 and provides the support of the pipe link 15 that verts and lubricated.Fuselage supports lubrication assembly 16 and comprises fixed hub 40, sliding bearing sleeve 41, pad 39 and jam nut 38.Fixed hub 40 passes fuselage side plate 18 and wing side plate 17, and through jam nut 38 fixing and lockings, sliding bearing sleeve 41 is equipped with in its inside, links to each other with the pipe link 15 that verts, and pad 39 has the effect of protection fixed hub 40.Pipe link 15 relevant positions of verting have screw thread, cooperate with setscrew nut 37, the location of the pipe link 15 of realizing verting.
Fig. 4, cutaway view and cooperation scheme drawing for the driver train 20 that verts shown in Figure 5.Can know that worm screw 51 is equipped with in propeller shaft sleeve 34 inside of verting on the figure, with lubricated, axle sleeve 34 belows of verting are fixed with stepping motor 35 to worm screw 51 through antifriction-bearing box 50,52 location, rotate in order to drive worm screw 51.The driver train 20 that verts is fixed on the frame 10 through the propeller shaft sleeve 34 that verts; Power transmission gear box casing 26 is fixed on the frame 10 equally; Can find out from Fig. 5, worm screw 51 and worm gear 21 routing motions in the driver train 20 that verts, worm gear 21 comprises power transmission gear box casing 26 rotation purposes for reaching; With half ring gear excision, at both ends cuts out the shape of corresponding power transmission gear box casing 26 simultaneously.Power transmission gear box casing 26 for can reach inclining rotary mechanism can be outside it sideway swivel purpose, it is designed to the particular circle arcuation, nacelle is verted satisfied-5 ° ~ 95 ° area requirement.Sensor 53 is equipped with in power transmission gear box casing 26 belows, is used for the zeroing of stepping motor 35 initial positions.
Claims (3)
1. a monomotor tiltrotor aircraft bispin wing inclining rotary mechanism comprises power transmission gear case and two nacelle gears case, and described power transmission gear case has a power intake and two clutch ends; Described nacelle gear case has an input end and a mouth, and two clutch ends of described power transmission gear case are connected with the input end of two nacelles respectively; It is characterized in that: connect the axle sleeve that verts respectively in described power transmission gear case both sides; The described axle sleeve that verts is fixedly linked with the pipe link that verts; The pipe link that verts is captiveed joint with nacelle; On described power transmission gear box casing, be fixed with a turbine, be provided with a worm screw that cooperates with described turbine at power transmission gear case front end.
2. monomotor tiltrotor aircraft bispin wing inclining rotary mechanism according to claim 1; It is characterized in that: said worm gear is positioned at power transmission gear box casing outside center position; Two clutch ends at described power transmission gear case are respectively arranged with the takeoff output axle sleeve; One end of the described axle sleeve that verts links to each other with described takeoff output axle sleeve through sliding bearing sleeve, and the other end of the axle sleeve that verts is connected fixing with the pipe link that verts through key.
3. monomotor tiltrotor aircraft bispin wing inclining rotary mechanism according to claim 2; It is characterized in that: described worm screw is arranged on the propeller shaft sleeve inside of verting; The two ends of worm screw are provided for respectively locating and lubricated antifriction-bearing box, and the axle sleeve below of verting is fixed with motor; Described worm gear is half ring gear, and the power transmission gear box casing rotates with turbine, and the slewing area of power transmission gear box casing is-5 ° ~ 95 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103856176A CN102431646A (en) | 2011-11-29 | 2011-11-29 | Dual-whirl wing tilting mechanism of single-engine tilting whirl wing aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103856176A CN102431646A (en) | 2011-11-29 | 2011-11-29 | Dual-whirl wing tilting mechanism of single-engine tilting whirl wing aerocraft |
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| Publication Number | Publication Date |
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| CN102431646A true CN102431646A (en) | 2012-05-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2011103856176A Pending CN102431646A (en) | 2011-11-29 | 2011-11-29 | Dual-whirl wing tilting mechanism of single-engine tilting whirl wing aerocraft |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103010450A (en) * | 2012-11-20 | 2013-04-03 | 无锡市万凌钢铁有限公司 | Synchronous rotating mechanism for left and right wings of transport helicopter |
| CN103466088A (en) * | 2013-08-23 | 2013-12-25 | 中国航空工业集团公司西安飞机设计研究所 | Nacelle gear tilting mechanism for tilt rotor aircraft |
| CN103935510A (en) * | 2014-04-15 | 2014-07-23 | 西安交通大学 | Tilted four-rotor aircraft |
| CN108657426A (en) * | 2018-05-17 | 2018-10-16 | 谭小平 | Light-duty tilt rotor aircraft |
| CN108773475A (en) * | 2018-04-28 | 2018-11-09 | 成都航空职业技术学院 | The small-sized power general-purpose aircraft that verts of Three-wing-surface |
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| CN1458030A (en) * | 2003-05-26 | 2003-11-26 | 韩培洲 | Horizontal and vertical take-off and landing plane with tilted front rotary wing |
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| WO2007014531A1 (en) * | 2005-08-02 | 2007-02-08 | Peizhou Han | A vtol aircraft with tilt front rotors |
| CN101875399A (en) * | 2009-10-30 | 2010-11-03 | 北京航空航天大学 | Tilt rotor aircraft adopting parallel coaxial dual rotors |
| CN101962075A (en) * | 2010-10-18 | 2011-02-02 | 南京航空航天大学 | Tilting mechanism, running mode of tilting mechanism, application of tilting mechanism in tilting rotorcraft |
| CN101973398A (en) * | 2010-09-30 | 2011-02-16 | 南京航空航天大学 | Tilt rotation driving mechanism for tilt rotation nacelle of tilt rotor craft |
| WO2011018697A1 (en) * | 2009-08-11 | 2011-02-17 | Santino Pancotti | Tilt-rotor aircraft |
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2011
- 2011-11-29 CN CN2011103856176A patent/CN102431646A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1458030A (en) * | 2003-05-26 | 2003-11-26 | 韩培洲 | Horizontal and vertical take-off and landing plane with tilted front rotary wing |
| CN1754777A (en) * | 2004-09-30 | 2006-04-05 | 李环 | Vertical take-off and landing aircraft |
| WO2007014531A1 (en) * | 2005-08-02 | 2007-02-08 | Peizhou Han | A vtol aircraft with tilt front rotors |
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| CN101875399A (en) * | 2009-10-30 | 2010-11-03 | 北京航空航天大学 | Tilt rotor aircraft adopting parallel coaxial dual rotors |
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| CN101962075A (en) * | 2010-10-18 | 2011-02-02 | 南京航空航天大学 | Tilting mechanism, running mode of tilting mechanism, application of tilting mechanism in tilting rotorcraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103010450A (en) * | 2012-11-20 | 2013-04-03 | 无锡市万凌钢铁有限公司 | Synchronous rotating mechanism for left and right wings of transport helicopter |
| CN103466088A (en) * | 2013-08-23 | 2013-12-25 | 中国航空工业集团公司西安飞机设计研究所 | Nacelle gear tilting mechanism for tilt rotor aircraft |
| CN103935510A (en) * | 2014-04-15 | 2014-07-23 | 西安交通大学 | Tilted four-rotor aircraft |
| CN108773475A (en) * | 2018-04-28 | 2018-11-09 | 成都航空职业技术学院 | The small-sized power general-purpose aircraft that verts of Three-wing-surface |
| CN108657426A (en) * | 2018-05-17 | 2018-10-16 | 谭小平 | Light-duty tilt rotor aircraft |
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Free format text: CORRECT: INVENTOR; FROM: XU JINFA ZHANG LIANG GUO LINMAO XIA QINGYUAN TO: XU JINFA ZHANG LIANG XIA QINGYUAN GUO LINMAO |
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| C53 | Correction of patent for invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Xu Jinfa Inventor after: Zhang Liang Inventor after: Xia Qingyuan Inventor after: Guo Linmao Inventor before: Xu Jinfa Inventor before: Zhang Liang Inventor before: Guo Linmao Inventor before: Xia Qingyuan |
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
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Application publication date: 20120502 |