CN104590546A - Wing flap air blowing and high lift device - Google Patents
Wing flap air blowing and high lift device Download PDFInfo
- Publication number
- CN104590546A CN104590546A CN201410769487.XA CN201410769487A CN104590546A CN 104590546 A CN104590546 A CN 104590546A CN 201410769487 A CN201410769487 A CN 201410769487A CN 104590546 A CN104590546 A CN 104590546A
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- China
- Prior art keywords
- sleeve pipe
- pipe
- wing flap
- lift device
- high lift
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Abstract
The invention discloses a wing flap air blowing and high lift device. The wing flap air blowing and high lift device comprises a casing pipe (1), a gas exhaust pipe (2), a cover plate (3), a pair of connecting bodies (4) and a slotted round head screw (5), wherein each of two ends of the casing pipe (1) are respectively provided with a gas inlet; the casing pipe (1) is provided with a group of gas exhaust grooves (1-1); the cover plate (3) is installed on the casing pipe (1) via the slotted round head screw (5), and is positioned on the group of gas exhaust grooves (1-1) in the casing pipe (1); the gas exhaust pipe (2) is provided with a plurality of groups of holes (2-1); two ends of the gas exhaust pipe (2) are respectively installed in the casing pipe (1) via the pair of connecting bodies (4). The wing flap air blowing and high lift device has the advantages of simple structure, small size, light weight and convenience in installation.
Description
Technical field
Patent of the present invention relates to amphibious aircraft field, is specifically related to a kind of wing flap blowing high lift device.
Background technology
In order to significantly shorten the landing distance of amphibious aircraft, improving behaviour at sea, needing the lift significantly improving full machine.Such as, when landing speed reduces by 30%, need lift coefficient improve 1 times approximately.By the high lift device of routine, as droope snoot, camber flap, split flap, slotted flap, retrusive wing flap etc. are all difficult to reach this index, for this reason, need to examine
Consider means such as combining flowing control.Wing flap blowing high lift device can improve the lift 10% ~ 350% of full machine.
patent of invention content
The object of patent of the present invention, in order to significantly shorten the landing distance of amphibious aircraft, improves behaviour at sea, needs the lift significantly improving full machine.Such as, when landing speed reduces by 30%, need lift coefficient improve 1 times approximately.By the high lift device of routine, as droope snoot, camber flap, split flap, slotted flap, retrusive wing flap etc. are all difficult to reach this index, for this reason, need to consider to combine the means such as flowing control.Wing flap blowing high lift device can improve the deficiency of the lift 10% ~ 350% of full machine, and provides a kind of wing flap blowing high lift device.
The present invention includes sleeve pipe, freeing pipe, cover plate, a pair connector and slotted round head screw, the two ends of sleeve pipe are respectively equipped with admission port, sleeve pipe has one group of air discharge duct, cover plate is arranged on sleeve pipe by slotted round head screw, and be positioned on one group of air discharge duct on sleeve pipe, freeing pipe has and organizes hole more, the two ends of freeing pipe are arranged in sleeve pipe respectively by a pair connector.
Through hole is respectively equipped with in a pair connector, one end of a pair connector is respectively equipped with negative thread, the two ends of freeing pipe are respectively equipped with outside thread, the two ends of freeing pipe are connected with a pair connector threaded one end respectively, and the two ends of freeing pipe communicate with the through hole in a pair connector respectively, a pair connector is arranged on the admission port place at the two ends of sleeve pipe respectively.
One group of sleeve pipe forms spray seam between air discharge duct and cover plate, the height of spray seam is 0.2mm ~ 2mm.
Advantage of the present invention is: structure is simple, and volume is little, lightweight, easy for installation.
Accompanying drawing explanation
Accompanying drawing 1 is patent structure schematic diagram of the present invention.Accompanying drawing 2 is partial enlargement figure structure schematic representations of accompanying drawing 1.
Detailed description of the invention
As shown in Figure 1, 2, patent of the present invention comprises sleeve pipe 1, freeing pipe 2, cover plate 3, a pair connector 4 and slotted round head screw 5, the two ends of sleeve pipe 1 are respectively equipped with admission port, sleeve pipe 1 has one group of air discharge duct 1-1, cover plate 3 is arranged on sleeve pipe 1 by slotted round head screw 5, and be positioned on one group of air discharge duct 1-1 on sleeve pipe 1, freeing pipe 2 has many group hole 2-1, the two ends of freeing pipe 2 are arranged in sleeve pipe 1 respectively by a pair connector 4.
Through hole is respectively equipped with in a pair connector 4, one end of a pair connector 4 is respectively equipped with negative thread, the two ends of freeing pipe 2 are respectively equipped with outside thread, the two ends of freeing pipe 2 are connected with a pair connector 4 threaded one end respectively, and the two ends of freeing pipe 2 communicate with the through hole in a pair connector 4 respectively, a pair connector 4 is arranged on the admission port place at the two ends of sleeve pipe 1 respectively.
Formed to spray between one group of air discharge duct 1-1 of sleeve pipe 1 and cover plate 3 and stitch 3-1, the height of spray seam is 0.2mm ~ 2mm.
Mode of operation: wing flap blowing device be contained in inboard (interior wing flap device) or be contained in (outer wing flap device) outside wing, draws ventilation flue from a pair connector 4 (sleeve pipe 1 two ends) and is connected with source of the gas.Source of the gas is blown from two ends by ventilation flue, a pair connector 4 in sleeve pipe 1, gas is through the some hole 2-1 of freeing pipe 2(pipe circumference uniform distribution) exhaust, form the gas that then certain air pressure spray certain pressure from the spray of the 0.2mm ~ 2mm of sleeve pipe 1 and cover plate 3 junction seam 3-1, obtain local air flow flowing to change, and then aircraft flight performance is significantly improved.
Claims (3)
1. a wing flap blowing high lift device, it is characterized in that it comprises sleeve pipe (1), freeing pipe (2), cover plate (3), a pair connector (4) and slotted round head screw (5), the two ends of sleeve pipe (1) are respectively equipped with admission port, sleeve pipe (1) has one group of air discharge duct (1-1), cover plate (3) is arranged on sleeve pipe (1) by slotted round head screw (5), and be positioned on one group of air discharge duct (1-1) on sleeve pipe (1), freeing pipe (2) has and organizes hole (2-1) more, the two ends of freeing pipe (2) are arranged in sleeve pipe (1) respectively by a pair connector (4).
2. a kind of wing flap blowing high lift device according to claim 1, it is characterized in that being respectively equipped with through hole in a pair connector (4), one end of a pair connector (4) is respectively equipped with negative thread, the two ends of freeing pipe (2) are respectively equipped with outside thread, the two ends of freeing pipe (2) are connected with a pair connector (4) threaded one end respectively, and the two ends of freeing pipe (2) communicate with the through hole in a pair connector (4) respectively, a pair connector (4) is arranged on the admission port place at the two ends of sleeve pipe (1) respectively.
3. a kind of wing flap blowing high lift device according to claim 1, it is characterized in that being formed to spray between one group of air discharge duct (1-1) of sleeve pipe (1) and cover plate (3) stitching (3-1), the height of spray seam (3-1) is 0.2mm ~ 2mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410769487.XA CN104590546A (en) | 2014-12-15 | 2014-12-15 | Wing flap air blowing and high lift device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410769487.XA CN104590546A (en) | 2014-12-15 | 2014-12-15 | Wing flap air blowing and high lift device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104590546A true CN104590546A (en) | 2015-05-06 |
Family
ID=53116694
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410769487.XA Pending CN104590546A (en) | 2014-12-15 | 2014-12-15 | Wing flap air blowing and high lift device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104590546A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB821662A (en) * | 1956-12-11 | 1959-10-14 | Power Jets Res & Dev Ltd | Improvements in or relating to aircraft jet propulsion arrangements |
| GB846322A (en) * | 1956-08-24 | 1960-08-31 | Commw Of Australia Crown Solic | Lift augmenting means |
| US5255881A (en) * | 1992-03-25 | 1993-10-26 | Vigyan, Inc. | Lift augmentation for highly swept wing aircraft |
| CN2334674Y (en) * | 1997-12-11 | 1999-08-25 | 崔建新 | Air jet power increasing wing |
| CN102730185A (en) * | 2011-04-11 | 2012-10-17 | 波音公司 | Systems and methods for attenuation of noise and wakes produced by aircraft |
| CN102781775A (en) * | 2009-12-23 | 2012-11-14 | 空中客车运作有限责任公司 | A high lift system for an aircraft |
| CN102781774A (en) * | 2009-12-23 | 2012-11-14 | 空中客车运作有限责任公司 | Aircraft with a control device |
-
2014
- 2014-12-15 CN CN201410769487.XA patent/CN104590546A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB846322A (en) * | 1956-08-24 | 1960-08-31 | Commw Of Australia Crown Solic | Lift augmenting means |
| GB821662A (en) * | 1956-12-11 | 1959-10-14 | Power Jets Res & Dev Ltd | Improvements in or relating to aircraft jet propulsion arrangements |
| US5255881A (en) * | 1992-03-25 | 1993-10-26 | Vigyan, Inc. | Lift augmentation for highly swept wing aircraft |
| CN2334674Y (en) * | 1997-12-11 | 1999-08-25 | 崔建新 | Air jet power increasing wing |
| CN102781775A (en) * | 2009-12-23 | 2012-11-14 | 空中客车运作有限责任公司 | A high lift system for an aircraft |
| CN102781774A (en) * | 2009-12-23 | 2012-11-14 | 空中客车运作有限责任公司 | Aircraft with a control device |
| CN102730185A (en) * | 2011-04-11 | 2012-10-17 | 波音公司 | Systems and methods for attenuation of noise and wakes produced by aircraft |
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| C06 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150506 |
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| WD01 | Invention patent application deemed withdrawn after publication |