CN106240802A - A kind of wing aerodynamic deceleration mechanism - Google Patents
A kind of wing aerodynamic deceleration mechanism Download PDFInfo
- Publication number
- CN106240802A CN106240802A CN201610589041.8A CN201610589041A CN106240802A CN 106240802 A CN106240802 A CN 106240802A CN 201610589041 A CN201610589041 A CN 201610589041A CN 106240802 A CN106240802 A CN 106240802A
- Authority
- CN
- China
- Prior art keywords
- flap
- fixed block
- wing
- pull bar
- screw mandrel
- 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
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/32—Air braking surfaces
- B64C9/323—Air braking surfaces associated with wings
Abstract
The invention provides a kind of wing aerodynamic deceleration mechanism, including wing, flap and controller, described flap is arranged at inside wing, the described upper surface of the airfoil position corresponding with flap upper surface is provided with opening, described opening is provided with portable plate, and described portable plate bottom is fixing with flap upper surface to be connected；The correspondence position of both sides, described flap bottom is respectively equipped with the first fixed block and the second fixed block, the first pull bar and the second pull bar is linked respectively on described first fixed block and the second fixed block, the other end of described first pull bar and the second pull bar links with the first slide block and the second slide block respectively, described first slide block and the second slide block are threadedly connected on the first screw mandrel and the second screw mandrel respectively, and described first screw mandrel and the second screw mandrel are connected with the output shaft of the first lead screw motor and the output shaft of the second lead screw motor respectively.Present configuration is simple, working stability, it is possible to quickly open flap when aircraft, meets and uses requirement.
Description
Technical field
The invention belongs to vehicle technology field, particularly relate to a kind of wing aerodynamic deceleration mechanism.
Background technology
At present, every country is all developing new landing mode, and deceleration is exactly one of important topic therein, aircraft landing
Time, in order to accelerate slowing effect, baffle plate can be increased on wing, opening baffle plate when of landing increases windage, and raising subtracts
Effect, but current baffle plate Unclosing structure is complicated, and production cost is high.
Summary of the invention
It is an object of the invention to for the above-mentioned problems in the prior art, it is provided that a kind of simple in construction, working stability,
And can quickly open the wing aerodynamic deceleration mechanism of flap.
The technical solution adopted for the present invention to solve the technical problems is:
A kind of wing aerodynamic deceleration mechanism, including wing, flap and controller, described flap is vertically
Being arranged at inside wing, the described upper surface of the airfoil position corresponding with flap upper surface is provided with opening, on described opening
Being provided with and the portable plate of opening close fit, described portable plate bottom is fixing with flap upper surface to be connected；
The correspondence position of both sides, described flap bottom has been respectively fixedly connected with the first fixed block and the second fixed block, described
On first fixed block and the second fixed block, hinge joint has the first pull bar and the second pull bar, described first pull bar and the second pull bar respectively
The other end links with the first slide block and the second slide block respectively, and described first slide block and the second slide block are threadedly connected to level respectively and set
On the first screw mandrel put and the second screw mandrel, one end of described first screw mandrel is connected with the output shaft of the first lead screw motor, and described
One end of two screw mandrels is connected with the output shaft of the second lead screw motor；
Described first lead screw motor and the second lead screw motor are electrically connected with the controller respectively.
Further, described first fixed block and the second fixed block have two groups, and the first fixed block described in two groups and second is admittedly
Determine block to be uniformly arranged along the length direction of flap.
Further, described first screw rod bushing is located on support, and described support has two, and two described supports lay respectively at
The two ends of the first screw mandrel.
Further, described second screw rod bushing is located on support, and described support has two, and two described supports lay respectively at
The two ends of the second screw mandrel.
Further, described first lead screw motor and the second lead screw motor are respectively by fixing seat and wing bottom inner surface
Fixing connection.
Compared with prior art, the beneficial effect comprise that:
(1), after opening the first lead screw motor and the second lead screw motor, the first slide block and the second slide block are respectively along the first screw mandrel
With moving to flap direction of the second screw mandrel, drive the first pull bar and the second pull bar to be risen by flap, make aircraft land
Time, it is possible to quickly open flap, make the landing speed of aircraft be unlikely to too fast.
(2) during aircraft flight, flap is positioned over inside wing, and upper surface of the airfoil is streamlined, does not affect flying of aircraft
Row state.
Accompanying drawing explanation
The present invention is further described below in conjunction with the accompanying drawings:
Fig. 1 is the overall structure schematic diagram of the present invention；
Fig. 2 is the top view of Fig. 1.
Wherein: 1. wing, 2. flap, 3. portable plate, 4. the first fixed block, 5. the second fixed block, 6. the first pull bar, 7.
Second pull bar, 8. the first slide block, 9. the second slide block, 10. the first screw mandrel, 11. second screw mandrels, 12. first lead screw motor, 13.
Two lead screw motor, 14. supports, 15. fix seat.
Detailed description of the invention
Below in conjunction with embodiment, the present invention will be further described:
As shown in Figure 1-2, the wing aerodynamic deceleration mechanism that the present invention provides, including wing 1, flap 2 with control
Device, it is internal that described flap 2 is vertically arranged at wing 1, and described wing 1 upper surface is corresponding with flap 2 upper surface
Position be provided with opening, described opening is provided with the portable plate 3 with opening close fit, described portable plate 3 bottom and deceleration
Plate 2 upper surface is fixing to be connected；
The correspondence position of both sides, described flap 2 bottom has been respectively fixedly connected with the first fixed block 4 and the second fixed block 5,
On described first fixed block 4 and the second fixed block 5, hinge joint has the first pull bar 6 and the second pull bar 7, described first pull bar 6 He respectively
The other end of the second pull bar 7 links with the first slide block 8 and the second slide block 9 respectively, and described first slide block 8 and the second slide block 9 are respectively
It is threadedly connected on horizontally disposed first screw mandrel 10 and the second screw mandrel 11, one end of described first screw mandrel 10 and the first screw mandrel electricity
The output shaft of machine 12 connects, and one end of described second screw mandrel 11 is connected with the output shaft of the second lead screw motor 13；
Described first lead screw motor 12 and the second lead screw motor 13 are electrically connected with the controller respectively.
Described first fixed block 4 and the second fixed block 5 have two groups, the first fixed block 4 and the second fixed block 5 edge described in two groups
The length direction of flap 2 is uniformly arranged.
Described first screw mandrel 10 is sheathed on support 14, and described support 14 has two, and two described supports 14 lay respectively at
The two ends of the first screw mandrel 10.
Described second screw mandrel 11 is sheathed on support 14, and described support 14 has two, and two described supports 14 lay respectively at
The two ends of the second screw mandrel 11.
Described first lead screw motor 12 and the second lead screw motor 13 are solid with wing 1 bottom inner surface by fixing seat 15 respectively
Fixed connection.
The work process of the present invention:
The wing aerodynamic deceleration mechanism of the present invention in use, the when of needing to rise flap 2, controls first
Lead screw motor 12 and the second lead screw motor 13 start, and make the first slide block 8 and the second slide block 9 respectively along the first screw mandrel 10 and second
Bar 11 moves to flap 2 direction, and the first pull bar 6 and the second pull bar 7 will subtract under the effect of the first slide block 8 and the second slide block 9
Speed plate 2 rises, the first pull bar 6, flap 2 and the first screw mandrel 10 and the second pull bar 7, between flap 2 and the second screw mandrel 11 point
Do not form triangle, improve the stability of flap 2.
Present configuration is simple, working stability, it is possible to quickly open flap when aircraft, meets and uses requirement.
Above by embodiment, the present invention is described in detail, but described content has been only the preferable enforcement of the present invention
Example, it is impossible to be considered the practical range for limiting the present invention.All impartial changes made according to the present patent application scope and improvement
Deng, within all should still belonging to the patent covering scope of the present invention.
Claims (5)
1. a wing aerodynamic deceleration mechanism, it is characterised in that:
Including wing, flap and controller, described flap is vertically arranged at inside wing, described upper surface of the airfoil
The position corresponding with flap upper surface is provided with opening, and described opening is provided with and the portable plate of opening close fit, institute
State that portable plate bottom and flap upper surface are fixing to be connected；
The correspondence position of both sides, described flap bottom has been respectively fixedly connected with the first fixed block and the second fixed block, and described first
On fixed block and the second fixed block, hinge joint has the first pull bar and the second pull bar respectively, another of described first pull bar and the second pull bar
End links with the first slide block and the second slide block respectively, and described first slide block and the second slide block are threadedly connected to horizontally disposed respectively
On first screw mandrel and the second screw mandrel, one end of described first screw mandrel is connected with the output shaft of the first lead screw motor, described second
One end of bar is connected with the output shaft of the second lead screw motor；
Described first lead screw motor and the second lead screw motor are electrically connected with the controller respectively.
Wing the most according to claim 1 aerodynamic deceleration mechanism, it is characterised in that: described first fixed block and second
Fixed block has two groups, and the first fixed block described in two groups and the second fixed block are uniformly arranged along the length direction of flap.
Wing the most according to claim 1 aerodynamic deceleration mechanism, it is characterised in that: described first screw rod bushing is located at
On frame, described support has two, and two described supports lay respectively at the two ends of the first screw mandrel.
Wing the most according to claim 1 aerodynamic deceleration mechanism, it is characterised in that: described second screw rod bushing is located at
On frame, described support has two, and two described supports lay respectively at the two ends of the second screw mandrel.
Wing the most according to claim 1 aerodynamic deceleration mechanism, it is characterised in that: described first lead screw motor and
Two lead screw motor are connected by fixing seat and wing bottom inner surface are fixing respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610589041.8A CN106240802A (en) | 2016-07-20 | 2016-07-20 | A kind of wing aerodynamic deceleration mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610589041.8A CN106240802A (en) | 2016-07-20 | 2016-07-20 | A kind of wing aerodynamic deceleration mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106240802A true CN106240802A (en) | 2016-12-21 |
Family
ID=57604398
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610589041.8A Pending CN106240802A (en) | 2016-07-20 | 2016-07-20 | A kind of wing aerodynamic deceleration mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106240802A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606399A (en) * | 2019-01-10 | 2019-04-12 | 宝鸡文理学院 | A kind of Reduction gear for rail transit |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3360218A (en) * | 1965-06-14 | 1967-12-26 | Wendell S Miller | Vertical take-off aircraft |
| US20090284016A1 (en) * | 2008-05-16 | 2009-11-19 | Frontier Wind, Llc | Wind turbine with gust compensating air deflector |
| KR101094888B1 (en) * | 2004-04-20 | 2011-12-15 | 한국항공우주산업 주식회사 | Retractable Deflector for Aircraft Auxiliary Power Unit |
| CN102511987A (en) * | 2011-12-15 | 2012-06-27 | 广州物联家信息科技股份有限公司 | Stretching and lifting device and integrated table with same for displayer |
| CN102619677A (en) * | 2011-01-28 | 2012-08-01 | 通用电气公司 | Actuatable surface features for wind turbine rotor blades |
| CN102953926A (en) * | 2011-08-25 | 2013-03-06 | 通用电气公司 | Rotor blade assembly and method for adjusting loading capability of rotor blade |
| DE202015102982U1 (en) * | 2015-06-09 | 2015-06-24 | Waldemar Mezler | Tragfläche particular of an aircraft |
| CN204802924U (en) * | 2015-07-22 | 2015-11-25 | 浙江工业大学 | Pneumatize jack -up supporting mechanism |
| CN205022848U (en) * | 2015-10-10 | 2016-02-10 | 扬州新棱机械制造有限公司 | Wing speed reduction baffle controlling means |
-
2016
- 2016-07-20 CN CN201610589041.8A patent/CN106240802A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3360218A (en) * | 1965-06-14 | 1967-12-26 | Wendell S Miller | Vertical take-off aircraft |
| KR101094888B1 (en) * | 2004-04-20 | 2011-12-15 | 한국항공우주산업 주식회사 | Retractable Deflector for Aircraft Auxiliary Power Unit |
| US20090284016A1 (en) * | 2008-05-16 | 2009-11-19 | Frontier Wind, Llc | Wind turbine with gust compensating air deflector |
| CN102619677A (en) * | 2011-01-28 | 2012-08-01 | 通用电气公司 | Actuatable surface features for wind turbine rotor blades |
| CN102953926A (en) * | 2011-08-25 | 2013-03-06 | 通用电气公司 | Rotor blade assembly and method for adjusting loading capability of rotor blade |
| CN102511987A (en) * | 2011-12-15 | 2012-06-27 | 广州物联家信息科技股份有限公司 | Stretching and lifting device and integrated table with same for displayer |
| DE202015102982U1 (en) * | 2015-06-09 | 2015-06-24 | Waldemar Mezler | Tragfläche particular of an aircraft |
| CN204802924U (en) * | 2015-07-22 | 2015-11-25 | 浙江工业大学 | Pneumatize jack -up supporting mechanism |
| CN205022848U (en) * | 2015-10-10 | 2016-02-10 | 扬州新棱机械制造有限公司 | Wing speed reduction baffle controlling means |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606399A (en) * | 2019-01-10 | 2019-04-12 | 宝鸡文理学院 | A kind of Reduction gear for rail transit |
| CN109606399B (en) * | 2019-01-10 | 2020-07-07 | 宝鸡文理学院 | Speed reduction device for rail transit |
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161221 |
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| RJ01 | Rejection of invention patent application after publication |