CN106672204A - Tilting mechanism for tilting rotor wing airplane - Google Patents
Tilting mechanism for tilting rotor wing airplane Download PDFInfo
- Publication number
- CN106672204A CN106672204A CN201710137841.0A CN201710137841A CN106672204A CN 106672204 A CN106672204 A CN 106672204A CN 201710137841 A CN201710137841 A CN 201710137841A CN 106672204 A CN106672204 A CN 106672204A
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- CN
- China
- Prior art keywords
- rotary mechanism
- wing
- inclining rotary
- slide block
- guide rail
- Prior art date
- Legal status (The legal status 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 status listed.)
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- 230000005540 biological transmission Effects 0.000 abstract description 4
- 230000003247 decreasing effect Effects 0.000 abstract 1
- 230000033001 locomotion Effects 0.000 description 7
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a tilting mechanism for a tilting rotor wing airplane. The overall tilting mechanism comprises a stepping motor, a shaft coupler, a screw rod, a screw rod nut, a guide rail, a linear bearing, a fixed block, a sliding block, a supporting connection rod and the like. When the stepping motor rotates clockwise, the angle of attack of a wing is decreased, and the airplane is transitioned to a fixed wing mode; when the stepping motor rotates anticlockwise, the angle of attack of the wing is increased, the airplane is transitioned to a multi-rotor-wing mode. The tilting mechanism is actually a crank and slide block mechanism which is ingenious, simple and low in mass; however, in any flying state, the structure is relatively high in bearing capacity, and has a self-locking function. Moreover, the tilting mechanism is driven by the stepping motor, so as to realize mechanical design and control conveniently. To sum up, compared with conventional steering engine driving, the tilting mechanism has great advantages and a wide application prospect due to tilting modes such as gear transmission and hydraulic transmission.
Description
Technical field
The present invention relates to a kind of inclining rotary mechanism of the tilt rotor aircraft of tilting wing form, belongs to tiltrotor aircraft
Inclining rotary mechanism technical field.
Background technology
Tilt rotor aircraft combines the advantage of gyroplane and fixed wing airplane, lead to pitch motion, realize gyroplane and
Conversion between fixed wing airplane, the VTOL of existing gyroplane, vertical flight ability have flying for fixed wing airplane concurrently again
The advantage such as scanning frequency degree is fast, flying height is big, voyage is remote, endurance is strong.In tilt rotor aircraft designing technique, its core
Point it is the design of inclining rotary mechanism, the existing kind of drive has servo driving, gear drive, hydraulic drive etc., the side of servo driving
Formula simple structure, load is less, and does not typically possess auto-lock function, is generally used on small-sized tilt rotor aircraft.Gear and liquid
The pressure kind of drive can have carrying, but its complex structure, and construction weight is excessive, causes take-off weight larger.In synthesis
The deficiencies in the prior art are stated, the present invention provides a kind of new inclining rotary mechanism.
The content of the invention
The purpose of the present invention is not enough present on existing inclining rotary mechanism technology, there is provided a kind of tilting wing formula is verted
The inclining rotary mechanism of gyroplane, the mechanism can realize more accurate tilt angle control, and with simple structure, weight
Gently, power transmission is larger, being capable of the functional characteristics such as self-locking.
The technical purpose of the present invention is realized by following arbitrary technical scheme.
A kind of inclining rotary mechanism for tiltrotor, the tiltrotor includes being installed on verting for fuselage roof
Wing, it is characterised in that:
The trailing edge and fuselage are hinged, and the inclining rotary mechanism drives the wing to vert along hinged place；
The inclining rotary mechanism includes motor, guide rail, slide block and support link, and slide block is led described described in the Motor drive
Translate on rail, the support link two ends are hinged respectively with the leading edge of the slide block and the wing.
Inclining rotary mechanism according to any of the above-described technical scheme, it is characterised in that the motor is motor.
Inclining rotary mechanism according to any of the above-described technical scheme, it is characterised in that the inclining rotary mechanism also includes leading screw 5
With feed screw nut 8, the slide block 4 and the feed screw nut 8 fix；The motor 12 drives leading screw 5 to rotate when rotating,
And then driving feed screw nut 8 to translate so that slide block 4 is translated on guide rail.
Inclining rotary mechanism according to any of the above-described technical scheme, it is characterised in that the inclining rotary mechanism also includes and slides
The linear bearing 9 that block 4 is fixed, the slide block 4 is translated by the linear bearing 9 on guide rail.
Inclining rotary mechanism according to any of the above-described technical scheme, it is characterised in that the guide rail is fixed relative to fuselage.
Inclining rotary mechanism according to any of the above-described technical scheme, it is characterised in that the guide rail is in 30- with fuselage axis
60 ° of angle.
In one more specifically technical scheme, the present invention provides a kind of inclining rotary mechanism for tiltrotor, whole
Body includes the parts such as motor, shaft coupling, leading screw, feed screw nut, guide rail, linear bearing, fixed block, slide block, support link,
Overall structure is fairly simple.The structure uses step motor drive, is easy to Machine Design and control realization.
Fixed block is constituted by two pieces, is both secured on fuselage；Leading screw and guide rail parallel are fixed between two fixed blocks, with
Fuselage axis is fixed on guide rail between two fixed blocks with screw in 30 ° to 60 ° of angle, and leading screw two ends are respectively embedded into axle
Hold, then be fixed on two fixed blocks, leading screw can rotate along own axes, but axis direction is spacing by fixed block；Motor
It is fixed on lower fixed block, its power output shaft is connected by shaft coupling with leading screw lower end, for driving leading screw along own axes
Rotate；Feed screw nut and linear bearing are respectively fitted on leading screw and guide rail, and feed screw nut and linear bearing be screwed in
On slide block, slide block limits their relative displacement, and they can only be moved along the axis direction simultaneously along leading screw and guide rail；Support
Connecting rod one end is hinged with slide block, and the other end is hinged with the rib at the leading edge of a wing；Trailing edge it is symmetrical two at be hinged with fuselage.
The substantially slider-crank mechanism of the inclining rotary mechanism.
When wing verts, step motor drive leading screw is rotated, and the convert rotational motion of leading screw is feed screw nut, linear bearing
With slide block along leading screw, the linear motion of guide rail, then, slide block drives support link motion, support link to drive wing again along machine
The wing is rotated with the pin joint of fuselage, realizes the conversion of offline mode.
Beneficial effects of the present invention include following any one：
1. the inclining rotary mechanism uses step motor drive, is easy to Machine Design and control realization；Lead screw guide rails structure will revolve
The dynamic pitch motion for being converted into linear motion and then driving wing of transhipment；The mechanism structure is simple, and lightweight, power transmission is larger, accounts for
Ground space is little and with auto-lock function, it is adaptable to the aircraft of various tilting wing formulas.
2. leading screw and guide rail parallel, with fuselage axis in 30 ° to 60 ° of angle；The effective travel and support link of slide block
Length quite, and the distance of two pin joints of support link is approximately the pin joint of wing front and rear edge in aircraft plane of symmetry upslide
1.4 times of the length of shadow, therefore, no matter aircraft be it is flat fly, hanging down flies or in transition stage, support link pin joint line with
All the time between 45 ° to 135 °, this causes support link uniform force to the angle of wing front and rear edge pin joint line, safety compared with
It is high.It is also possible to make during wing verts, the space that support link movement locus are streaked is less, reduces and fuselage
The probability that other parts are interfered.
Description of the drawings
With reference to the accompanying drawings and examples the present invention is further described
Fig. 1 is schematic diagram during aircraft verts；
Fig. 2 is the detail view at lead screw guide rails；
Fig. 3 is the flat winged state diagrammatic side views of aircraft；
Fig. 4 is the vertical winged state diagrammatic side views of aircraft；
Fig. 5 is the vertical winged view of aircraft；
Fig. 6 is the flat winged view of aircraft；
In figure：1 wing, 2 fuselages, 3 support links, 4 slide blocks, 5 leading screws, 6 times fixed blocks, fixed block on 7,8 feed screw nuts,
9 linear bearings, 10 guide rails, 11 shaft couplings, 12, motor, 13 bearings, 14 inclining rotary mechanism.
Specific embodiment
In order that technical problem solved by the invention, technical scheme and beneficial effect become more apparent, below in conjunction with
Drawings and Examples, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein only to
The present invention is explained, is not intended to limit the present invention.
Aircraft is flat winged state when hypothesis starts, and now, slide block 4 is in guide rail 10 and the bottom of leading screw 5, with lower fixed block 6
Close, support link 3 is substantially conllinear with guide rail 10 and leading screw 5.Overall structure is as shown in Figure 3.
When motor 12 is rotated counterclockwise, aircraft flies to the winged status transition that hangs down by flat, and motor 12 is rotated, and drives silk
Thick stick nut 8, slide block 4 and linear bearing 9 are moved upwards together along leading screw 5 and guide rail 10, because slide block 4 is hinged with support link 3,
Support link 3 is also and then moved upwards, and with fuselage 2 be connected two pin joints of the wing 1 along trailing edge are verted, and realizes flying
The operation of verting of machine.
When wing 1 verts vertical state, aircraft completes transition, and in winged state of hanging down, now, slide block 4 is in guide rail 10
With the top of leading screw 5, close with upper fixed block 7, support link 3 is substantially conllinear with guide rail 10 and leading screw 5 again.Overall structure is such as
Shown in Fig. 4, a whole set of inclining rotary mechanism position aboard is as shown in Figure 5.
Claims (6)
1. a kind of inclining rotary mechanism for tiltrotor, the tiltrotor includes being installed on the verted machine of fuselage roof
The wing, it is characterised in that:
The trailing edge and fuselage are hinged, and the inclining rotary mechanism drives the wing to vert along hinged place；
The inclining rotary mechanism includes motor, guide rail, slide block and support link, and slide block is on the guide rail described in the Motor drive
Translation, the support link two ends are hinged respectively with the leading edge of the slide block and the wing.
2. inclining rotary mechanism according to claim 1, it is characterised in that the motor is motor.
3. inclining rotary mechanism according to claim 1, it is characterised in that the inclining rotary mechanism also includes leading screw 5 and leading screw spiral shell
Mother 8, the slide block 4 and the feed screw nut 8 fix；The motor 12 drives leading screw 5 to rotate when rotating, and then drives
Feed screw nut 8 is translated so that slide block 4 is translated on guide rail.
4. inclining rotary mechanism according to claim 1, it is characterised in that the inclining rotary mechanism also includes and slide block 4 fixes
Linear bearing 9, the slide block 4 is translated by the linear bearing 9 on guide rail.
5. inclining rotary mechanism according to claim 1, it is characterised in that the guide rail is fixed relative to fuselage.
6. inclining rotary mechanism according to claim 1, it is characterised in that the guide rail is with fuselage axis in 30 ° to 60 ° of folder
Angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710137841.0A CN106672204A (en) | 2017-03-09 | 2017-03-09 | Tilting mechanism for tilting rotor wing airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710137841.0A CN106672204A (en) | 2017-03-09 | 2017-03-09 | Tilting mechanism for tilting rotor wing airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106672204A true CN106672204A (en) | 2017-05-17 |
Family
ID=58825985
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710137841.0A Pending CN106672204A (en) | 2017-03-09 | 2017-03-09 | Tilting mechanism for tilting rotor wing airplane |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018333A (en) * | 2018-09-28 | 2018-12-18 | 北京清航紫荆装备科技有限公司 | A kind of reclining device and tilt rotor helicopter |
| CN110143275A (en) * | 2018-12-29 | 2019-08-20 | 上海歌尔泰克机器人有限公司 | Multi-rotor unmanned aerial vehicle |
| CN110435887A (en) * | 2019-08-30 | 2019-11-12 | 深圳智航无人机有限公司 | A kind of vert structure and the vertically taking off and landing flyer of aircraft |
| CN111516866A (en) * | 2020-04-29 | 2020-08-11 | 燕山大学 | Single-drive tilting dual-rotor aircraft |
| CN113212747A (en) * | 2021-05-18 | 2021-08-06 | 浙江鸿鹄翼航空科技有限公司 | Propeller tilting mechanism of fixed-wing aircraft |
| CN113232852A (en) * | 2021-05-11 | 2021-08-10 | 重庆大学 | Transmission mechanism for wings of tilt rotor aircraft |
| CN113371191A (en) * | 2021-07-22 | 2021-09-10 | 广东汇天航空航天科技有限公司 | Rotor wing tilting mechanism, tilting rotor wing aerocar and flying device |
| CN114476047A (en) * | 2021-12-03 | 2022-05-13 | 南昌三瑞智能科技有限公司 | Mechanism that verts of rotor unmanned aerial vehicle motor verts |
| CN114506451A (en) * | 2022-04-21 | 2022-05-17 | 西北工业大学 | Rotor unmanned aerial vehicle verts |
| CN117446163A (en) * | 2023-12-22 | 2024-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Redundancy tilting control mechanism of tilting rotorcraft |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0754620A1 (en) * | 1995-07-21 | 1997-01-22 | Freiherr von Wilmowsky, Kaspar | Tilt rotor helicopter |
| 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 |
| CN103466087A (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 tilting mechanism for tilt rotor aircraft |
| CN105667783A (en) * | 2016-02-29 | 2016-06-15 | 南京信息工程大学 | Tiliting fixed-wing water unmanned plane with power structure |
| CN106426270A (en) * | 2016-12-15 | 2017-02-22 | 徐航 | Mechanical arm joint structure |
| CN206634198U (en) * | 2017-03-09 | 2017-11-14 | 北京天宇新超航空科技有限公司 | A kind of inclining rotary mechanism for tiltrotor |
-
2017
- 2017-03-09 CN CN201710137841.0A patent/CN106672204A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0754620A1 (en) * | 1995-07-21 | 1997-01-22 | Freiherr von Wilmowsky, Kaspar | Tilt rotor helicopter |
| 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 |
| 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 |
| CN103466087A (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 tilting mechanism for tilt rotor aircraft |
| CN105667783A (en) * | 2016-02-29 | 2016-06-15 | 南京信息工程大学 | Tiliting fixed-wing water unmanned plane with power structure |
| CN106426270A (en) * | 2016-12-15 | 2017-02-22 | 徐航 | Mechanical arm joint structure |
| CN206634198U (en) * | 2017-03-09 | 2017-11-14 | 北京天宇新超航空科技有限公司 | A kind of inclining rotary mechanism for tiltrotor |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018333A (en) * | 2018-09-28 | 2018-12-18 | 北京清航紫荆装备科技有限公司 | A kind of reclining device and tilt rotor helicopter |
| CN109018333B (en) * | 2018-09-28 | 2024-03-29 | 北京清航紫荆装备科技有限公司 | Tilting device and tilting rotor helicopter |
| CN110143275A (en) * | 2018-12-29 | 2019-08-20 | 上海歌尔泰克机器人有限公司 | Multi-rotor unmanned aerial vehicle |
| CN110143275B (en) * | 2018-12-29 | 2023-01-10 | 上海歌尔泰克机器人有限公司 | Multi-rotor unmanned aerial vehicle |
| CN110435887A (en) * | 2019-08-30 | 2019-11-12 | 深圳智航无人机有限公司 | A kind of vert structure and the vertically taking off and landing flyer of aircraft |
| CN111516866B (en) * | 2020-04-29 | 2022-08-19 | 燕山大学 | Single-drive tilting dual-rotor aircraft |
| CN111516866A (en) * | 2020-04-29 | 2020-08-11 | 燕山大学 | Single-drive tilting dual-rotor aircraft |
| CN113232852A (en) * | 2021-05-11 | 2021-08-10 | 重庆大学 | Transmission mechanism for wings of tilt rotor aircraft |
| CN113232852B (en) * | 2021-05-11 | 2023-05-09 | 重庆大学 | Transmission mechanism for tilting rotorcraft wing |
| CN113212747A (en) * | 2021-05-18 | 2021-08-06 | 浙江鸿鹄翼航空科技有限公司 | Propeller tilting mechanism of fixed-wing aircraft |
| CN113371191A (en) * | 2021-07-22 | 2021-09-10 | 广东汇天航空航天科技有限公司 | Rotor wing tilting mechanism, tilting rotor wing aerocar and flying device |
| CN114476047A (en) * | 2021-12-03 | 2022-05-13 | 南昌三瑞智能科技有限公司 | Mechanism that verts of rotor unmanned aerial vehicle motor verts |
| CN114476047B (en) * | 2021-12-03 | 2024-02-13 | 南昌三瑞智能科技有限公司 | Tilting mechanism of tilting rotor unmanned aerial vehicle motor |
| CN114506451A (en) * | 2022-04-21 | 2022-05-17 | 西北工业大学 | Rotor unmanned aerial vehicle verts |
| CN117446163A (en) * | 2023-12-22 | 2024-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Redundancy tilting control mechanism of tilting rotorcraft |
| CN117446163B (en) * | 2023-12-22 | 2024-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Redundancy tilting control mechanism of tilting rotorcraft |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170517 |
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