CN109606627A - A kind of aviation aircraft winglet attachment device - Google Patents
A kind of aviation aircraft winglet attachment device Download PDFInfo
- Publication number
- CN109606627A CN109606627A CN201811504371.8A CN201811504371A CN109606627A CN 109606627 A CN109606627 A CN 109606627A CN 201811504371 A CN201811504371 A CN 201811504371A CN 109606627 A CN109606627 A CN 109606627A
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- CN
- China
- Prior art keywords
- abaculus
- wingtip
- groove
- connecting rod
- attachment device
- 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
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/52—Warping
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of aviation aircraft winglet attachment devices comprising wingtip support and wingtip connection unit, wingtip connection unit include abaculus, connecting rod and holddown spring；Wingtip support is semicylinder, wingtip support is fixed on wing tip by the lateral plane of semicylinder side, it is provided on the cylindrical surface of the semicylinder other side multiple for installing wingtip connection unit groove, a side wall surface in groove is equipped with the abaculus groove of a non-circular shape, and blind hole is equipped in another side wall surface；Abaculus is able to cooperate deck in abaculus groove, and a circle circumferentially equally distributed multiple indexing jacks are offered on the outer end face of abaculus；For connecting with winglet, a side of the other end is plane for one end of connecting rod, is provided with bolt on another side；One end of holddown spring is landed in blind hole, and the other end is withstood in the plane of the side of connecting rod.Occupied space of the present invention is smaller, light-weight, and angle adjustable is more.
Description
Technical field
The present invention relates to a kind of winglet attachment devices, belong to aviation aircraft design field.
Background technique
Winglet is used for subsonic aircraft, mainly includes airline carriers of passengers, military transportation airplane, tanker aircraft, early warning plane
And unmanned plane.In the subsonic aircraft of the world today, partially it is provided with winglet and is opened up with improving wing to air-flow flowing, subtracted
Small wing induced drag reduces fuel consumption, improves economic performance.
But not every subsonic aircraft all uses winglet.It is cost problem first, installs winglet additional and increase
Cost is designed and manufactured, passenger plane, which installs winglet additional, will expend hundreds of thousands of dollars.Secondly, aircraft execute task be it is various,
And winglet only could utmostly exert advantages of oneself during cruise, that is to say, that only in long-distance flight
The oil-saving effect of winglet is best；Again, winglet is located at wing both ends, is very easy to damage because of collision, reliably
Property it is not high, and due to being difficult to dismantle, the maintenance after damaging is also more troublesome, maintainable poor.Therefore, subsonic aircraft exists
It needs to comprehensively consider when design and decides whether that winglet is arranged.
So the diversity for how accomplishing that winglet is easy to remove and repair and adapts to task is a key point.If this
The application that a little problems are able to solve so winglet will be more extensive.
Application No. is a kind of 201310692469.1 Chinese invention patent " winglet dresses of detachable adjustable inclination angle
Set " a kind of winglet device is disclosed, the adjustable of winglet angle is realized using intubation and slot, is passed through and is inserted using metal bitch chain
Winglet is fixed in pipe.But the device angle adjustable is few, occupied space is larger, and metal bitch chain can move in the sky, is easy
Disconnection falls off, and influences flight safety.
Summary of the invention
The technical problem to be solved by the present invention is having overcome the deficiencies of the prior art and provide, a kind of angle adjustable is more, occupies
Space is small, high reliablity aviation aircraft winglet device.
Aviation aircraft winglet device of the present invention includes wingtip support and wingtip connection unit, described
Wingtip connection unit includes abaculus, connecting rod and holddown spring；The wingtip support be semicylinder, the wingtip support by
The lateral plane of semicylinder side is fixed on wing tip, is provided on the cylindrical surface of the semicylinder other side multiple for pacifying
The wingtip connection unit groove is filled, a side wall surface in the groove is equipped with the abaculus groove of a non-circular shape,
In another side wall surface, the blind hole as spring base is offered in the position opposite with the abaculus groove；The abaculus is energy
Cooperate shape of the deck in the abaculus groove, it is circumferentially equally distributed more to offer a circle on the outer end face of the abaculus
A indexing jack；For connecting with winglet, a side of the other end is plane for one end of the connecting rod, another
A circle is provided on side can cooperate the bolt for being inserted into the indexing jack；One end of the holddown spring is landed in blind hole
Interior, the other end is withstood in the plane of the side of connecting rod, to axial compression connecting rod.
It is preferred that the quantity of the indexing jack is more than or equal to 16.
It is preferred that it is in semi-conical that one end of the wingtip support, which is shunk,.
It is preferred that the abaculus groove and abaculus are interference fitted.
It is preferred that the indexing jack and bolt are clearance fit.
It is preferred that the abaculus groove is the square groove shape that side is rounded down.
It is preferred that the abaculus groove is two, it is symmetrically distributed in the both ends of the wingtip support.
It is preferred that the abaculus is provided centrally with loss of weight through-hole.
The advantages of the present invention over the prior art are that:
1) angle that the present invention is socket-connected by changing the bolt on the indexing jack and connecting rod on abaculus, keeps wingtip small
The tilt adjustable of the wing.The optimal inclination angle of winglet can be determined by the flight test under different angle；And the socket structure occupies sky
Between it is smaller, weight is lighter, can be realized step-less adjustment angle, i.e. the smaller interval of angle, angle adjustable is more；
2) present invention is connect using connecting rod with winglet, and connecting rod occupies volume more in the groove of wingtip support
Small, weight is lighter, and this point is quite important for aeronautic structure；Secondly because small in size, air drag is smaller；
3) present invention is moved forward and backward using holddown spring limitation winglet, and holddown spring pressing force is big, is not easy to disengage, can
By property height；Holddown spring does not tend to have gap between connecting rod, and limitation capability is stronger；
4) in the present invention, winglet and wing are not integrated, and part is few, convenient disassembly, therefore when winglet damages
When, can directly, rapidly replace winglet, replace and safeguard and is more convenient；
5) in the present invention, wingtip support is airflow design, and air drag is small.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of apparatus of the present invention；
Fig. 2 is the first axonometric drawing of wingtip support of the present invention；
Fig. 3 is the second axonometric drawing of wingtip support of the present invention；
Fig. 4 is the schematic diagram of abaculus of the present invention；
Fig. 5 is the schematic diagram of connecting rod of the present invention；
Fig. 6 is the schematic diagram of holddown spring of the present invention；
Fig. 7 is groove part partial schematic diagram of the present invention.
Specific embodiment
As shown in Figure 1 and Figure 7, the present invention provides a kind of aviation aircraft winglet attachment devices, comprising: wingtip branch
Seat 1, abaculus 2, connecting rod 3 and holddown spring 4.
As shown in Figures 2 and 3, wingtip support 1 is connect with wing wingtip, is semicylinder, and one end of semicylinder is shunk
In semi-conical, to reduce air drag；Groove there are two opening on semicylinder cylindrical surface, the both ends of each groove have
The abaculus groove and a blind hole of one non-circular shape, abaculus groove is the square hole shape that side is rounded down in the present embodiment.
As shown in figure 4, the shape of abaculus 2 is consistent with the shape of abaculus groove, card is sitting in abaculus groove, and is interference fitted with it.It is embedding
There is a through-hole at the center of block 2, and the purpose that through-hole is arranged is in order to reduce the weight；There is a circle equal along through-hole on one side of abaculus 2
The indexing jack of even distribution, the quantity for indexing jack should be 16 or more, to give full play to the effect for adjusting angle.This implementation
Indexing jack is shrinkage pool in example, and the shape of each indexing jack is consistent, is collectively constituted along the centrosymmetric figure of the circle center；
As shown in figure 5, connecting rod 3 is equipped with circular hole, in addition setting circular hole can also reduce the face of machined surface with loss of weight
Product；One end face of connecting rod 3 is equipped with a circle circumferentially equally distributed bolt and inserts corresponding to the indexing jack on abaculus 2
Pin injects in indexing jack, is between the two clearance fit, connecting rod 3 is connect with winglet.
The design for indexing jack and bolt, first is that two are that by stepless angle adjusting, i.e., in order to limit the rotation of connecting rod 3
Lesser angular adjustment interval.When installation, the angle to be socket-connected by changing indexing jack and bolt changes and connects with connecting rod 3
The tilt angle of the winglet connect.The tilt adjustable of winglet can determine winglet by the flight test under different angle
Optimal inclination angle.
It is illustrated in figure 6 holddown spring 4, in blind hole, the other end withstands on the another of connecting rod 3 for one end of holddown spring 4
On one end face, axial compression connecting rod 3, effect is to limit the axial movement of connecting rod 3.
Acceleration in view of aircraft along own axes direction is generally less than acceleration of gravity, is total to there are two holddown spring,
Consider safe clearance simultaneously, the size of the pressing force of holddown spring 4 should be at least winglet quality multiplied by an acceleration of gravity,
That is F >=mg.
The installation and application of the invention described device is as follows:
First by abaculus 2 in the abaculus groove of wingtip support 1 when use, holddown spring 4 is then mounted on wingtip
In the circular hole of support 1, then by spring compression, connecting rod 3 is inserted into abaculus 2, trip spring, it is made to compress connecting rod 3.
The incident angle for adjusting connecting rod 3 determines that the optimal of winglet inclines by the flight test under different angle
Angle.
More specific description is carried out to the present invention below by several examples:
Example one adjusts winglet inclination angle to be optimal pneumatic effect
The adjustable winglet inclination angle of winglet device of the present invention is tried by the flight under different angle
It tests, test data result is analyzed, determine the optimal inclination angle of winglet, to obtain optimal pneumatic effect.
Example two quickly and easily replaces impaired winglet
Winglet device of the present invention maintenance convenient to use.If aircraft winglet damages, do not have to as now
Winglet go to repair like that, but can disassemble and be replaced immediately, save the maintenance times of a large amount of preciousnesses.Together
When impaired winglet can be taken back maintenance area and repair processing, thrown away without discarded, save great amount of cost.
The description that is carried out of the present invention is only illustrated rather than in described above and explanation limited, and not departed from
Under the premise of the present invention as defined by the appended claims, can to above-described embodiment carry out various changes, deformation and/
Or amendment.
Unspecified part of the present invention belongs to the well-known technique of those skilled in the art.
Claims (8)
1. a kind of aviation aircraft winglet attachment device, which is characterized in that including wingtip support and wingtip connection unit,
The wingtip connection unit includes abaculus, connecting rod and holddown spring；
The wingtip support is semicylinder, and the wingtip support is fixed on wing end by the lateral plane of semicylinder side
On the tip, it is provided on the cylindrical surface of the semicylinder other side multiple for installing the groove of the wingtip connection unit, the groove
An interior side wall surface be equipped with a non-circular shape abaculus groove, in another side wall surface, with the abaculus groove
Opposite position offers the blind hole as spring base；The abaculus is the shape for being able to cooperate deck in the abaculus groove,
A circle circumferentially equally distributed multiple indexing jacks are offered on the outer end face of the abaculus；One end of the connecting rod is used for
It is connect with winglet, a side of the other end is plane, and a circle is provided on another side can cooperate insertion institute
State the bolt of indexing jack；One end of the holddown spring is landed in blind hole, and the other end withstands on the plane of the side of connecting rod
On, to axial compression connecting rod.
2. a kind of aviation aircraft winglet attachment device as described in claim 1, it is characterised in that: the indexing jack
Quantity be more than or equal to 16.
3. a kind of aviation aircraft winglet attachment device as claimed in claim 1 or 2, it is characterised in that: the wingtip
It is in semi-conical that one end of support, which is shunk,.
4. a kind of aviation aircraft winglet attachment device as claimed in claim 1 or 2, it is characterised in that: the abaculus
Groove and abaculus are interference fitted.
5. a kind of aviation aircraft winglet attachment device as claimed in claim 1 or 2, it is characterised in that: the indexing
Jack and bolt are clearance fit.
6. a kind of aviation aircraft winglet attachment device as claimed in claim 1 or 2, it is characterised in that: the abaculus
Groove is the square groove shape that side is rounded down.
7. a kind of aviation aircraft winglet attachment device as claimed in claim 1 or 2, it is characterised in that: the abaculus
Groove is two, is symmetrically distributed in the both ends of the wingtip support.
8. a kind of aviation aircraft winglet attachment device as claimed in claim 1 or 2, it is characterised in that: the abaculus
Be provided centrally with loss of weight through-hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811504371.8A CN109606627A (en) | 2018-12-10 | 2018-12-10 | A kind of aviation aircraft winglet attachment device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811504371.8A CN109606627A (en) | 2018-12-10 | 2018-12-10 | A kind of aviation aircraft winglet attachment device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109606627A true CN109606627A (en) | 2019-04-12 |
Family
ID=66007570
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811504371.8A Pending CN109606627A (en) | 2018-12-10 | 2018-12-10 | A kind of aviation aircraft winglet attachment device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109606627A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102407938A (en) * | 2011-10-19 | 2012-04-11 | 南京航空航天大学 | Wing installed with variant wingtip winglet and working mode thereof |
| CN103625634A (en) * | 2013-12-17 | 2014-03-12 | 中国航天空气动力技术研究院 | Detachable wingtip winglet device with adjustable dip angles |
| CN105366031A (en) * | 2015-12-04 | 2016-03-02 | 中国航天空气动力技术研究院 | Winglet device with adjustable angle |
| CN105438441A (en) * | 2015-12-04 | 2016-03-30 | 中国航天空气动力技术研究院 | Winglet device |
-
2018
- 2018-12-10 CN CN201811504371.8A patent/CN109606627A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102407938A (en) * | 2011-10-19 | 2012-04-11 | 南京航空航天大学 | Wing installed with variant wingtip winglet and working mode thereof |
| CN103625634A (en) * | 2013-12-17 | 2014-03-12 | 中国航天空气动力技术研究院 | Detachable wingtip winglet device with adjustable dip angles |
| CN105366031A (en) * | 2015-12-04 | 2016-03-02 | 中国航天空气动力技术研究院 | Winglet device with adjustable angle |
| CN105438441A (en) * | 2015-12-04 | 2016-03-30 | 中国航天空气动力技术研究院 | Winglet device |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190412 |
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| WD01 | Invention patent application deemed withdrawn after publication |