CN207324086U - Model of an airplane split flap structure without additional friction - Google Patents
Model of an airplane split flap structure without additional friction Download PDFInfo
- Publication number
- CN207324086U CN207324086U CN201721372764.9U CN201721372764U CN207324086U CN 207324086 U CN207324086 U CN 207324086U CN 201721372764 U CN201721372764 U CN 201721372764U CN 207324086 U CN207324086 U CN 207324086U
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- model
- split flap
- airplane
- conduit
- wing
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Abstract
It the utility model is related to a kind of model of an airplane split flap structure of no additional friction, it is characterised in that：Including the conduit being located at after wing in lower surface（6）With the split flap being hinged in conduit（4）, the conduit（6）Inside it is additionally provided with control steering engine（1）With by control steering engine（1）Control the rocking arm rotated（2）, the rocking arm（2）Free end and connecting rod（3）First end be hinged, the connecting rod（3）Second end and split flap（4）Upper convex portion be hinged.The beneficial effects of the utility model are：Since above-mentioned split flap and its driving part are each provided at after wing in the conduit of lower surface, so as to not only contribute to make wing lower surface more clean and tidy clean, it will not produce additional friction again at the same time, not influence the normal performance of aircraft, and being conducive to the takeoff and landing of the model of an airplane.
Description
Technical field：
It the utility model is related to a kind of model of an airplane split flap structure of no additional friction.
Background technology：
Wing flap is an important device of aircraft, it can increase considerably airplane ascensional force, contribute to aircraft take off and
Landing.Split flap（Also referred to as split flaps）As one piece of thin plate, it is close to trailing edge lower surface and forms one of wing
Point.Put down and (be rotated down) during use, a low-pressure area is formed between trailing edge and wing, is had to the air-flow of upper surface of the airfoil
Sucking action, increases air-flow velocity, so as to increase the pressure difference of wing upper and lower surface, increases lift.In addition, the flap
After wing decentralization, the camber of air-foil is increased, can equally improve lift.This wing flap can generally carry the lift coefficient of wing
It is high by 75%~85%.The steering engine and connecting rod of conventional model of an airplane wing flap are external, and installation method is identical with aileron, this mounting means meeting
The model of an airplane is produced extra resistance, be particularly disadvantageous for the unpowered gliding process of aerodone.
The content of the invention：
The purpose of this utility model is to provide a kind of model of an airplane split flap structure of no additional friction, the nothing are extra
Drag model aircraft split flap is reasonable in design, is conducive to make wing lower surface neatly clean, will not produce extra resistance
Power.
The technical solution of the utility model：
Model of an airplane split flap structure of the utility model without additional friction, it is characterised in that：After being located at wing
Conduit in lower surface（6）With the split flap being hinged in conduit（4）, the conduit（6）Inside it is additionally provided with control steering engine（1）
With by control steering engine（1）Control the rocking arm rotated（2）, the rocking arm（2）Free end and connecting rod（3）First end be hinged, institute
State connecting rod（3）Second end and split flap（4）Upper convex portion be hinged.
Further, the trailing edge of above-mentioned wing（5）Using thin mask and carbon fiber, to maintain upper surface of the airfoil camber line.
Further, above-mentioned control steering engine（1）Drive rocking arm（2）Hunting range is 0-90 degree.
Model of an airplane split flap structure of the utility model without additional friction is by controlling steering engine（1）Action, make to shake
Arm（2）Start rotation, the rocking arm of rotation（2）Drive connecting rod（3）It is mobile, then drive split flap（4）Under turn over or raise up closure
Action.
The beneficial effects of the utility model are：
Since above-mentioned split flap and its driving part are each provided at after wing in the conduit of lower surface, so that not only favourable
In making wing lower surface more clean and tidy clean, while additional friction will not be produced again, does not influence the normal performance of aircraft, and favorably
In the takeoff and landing of the model of an airplane.
Brief description of the drawings：
Fig. 1 is airfoil cross-section schematic diagram when wing flap closes；
Fig. 2 is the airfoil cross-section schematic diagram after wing flap is opened.
Embodiment：
Model of an airplane split flap structure of the utility model without additional friction is included being located at after wing in lower surface
Conduit（6）With the split flap being hinged in conduit（4）, the conduit（6）Inside it is additionally provided with control steering engine（1）With by control steering engine
（1）Control the rocking arm rotated（2）, the rocking arm（2）Free end and connecting rod（3）First end be hinged, the connecting rod（3）
Two ends and split flap（4）Upper convex portion be hinged.
Further, in order to increase intensity and light, the trailing edge of above-mentioned wing（5）Using thin mask and carbon fiber, with dimension
Hold upper surface of the airfoil camber line.
Further, in order to design rationally, above-mentioned control steering engine（1）Drive rocking arm（2）Hunting range is 0-90 degree.In order to
Increase split flap（4）With trailing edge（5）The leakproofness of linking, in split flap（4）Surface can lay one layer of layer of silica gel.
Above-mentioned conduit（6）To dig out groove on a rib, will control steering engine on the rib, connecting rod connecting rocker arm and open
Wing flap is split, by controlling steering engine and rocking arm to control putting down and withdrawing for split flap.
Model of an airplane split flap structure of the utility model without additional friction is by controlling steering engine（1）Action, make to shake
Arm（2）Start rotation, the rocking arm of rotation（2）Drive connecting rod（3）It is mobile, then drive split flap（4）Under turn over or raise up closure
Action.
The beneficial effects of the utility model are：
Since above-mentioned split flap and its driving part are each provided at after wing in the conduit of lower surface, so that not only favourable
In making wing lower surface more clean and tidy clean, while additional friction will not be produced again, does not influence the normal performance of aircraft, and favorably
In the takeoff and landing of the model of an airplane.
Claims (3)
- A kind of 1. model of an airplane split flap structure of no additional friction, it is characterised in that：Including being located at lower surface after wing Interior conduit（6）With the split flap being hinged in conduit（4）, the conduit（6）Inside it is additionally provided with control steering engine（1）With by controlling Steering engine（1）Control the rocking arm rotated（2）, the rocking arm（2）Free end and connecting rod（3）First end be hinged, the connecting rod（3） Second end and split flap（4）Upper convex portion be hinged.
- 2. the model of an airplane split flap structure of no additional friction according to claim 1, it is characterised in that：The wing Trailing edge（5）Using thin mask and carbon fiber, to maintain upper surface of the airfoil camber line.
- 3. the model of an airplane split flap structure of no additional friction according to claim 1, it is characterised in that：The control Steering engine（1）Drive rocking arm（2）Hunting range is 0-90 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721372764.9U CN207324086U (en) | 2017-10-19 | 2017-10-19 | Model of an airplane split flap structure without additional friction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721372764.9U CN207324086U (en) | 2017-10-19 | 2017-10-19 | Model of an airplane split flap structure without additional friction |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207324086U true CN207324086U (en) | 2018-05-08 |
Family
ID=62365879
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721372764.9U Expired - Fee Related CN207324086U (en) | 2017-10-19 | 2017-10-19 | Model of an airplane split flap structure without additional friction |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207324086U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114506442A (en) * | 2022-01-28 | 2022-05-17 | 中国商用飞机有限责任公司 | Wing with turbulence auxiliary device and flight device comprising same |
-
2017
- 2017-10-19 CN CN201721372764.9U patent/CN207324086U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114506442A (en) * | 2022-01-28 | 2022-05-17 | 中国商用飞机有限责任公司 | Wing with turbulence auxiliary device and flight device comprising same |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180508 Termination date: 20201019 |