CN105366031A - Winglet device with adjustable angle - Google Patents
Winglet device with adjustable angle Download PDFInfo
- Publication number
- CN105366031A CN105366031A CN201510884027.6A CN201510884027A CN105366031A CN 105366031 A CN105366031 A CN 105366031A CN 201510884027 A CN201510884027 A CN 201510884027A CN 105366031 A CN105366031 A CN 105366031A
- Authority
- CN
- China
- Prior art keywords
- winglet
- abaculus
- wingtip
- groove
- pipe link
- 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
Links
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
- B64C3/44—Varying camber
- B64C3/50—Varying camber by leading or trailing edge flaps
Abstract
A winglet device with adjustable angle includes a wingtip holder (1), insert blocks (2), connecting rods (3) and compression springs (4). The wingtip holder (1) is connected with the wingtip; one side of the wingtip holder (1) is provided with two or more grooves; both ends of each groove are respectively provided an insert block groove in a non-rotating shape and a blind hole; the shape of the insert blocks (2) is consistent with the shape of the insert block grooves, and the insert blocks are inserted into the insert block grooves; the outer end face of each insert block (2) is provided with a ring of adjustment grooves circumferentially arranged, and each adjustment groove forms a centrosymmetric figure along the center of the circumference; one end of each connecting rod (3) is provided with a ring of projections matching with the adjustment grooves, the projections are in the adjustment grooves, and the connecting rods (3) are connected with the winglet; and one end of each compression spring (4) is arranged in the blind hole, and the other end of each compression spring abuts against the other end face of the connecting rod (3) and is axially compresses the connecting rod (3). The winglet device has the advantages of small space occupation, light weight, and the many adjustable angles.
Description
Technical field
The present invention relates to a kind of winglet device, belong to aviation aircraft design field.
Background technology
Winglet is used for subsonic aircraft, mainly comprises airline carriers of passengers, military transportation airplane, tanker aircraft, early warning plane and unmanned plane.In the subsonic aircraft of the world today, part is provided with winglet to improve wing exhibition to air current flow, reduces wing induced drag, reduces fuel oil consumption, improve economic performance.
But not every subsonic aircraft all adopts winglet.First be Cost Problems, install winglet additional and add Design and manufacture cost, passenger plane installs winglet additional will expend hundreds of thousands of dollars.Secondly, it is various that aircraft is executed the task, and winglet only could at utmost exert advantages of oneself in the process of cruising, and that is only when long-distance flight, the oil-saving effect of winglet is best; Again, winglet is positioned at wing two ends, is very easy to damage because of collision, and reliability is not high, and owing to being difficult to dismounting, the maintenance after damage is also cumbersome, maintainable poor.Therefore, subsonic aircraft needs to consider decision whether arrange winglet when designing.
So how to accomplish that winglet is easy to remove and repair and the variety that adapts to task is a key point.If the application that these problems can solve so winglet will be more extensive.
Patent " a kind of winglet device of detachable adjustable inclination angle " (application number: 201310692469.1) disclose a kind of winglet device, utilize intubate and slot to realize the adjustable of winglet angle, utilize metal bitch chain to be fixed winglet through intubate.But this device angle adjustable is few, take up room comparatively large, metal bitch chain can aloft move, and easily disconnects and coming off, affect flight safety.
Summary of the invention
The technical problem to be solved in the present invention is: overcome prior art deficiency, provides that a kind of angle adjustable is many, take up room the winglet device little, reliability is high.
The technical solution adopted in the present invention is:
A winglet device for tilt adjustable, comprising: wingtip bearing, abaculus, pipe link and holddown spring;
Wingtip bearing is connected with wing wingtip, is semicylinder, and one end of semicylinder is shunk in semi-conical; The semicylinder face of cylinder has two and with upper groove, the end face that two of each groove are relative is respectively equipped with abaculus groove and a blind hole of a non-revolved body shape; The profile of abaculus is consistent with the shape of abaculus groove, is enclosed within abaculus groove, the outer face of abaculus has the circumferential adjusting grooves of a circle, and each adjusting grooves forms along the centrosymmetric figure of this circle center jointly; One end of pipe link is provided with the projection that a circle matches with adjusting grooves, and projection is enclosed within adjusting grooves, and pipe link is connected with winglet; One end of holddown spring is contained in blind hole, and the other end withstands on another end face of pipe link, axial compression pipe link.
The quantity of described abaculus groove be 16 and more than.
Described abaculus groove and abaculus interference fit.
Described adjusting grooves and projection are free-running fit.
Described abaculus groove is the rectangular shape that side is rounded down.
The present invention's advantage is compared with prior art:
1) angle that socket-connects by changing the adjusting grooves on abaculus and the projection on pipe link of the present invention, makes the tilt adjustable of winglet.By the flight test under different angle, determine the optimum inclination angle of winglet; And this socket join structure takes up room less, weight is lighter, and can realize step-less adjustment angle, namely the interval of angle is less, and angle adjustable is more;
2) the present invention utilizes pipe link to be connected with winglet, and pipe link, in the groove of wingtip bearing, takies volume less, and weight is lighter, and this point is for quite important aeronautic structure; Secondly because volume is little, air resistance is less;
3) what the present invention adopted is that holddown spring restriction winglet moves forward and backward, and holddown spring thrust is large, and not easily throw off, reliability is high; Holddown spring and not easily have gap between pipe link, limitation capability is stronger;
4), in the present invention, winglet and wing are not one, and part is few, convenient disassembly, therefore when winglet damages, directly, rapidly can change winglet, changes and safeguards convenient;
5), in the present invention, wingtip bearing is airflow design, and air resistance is little.
Accompanying drawing explanation
Fig. 1 is the structural representation of apparatus of the present invention;
Fig. 2 is the first axonometric drawing of wingtip bearing of the present invention;
Fig. 3 is the second axonometric drawing of wingtip bearing of the present invention;
Fig. 4 is the schematic diagram of abaculus of the present invention;
Fig. 5 is the schematic diagram of pipe link 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.
Detailed description of the invention
As shown in Figure 1 and Figure 7, the invention provides a kind of winglet device of tilt adjustable, comprising: wingtip bearing 1, abaculus 2, pipe link 3 and holddown spring 4.
As shown in Figures 2 and 3, wingtip bearing 1 is connected with wing wingtip, is semicylinder, and one end of semicylinder is shunk in semi-conical, to reduce air resistance; The semicylinder face of cylinder has two grooves, the two ends of each groove have abaculus groove and a blind hole of a non-revolved body shape, and in the present embodiment, abaculus groove is the rectangular shape that side is rounded down.As shown in Figure 4, the profile of abaculus 2 is consistent with the shape of abaculus groove, is enclosed within abaculus groove, and with its interference fit.There is a through hole at the center of abaculus 2, and the object arranging through hole is in order to loss of weight; There is a circle side of abaculus 2 along through hole well-distributed adjusting grooves, the quantity of adjusting grooves should be 16 and more than, to give full play to the effect of adjusting angle.In the present embodiment, adjusting grooves is shrinkage pool, and the shape of each adjusting grooves is consistent, jointly forms along the centrosymmetric figure of this circle center;
As shown in Figure 5, pipe link 3 is provided with circular hole, and arranging circular hole can loss of weight, also reduces the area of finished surface in addition; An end face of pipe link 3 is provided with one and encloses circumferentially well-distributed projection, and corresponding to the adjusting grooves on abaculus 2, projection is enclosed within adjusting grooves, and be free-running fit between the two, pipe link 3 is connected with winglet.
The design of adjusting grooves and projection, one is the rotation in order to limit pipe link 3, and two is to realize stepless angle adjusting, namely less angular adjustment interval.During installation, the angle socket-connected by change adjusting grooves and projection, changes the angle of inclination of the winglet be connected with pipe link 3.The tilt adjustable of winglet, by the flight test under different angle, determines the optimum inclination angle of winglet.
Be illustrated in figure 6 holddown spring 4, one end of holddown spring 4 is contained in blind hole, and the other end withstands on another end face of pipe link 3, axial compression pipe link 3, and its effect is the axial motion of restriction pipe link 3.
Consider that aircraft is generally less than acceleration due to gravity along the acceleration/accel in own axes direction, have two holddown springs, consider safe clearance simultaneously, the size of the thrust of holddown spring 4 should be at least winglet quality and be multiplied by acceleration due to gravity, i.e. a F >=mg.
The installation and application of the described device of this invention is as follows:
First abaculus 2 is contained in the abaculus groove of wingtip bearing 1 during use, then holddown spring 4 is arranged in the circular hole of wingtip bearing 1, then by spring application, pipe link 3 is inserted in abaculus 2, trip spring, make it compress pipe link 3.
Regulate the incident angle of pipe link 3, by the flight test under different angle, determine the optimum inclination angle of winglet.
Below by several example, more specific description is carried out to the present invention:
Example one, adjustment winglet inclination angle is to reach optimum pneumatic effect
Winglet device of the present invention can regulate winglet inclination angle, by the flight test under different angle, analyzes test figures result, determines the optimum inclination angle of winglet, to obtain optimum pneumatic effect.
Example two, changes impaired winglet quickly and easily
Winglet device of the present invention maintenance easy to use.If aircraft winglet damages, maintenance need not be gone as present winglet, but can disassemble immediately and change, save a large amount of valuable maintenance time.Simultaneously impaired winglet can be taken back maintenance area and carry out maintenance process, and need not discard and throw away, save great amount of cost.
Just to illustrate but not determinate in the above description described and carry out the present invention in illustrating, and do not depart from as appended claims under the prerequisite of the present invention that limits, can various change, distortion be carried out to above-described embodiment and/or revise.
The unspecified part of the present invention belongs to technology as well known to those skilled in the art.
Claims (6)
1. a winglet device for tilt adjustable, is characterized in that, comprising: wingtip bearing (1), abaculus (2), pipe link (3) and holddown spring (4);
Wingtip bearing (1) is connected with wing wingtip, and a side of wingtip bearing (1) has two and with upper groove, and the end face that two of each groove are relative is respectively equipped with abaculus groove and a blind hole of a non-revolved body shape; The profile of abaculus (2) is consistent with the shape of abaculus groove, is enclosed within abaculus groove, the outer face of abaculus (2) has the circumferential adjusting grooves of a circle, and each adjusting grooves forms along the centrosymmetric figure of this circle center jointly; One end of pipe link (3) is provided with the projection that a circle matches with adjusting grooves, and projection is enclosed within adjusting grooves, and pipe link (3) is connected with winglet; One end of holddown spring (4) is contained in blind hole, and the other end withstands on another end face of pipe link (3), axial compression pipe link (3).
2. a winglet device for tilt adjustable as claimed in claim 1, is characterized in that, the quantity of described abaculus groove be 16 and more than.
3. a winglet device for tilt adjustable as claimed in claim 1 or 2, is characterized in that, described wingtip bearing (1) is semicylinder, and one end of semicylinder is shunk in semi-conical.
4. a winglet device for tilt adjustable as claimed in claim 1 or 2, is characterized in that, described abaculus groove and abaculus (2) interference fit.
5. a winglet device for tilt adjustable as claimed in claim 1 or 2, is characterized in that, described adjusting grooves and projection are free-running fit.
6. a winglet device for tilt adjustable as claimed in claim 1 or 2, is characterized in that, described abaculus groove is the rectangular shape that side is rounded down.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510884027.6A CN105366031A (en) | 2015-12-04 | 2015-12-04 | Winglet device with adjustable angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510884027.6A CN105366031A (en) | 2015-12-04 | 2015-12-04 | Winglet device with adjustable angle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105366031A true CN105366031A (en) | 2016-03-02 |
Family
ID=55368779
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510884027.6A Pending CN105366031A (en) | 2015-12-04 | 2015-12-04 | Winglet device with adjustable angle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105366031A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606627A (en) * | 2018-12-10 | 2019-04-12 | 彩虹无人机科技有限公司 | A kind of aviation aircraft winglet attachment device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080308683A1 (en) * | 2007-06-15 | 2008-12-18 | The Boeing Company | Controllable winglets |
| CN201224495Y (en) * | 2008-06-24 | 2009-04-22 | 北京航空航天大学 | Wing tip winglet of 150-seat trunkliner |
| US20120091262A1 (en) * | 2010-10-15 | 2012-04-19 | The Boeing Company | Forward swept winglet |
| CN202600555U (en) * | 2012-06-11 | 2012-12-12 | 常熟英那金属制品有限公司 | Rotary limit device |
| 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 |
-
2015
- 2015-12-04 CN CN201510884027.6A patent/CN105366031A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080308683A1 (en) * | 2007-06-15 | 2008-12-18 | The Boeing Company | Controllable winglets |
| CN201224495Y (en) * | 2008-06-24 | 2009-04-22 | 北京航空航天大学 | Wing tip winglet of 150-seat trunkliner |
| US20120091262A1 (en) * | 2010-10-15 | 2012-04-19 | The Boeing Company | Forward swept winglet |
| CN202600555U (en) * | 2012-06-11 | 2012-12-12 | 常熟英那金属制品有限公司 | Rotary limit device |
| 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 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606627A (en) * | 2018-12-10 | 2019-04-12 | 彩虹无人机科技有限公司 | A kind of aviation aircraft winglet attachment device |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160302 |