CN107697270A - Dismantled and assembled aileron mounting structure - Google Patents
Dismantled and assembled aileron mounting structure Download PDFInfo
- Publication number
- CN107697270A CN107697270A CN201710903750.3A CN201710903750A CN107697270A CN 107697270 A CN107697270 A CN 107697270A CN 201710903750 A CN201710903750 A CN 201710903750A CN 107697270 A CN107697270 A CN 107697270A
- Authority
- CN
- China
- Prior art keywords
- aileron
- bearing
- root
- dismantled
- coercive mechanism
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Mounting Of Bearings Or Others (AREA)
Abstract
The invention discloses a kind of dismantled and assembled aileron mounting structure, the watchfully rib machine of installation root aileron coercive mechanism, which extends, yearns for the skew of airfoil root direction, leaves space of the installation with bearing, dismantled and assembled aileron coercive mechanism；Another watchfully rib machine is disposed adjacent to aileron end, the bearing with through hole is housed on rib, as end aileron coercive mechanism；Root aileron coercive mechanism also includes overhanging load-carrying construction, overhanging load-carrying construction is used to install bearing fixed seat, it is connected by screw bolts between bearing fixed seat and overhanging load-carrying construction and wing cover, bolt connection realizes the dismounting of bearing fixed seat, and then realizes the dismounting of aileron；The middle-size and small-size high-speed unmanned aerial vehicle of thin airfoil internally completes the installation with bearing, dismantled and assembled aileron coercive mechanism in the limited aerofoil in space, it is dismantled and assembled that aileron is realized on the premise of high-speed unmanned aerial vehicle aerofoil aeroperformance is not influenceed, unmanned plane use cost is reduced, the cooperation installation of aileron rotating shaft-bearing reduces aileron by the risk of card, structural reliability height.
Description
Technical field
The invention belongs to Aircraft structural design field, suitable for middle-size and small-size high-speed unmanned aerial vehicle aileron mounting structure, especially
It is related to a kind of dismantled and assembled mounting structure of aileron.
Background technology
Aileron is mounted in the movable aerofoil on the outside of wing wingtip trailing edge, to ensure under defined all flight conditions pair
Aircraft carries out effective control of horizontal rolling, it is necessary to avoids awing because wing bending makes aileron stuck.
Thin airfoil small and medium size unmanned aerial vehicles wing wingtip structure height is small, and inner space is limited.Low-speed unmanned aerial vehicle is to pneumatic property
It can require low, coercive mechanism can be overhang in aerofoil surface and be connected with aileron, to realize the dismoutability of aileron.And the middle-size and small-size nothing of high speed
It is man-machine high to aerodynamic performance requirements, coercive mechanism is overhang not in aerofoil, increases gas-flow resistance and then influences the property of aircraft
Energy.
In the prior art due to the watchfully rib machine web space not mounting structure of bearing, watchfully rib machine can only be used
The mounting structure that upper connects bearing, root aileron coercive mechanism and end aileron coercive mechanism are coordinated using axle-hole, this installation
Although structure meets the requirement of aeroperformance, but aileron pin-ended point is all coordinated using axle-hole, and pivoting friction is big, easily
Generation aileron is by card phenomenon.It is not removable and aileron is integral with wing, the later stage during use, if aileron damage, machine
The wing, aileron are both needed to change, and substantially increase use cost.
The content of the invention
The purpose of the present invention is to be directed to above-mentioned the deficiencies in the prior art, there is provided one kind is applied to the middle-size and small-size high speed nothing of thin airfoil
The limited dismantled and assembled aileron mounting structure in man-machine wing structure inner space, being also applied for the middle-size and small-size high-speed unmanned aerial vehicle of thin airfoil can
Dismount on aerofoil.
To realize above-mentioned technical purpose, the technical scheme that the present invention takes is：Dismantled and assembled aileron mounting structure, including root
Aileron coercive mechanism and end aileron coercive mechanism, root aileron coercive mechanism and end aileron coercive mechanism are used to install fixed aileron；End
Portion's aileron coercive mechanism includes end watchfully rib machine and the bearing on rib web；Root aileron coercive mechanism includes root
Watchfully rib machine, bearing fixed seat, bearing, small cornual plate and dimension shape lid；The root watchfully rib machine is opened up along wing yearns for wing root
Portion direction is offset, to reserve the space for dismantled and assembled aileron coercive mechanism；Also include being arranged on watchfully rib machine web and wing
The overhanging load-carrying construction of skin shape fitting, the overhanging load-carrying construction are used to install bearing fixed seat, bearing fixed seat with it is outer
Stretch and be connected by screw bolts between load-carrying construction and wing cover；The bolt connection facilitates the dismounting of bearing fixed seat, enters
And realize the dismounting of aileron；
Further, there is the through hole with tolerance on the bearing, aileron rotating shaft is inserted directly into through hole, realizes aileron one
The installation for holding axle-hole to coordinate.
Further, the bearing is arranged on bearing fixed seat, in aileron rotating shaft insertion bearing；Realize aileron one end
The installation of axle-bearing fit；
Further, the small cornual plate is arranged on the watchfully rib machine web of root, and small cornual plate is provided with plate nut, is used for
It is fixedly connected with dimension shape lid.
The present invention is mainly made up of 6 parts：
(1) watchfully rib machine：That is wing load-carrying member, arrived for the moment of torsion that transmits aileron structure, the load transmission such as shearing
On wing main force support structure.The watchfully rib machine of 2 connection aileron coercive mechanisms, i.e. root watchfully rib machine and end machine are arranged on wing
Thriving rib, wherein root watchfully rib machine, which extend, yearns for airfoil root direction skew about 35mm, outer on the web of root watchfully rib machine
Load-carrying construction is stretched, for installing bearing fixed seat.Small cornual plate is also projected with the watchfully rib machine of root, supporting plate spiral shell is installed on small cornual plate
Mother, shape lid is tieed up for fixed.Other end watchfully rib machine is by traditional arrangement close to the wing end of aileron end, end machine
The bearing that axle-hole tolerance fit installation is realized with aileron rotating shaft is housed on thriving rib.
(2) overhanging load-carrying construction.Overhanging load-carrying construction with root watchfully rib machine web while be connected, with wing topographies
One side and the greasy splicing of covering glue.Between overhanging load-carrying construction and covering plus glue it is greasy be in order to be tightened up in bolt in the case of maintain
Wing cover profile, bearing fixed seat is installed on overhanging load-carrying construction, caused load transmission on the aileron coercive mechanism of root is given
Root watchfully rib machine.
(3) small cornual plate：Small cornual plate is installed plate nut, is used for while be connected with root watchfully rib machine web on another side
Fixed dimension shape lid.
(4) shape lid is tieed up：For dismounting aileron, and the integrality of wing profile is safeguarded, bear local pneumatic load, do not join
With structure entirety stress.
(5) bearing fixed seat：Bearing fixed seat is arranged on overhanging load-carrying construction, with overhanging load-carrying construction, wing cover
Between be connected by screw bolts.Bolt connection realizes the dismantled and assembled of bearing fixed seat, and then realizes the dismantled and assembled of aileron.Bearing
On bearing fixed seat, side seals bearing with cover plate.
(6) bearing：Bearing is fixed on the watchfully rib machine of end, there is the leading to precision coordinated with aileron rotating shaft on bearing
Hole.
Beneficial effects of the present invention：
1st, aileron is dismantled and assembled, can save middle-size and small-size high-speed unmanned aerial vehicle use cost；2nd, aileron coercive mechanism is arranged in wing
Portion, high-speed unmanned aerial vehicle aerofoil aeroperformance is not influenceed；3rd, on the premise of wing structure inner space is limited, close to airfoil root
Bearing is housed, aileron all uses axle-hole tolerance by card ground risk well below both ends aileron coercive mechanism on the aileron coercive mechanism of one end
The mounting structure of cooperation；4 dimension shape lids are not involved in structure entirety stress, and the related wing structure number of parts being related to therewith is most
It is small；5 structural reliabilities are high.
Brief description of the drawings：
Fig. 1 illustrates for wing overall structure.
Fig. 2 is aileron structural representation.
Fig. 3 is the structural representation that end aileron hands over fulcrum to be connected with aileron.
Fig. 4 is that root watchfully rib machine extends the partial structural diagram after yearning for the skew of airfoil root direction.
Fig. 5 is the structural representation of root watchfully rib machine connection.
Fig. 6 is the partial structural diagram that root aileron coercive mechanism is connected with aileron.
Fig. 7 is the structural representation of bearing fixed seat.
Embodiment：
Embodiment 1：
Referring to Fig. 1-Fig. 7, dismantled and assembled aileron mounting structure, including root aileron coercive mechanism and end aileron coercive mechanism, root
Portion's aileron coercive mechanism and end aileron coercive mechanism are used to install fixed aileron 2；End aileron coercive mechanism includes end watchfully rib machine 8
With the bearing 7 being fixed on rib web, there is the through hole with precision on bearing, for installing aileron rotating shaft 6, realize aileron one
The installation for holding axle-hole to coordinate；Root aileron coercive mechanism includes root watchfully rib machine 9, bearing fixed seat 13, bearing, maintenance lid
3rd, overhanging load-carrying construction 11, small cornual plate 10.The root watchfully rib machine 9 is opened up along wing 1 yearns for the skew of the root direction of wing 1
35mm, to reserve the space for dismounting root aileron coercive mechanism.The overhanging load-carrying construction 11 is used to install bearing fixed seat
13, connected between bearing fixed seat 13 and overhanging load-carrying construction 11 and wing cover using bolt 4.Bearing is fixed installed in bearing
On seat 13, the bearing is used to install aileron root rotating shaft 5, realizes the installation of aileron one end axle-bearing fit.It is described small
Cornual plate 10 is provided with plate nut, and for fixed dimension shape lid 3, the other end of dimension shape lid 3, which is fixed on, to be obturaged on plate 12.The bearing
Sealed close to the side of aileron 2 by cover plate 14.
Aileron is installed：
1st, by the precision holes on the end aileron rotating shaft insertion end watchfully rib machine bearing of aileron one end；
2nd, on the bearing that aileron rotating shaft insertion in root is fixed in bearing fixed seat；
3rd, bearing fixed seat is lain on overhanging load-carrying construction, hole alignment, by bearing fixed seat, overhanging load-carrying construction and illiteracy
Skin 2 groups of bolts and tight；
4th, aileron is finely tuned, makes the gap of aileron both ends and wing basically identical, the aperture of root aileron rotating shaft is not open
Pin, vibration of the limitation aileron in spanwise direction；
5th, aileron is checked, it is ensured that aileron rotates freely, and under reset condition, aileron both ends do not allow to produce price scissors；
6th, installation dimension shape lid, screw is inserted respectively to obturaging on plate and small cornual plate in default plate nut hole, is tightened
Screw；
7th, install.
Aileron dismounts：
1st, unscrew the screw in dimension shape lid, take out screw, pull down dimension shape lid；
2nd, looser a bolt, unload lower nut, take out bolt；
3rd, mobile bearing fixed seat, end pair is gently slided from the through hole with precision of the bearing on the watchfully rib machine of end
Wing rotating shaft, take out aileron；
4th, aileron and bearing fixed seat are carried away, twists into two parts the split pin in the aileron rotating shaft of root, from the axle on bearing fixed seat
Root aileron rotating shaft, release bearing fixed seat and aileron are slided in bearing bore；
5th, dismounting finishes.
Claims (3)
1. dismantled and assembled aileron mounting structure, including root aileron coercive mechanism and end aileron coercive mechanism, root aileron coercive mechanism and
End aileron coercive mechanism is used to install fixed aileron；
End aileron coercive mechanism includes end watchfully rib machine and the bearing on rib web；Have on bearing with tolerance
Through hole, aileron rotating shaft are inserted directly into through hole, realize the installation that aileron one end axle-hole coordinates；
Root aileron coercive mechanism includes root watchfully rib machine, bearing fixed seat, bearing, small cornual plate and dimension shape lid；Also include peace
It is used for installation axle with the overhanging load-carrying construction of wing cover topographies, the overhanging load-carrying construction on watchfully rib machine web
Fixed seat is held, is connected by screw bolts between bearing fixed seat and overhanging load-carrying construction and wing cover；The bolt connection side
Bearing fixed seat dismounting, and then realize the dismounting of aileron；Bearing is arranged on bearing fixed seat, aileron rotating shaft insertion axle
In holding；Realize the installation of aileron one end axle-bearing fit.
2. dismantled and assembled aileron mounting structure according to claim 1, it is characterised in that：The root watchfully rib machine is along wing
The skew of airfoil root direction is yearned in exhibition, to reserve the space for dismantled and assembled aileron coercive mechanism.
3. dismantled and assembled aileron mounting structure according to claim 1, it is characterised in that：The small cornual plate is arranged on root machine
On wing rib web, small cornual plate is provided with plate nut, for being fixedly connected with dimension shape lid, is easy to dismount aileron.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710903750.3A CN107697270A (en) | 2017-09-29 | 2017-09-29 | Dismantled and assembled aileron mounting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710903750.3A CN107697270A (en) | 2017-09-29 | 2017-09-29 | Dismantled and assembled aileron mounting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107697270A true CN107697270A (en) | 2018-02-16 |
Family
ID=61174646
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710903750.3A Pending CN107697270A (en) | 2017-09-29 | 2017-09-29 | Dismantled and assembled aileron mounting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107697270A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108609159A (en) * | 2018-05-21 | 2018-10-02 | 顺丰科技有限公司 | Wing, empennage and aircraft |
| CN108791820A (en) * | 2018-05-08 | 2018-11-13 | 兰州空间技术物理研究所 | A kind of flat steering engine mechanism for aileron |
| CN109703744A (en) * | 2019-02-20 | 2019-05-03 | 西安爱生技术集团公司 | A kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism and assembly and disassembly methods |
| WO2020000690A1 (en) * | 2018-06-25 | 2020-01-02 | 深圳市大疆创新科技有限公司 | Fixed-wing unmanned aerial vehicle and empennage thereof |
| CN114750929A (en) * | 2022-04-26 | 2022-07-15 | 北京北航天宇长鹰无人机科技有限公司 | Unmanned aerial vehicle aileron structure and unmanned aerial vehicle |
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| CN202244073U (en) * | 2011-06-07 | 2012-05-30 | 北方电科集团有限公司 | Torque compensation tail wing of airship |
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| CN103057695A (en) * | 2013-01-08 | 2013-04-24 | 西北工业大学 | Combined control surface of tailless airplane |
| BRPI1005020A2 (en) * | 2010-12-23 | 2015-11-10 | Univ Minas Gerais | fixed wing aircraft aileron and wing geometry |
| CN204822056U (en) * | 2015-05-25 | 2015-12-02 | 中国航天空气动力技术研究院 | Combined material aileron structure |
| CN206511107U (en) * | 2017-02-25 | 2017-09-22 | 郑州海王实业有限公司 | Available for wing the device being connected is rotated with aileron |
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2017
- 2017-09-29 CN CN201710903750.3A patent/CN107697270A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BRPI1005020A2 (en) * | 2010-12-23 | 2015-11-10 | Univ Minas Gerais | fixed wing aircraft aileron and wing geometry |
| CN202244073U (en) * | 2011-06-07 | 2012-05-30 | 北方电科集团有限公司 | Torque compensation tail wing of airship |
| CN102901595A (en) * | 2012-10-12 | 2013-01-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for measuring hinge moment of control surface |
| CN103057695A (en) * | 2013-01-08 | 2013-04-24 | 西北工业大学 | Combined control surface of tailless airplane |
| CN204822056U (en) * | 2015-05-25 | 2015-12-02 | 中国航天空气动力技术研究院 | Combined material aileron structure |
| CN206511107U (en) * | 2017-02-25 | 2017-09-22 | 郑州海王实业有限公司 | Available for wing the device being connected is rotated with aileron |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791820A (en) * | 2018-05-08 | 2018-11-13 | 兰州空间技术物理研究所 | A kind of flat steering engine mechanism for aileron |
| CN108609159A (en) * | 2018-05-21 | 2018-10-02 | 顺丰科技有限公司 | Wing, empennage and aircraft |
| WO2020000690A1 (en) * | 2018-06-25 | 2020-01-02 | 深圳市大疆创新科技有限公司 | Fixed-wing unmanned aerial vehicle and empennage thereof |
| CN109703744A (en) * | 2019-02-20 | 2019-05-03 | 西安爱生技术集团公司 | A kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism and assembly and disassembly methods |
| CN114750929A (en) * | 2022-04-26 | 2022-07-15 | 北京北航天宇长鹰无人机科技有限公司 | Unmanned aerial vehicle aileron structure and unmanned aerial vehicle |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180216 |