CN1184056A - Airfoil of aircraft - Google Patents
Airfoil of aircraft Download PDFInfo
- Publication number
- CN1184056A CN1184056A CN97123068A CN97123068A CN1184056A CN 1184056 A CN1184056 A CN 1184056A CN 97123068 A CN97123068 A CN 97123068A CN 97123068 A CN97123068 A CN 97123068A CN 1184056 A CN1184056 A CN 1184056A
- Authority
- CN
- China
- Prior art keywords
- wing
- airfoil member
- pivots
- tailgate
- wing flap
- 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
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/50—Varying camber by leading or trailing edge flaps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C2009/143—Adjustable control surfaces or members, e.g. rudders forming slots comprising independently adjustable elements for closing or opening the slot between the main wing and leading or trailing edge flaps
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Invalid Beds And Related Equipment (AREA)
Abstract
The main wing of an aircraft comprises a wing with a trailing edge. A pivoting flap is installed in the rear of the wing. A trailing plate is installed in the rear end part of the wing for guiding an air flow passing through an air passage formed between the wing and the flap. The trailing plate pivots between a position parallel to the upper surface of the flap and a position of contact with the trailing edge of the wing. The trailing plate is activated by a hydraulic actuator installed inside the wing.
Description
The present invention relates to a kind of host wing of aircraft, it comprises wing flap parts that pivot.
Fig. 1 schematically illustrates a kind of aircraft host wing figure commonly used.Referring to Fig. 1, a wing flap that pivots 18 is connected on the airfoil member 12 of the host wing 10 that can pivot.A leading edge 14 of this airfoil member 12 is made with a predetermined curvature.A recess 24 is made at trailing edge 16 places at airfoil member 12, and it has the curvature corresponding to wing flap 18 curvature that pivot.In addition, form a tab 26 at the downside place of trailing edge 16, it is driven by an electrical motor (not shown) perpendicular to trailing edge 16 lower surfaces and is provided.
As shown in fig. 1, when an airplane took off or lands, the wing flap 18 that pivots was pivoted downwards, and formed an air by-pass passage 100 between the leading edge of the surface of recess 24 and trailing edge 16 downsides and the wing flap 18 that pivots.Here, mobile along the upper surface airflow flowing Fu of airfoil member 12 along the upper surface of the wing flap 18 that pivots, and mobile along the lower surface airflow flowing Fj of airfoil member 12 along the lower surface of the wing flap 18 that pivots.Air-flow Fp along air by-pass passage 100 towards arrow " K " indicated direction advance, this air-flow Fp is adjusted the upper surface of the wing flap 18 that sheet 26 guiding pivot.
But because air-flow is pivoted towards the tab 26 of the upper surface of the wing flap 18 that rotates around the pivot guiding lower surface perpendicular to trailing edge 16, therefore near eddy current Fv of generation tab 26 forms a wake flow at the rear portion of tab 26 simultaneously.This eddy current and wake flow have increased resistance and have caused the degradation of taking off and landing.
In order to address the above problem, the purpose of this invention is to provide a kind of aircraft host wing with improved structure, by this improved structure decrease near the generation of airstream eddy current and wake flow tab, this tab is installed in the rear end of host wing.
In order to achieve the above object, a kind of host wing of aircraft is provided, it comprises an airfoil member with trailing edge, one is installed to the rear end of airfoil member so that the wing flap that pivots that can be pivoted, a tailgate that is installed in airfoil member rearward end office, with one be used to actuating device that this tailgate is pivoted, this tailgate is used for the lead upper surface of this wing flap that pivots of an air-flow by the air by-pass passage that forms between airfoil member and the wing flap that pivots, and tailgate is pivoted between the position of the position of a upper surface that is parallel to the wing flap that pivots and a contact airfoil member trailing edge.
In addition, according to another aspect of the present invention, a kind of host wing of aircraft is provided, it comprises that an airfoil member, one are installed to the wing flap that pivots, tailgate that is installed in airfoil member rearward end office that the airfoil member rear portion can be pivoted, with one be used to actuating device that this tailgate is pivoted, this tailgate forms a trailing edge of airfoil member, is used for the lead upper surface of this wing flap that pivots of an air-flow by the air by-pass passage that forms between airfoil member and the wing flap that pivots.
Preferably, this actuating device is one and is installed in airfoil member in-to-in hydraulic actuating cylinder.
By describing an one preferred embodiment in detail referring to accompanying drawing, it is more obvious that above-mentioned purpose of the present invention and advantage will become, wherein:
Fig. 1 is the side sectional view that a kind of aircraft host wing commonly used is shown;
Fig. 2 is the side sectional view that a kind of aircraft host wing according to a preferred embodiment of the present invention is shown;
Fig. 3 is the detailed side sectional view that tailgate shown in Fig. 2 is shown;
Fig. 4 is the side sectional view that a kind of aircraft host wing according to another preferred embodiment of the present invention is shown; With
Fig. 5 is the detailed side sectional view that tailgate shown in Fig. 4 is shown.
To a kind of aircraft host wing according to first preferred embodiment of the present invention be described referring to Fig. 2 and 3 now.Here, identical label representative has the same parts of identical function among Fig. 1-3.
According to the distinctive characteristics of present embodiment, the tailgate 36 that is used for the upper surface of wing flap 18 that the guiding of the air-flow Fp by air by-pass passage 100 is pivoted is installed in the rearward end office of the airfoil member 12 of host wing 10 by pivoting.This tailgate 36 is installed into from the rear end part of airfoil member 12 and stretches out towards the leading edge direction of the wing flap 18 that pivots.
Tailgate 36 is installed in wing section 12 in-to-in hydraulic actuating cylinders 35 by one and is pivoted between the position of the lower surface of the position of a upper surface that is parallel to the wing flap 18 that pivots and a contact trailing edge 16.That is to say that when an airplane took off or lands, tailgate 36 was pivoted by the leading edge of hydraulic actuating cylinder 35 towards the wing flap 18 that pivots, and is roughly parallel to this wing flap that pivots 18.Thereby the air-flow Fp by air by-pass passage 100 is by the upper surface of tailgate 36 these wing flaps that pivot 18 of guiding.Here, the air-flow Fp of contact tailgate 36 gently flows, and has reduced the generation of eddy current, and has reduced the resistance to host wing 10.
In addition, when an airplane in when flight, tailgate 36 pivots to the lower surface of contact trailing edge 16.This wing flap that pivots 18 can for example replace hydraulic actuating cylinder to be pivoted with an electrical motor by an actuating device, and therefore, this actuating device is not limited to present embodiment of the present invention.
To a kind of host wing according to second preferred embodiment of the present invention be described referring to Figure 4 and 5 now.Here, with aforementioned figures in the identical parts of identical label representative.
According to the peculiar characteristics of the second embodiment of the present invention, tailgate 136 pivotings are combined in the rearward end office of airfoil member 12, and this tailgate 136 forms the trailing edge of the airfoil member 12 of host wing 10.Tailgate 136 is connected to and is installed on hydraulic actuating cylinder 135 of airfoil member 12 in-to-ins, so that it can pivot to and an airfoil member 12 or a predetermined angle.
When an airplane in when navigation, tailgate 136 keeps parallel with the wing flap 18 that pivots.When taking off or land, the wing flap 18 that pivots is pivoted down into a predetermined angle, as shown in the drawing.Tailgate 136 also is pivoted so downwards, so that the upper surface keeping parallelism of it and this wing flap that pivots 18.Therefore, the upper surface of the wing flap 18 that pivoted by tailgate 136 guiding of the air-flow Fp by air by-pass passage 100.Here, because the mobile of air-flow Fp is mild, thus can reduce the generation of eddy current, and thereby can reduce resistance to host wing.
In addition, if necessary, tailgate 136 can be used as a spoiler or an air circuit breaker is used.
As mentioned above, according to the host wing of a kind of aircraft of the present invention, tailgate adopts the rear end part be positioned at airfoil member, so as near the eddy current that tab, is produced according to routine techniques and since the turbulent resistance that produces can reduce a lot.
Claims (4)
1. the host wing of an aircraft comprises:
An airfoil member, it has a trailing edge;
The wing flap that can pivot, it is installed in the rear portion of described airfoil member, can be pivoted;
A tailgate, it is installed in the rearward end office of described airfoil member, be used for the leading upper surface of this wing flap that pivots by the air-flow of the air by-pass passage that between described airfoil member and the wing flap that pivots, forms, described tailgate is pivoted between the position of the position of a upper surface that is parallel to the wing flap that pivots and a contact airfoil member trailing edge; With
An actuating device is used to make described tailgate to be pivoted.
2. a kind of aircraft host wing as claimed in claim 1 is characterized in that described actuating device is one and is installed in airfoil member in-to-in hydraulic actuating cylinder.
3. the host wing of an aircraft comprises:
An alar part spare;
A wing flap that pivots, it is installed in the rear portion of described airfoil member, can be pivoted;
A tailgate, it is installed in the rearward end office of described airfoil member, form the trailing edge of this airfoil member, be used for the lead upper surface of this wing flap that pivots of the air-flow by the air by-pass passage that between described airfoil member and the wing flap that pivots, forms; With
An actuating device is used to make described tailgate to be pivoted.
4. the host wing of a kind of aircraft as claimed in claim 3 is characterized in that described actuating device is one and is installed in described airfoil member in-to-in hydraulic actuating cylinder.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR59835/96 | 1996-11-29 | ||
| KR1019960059835A KR19980040611A (en) | 1996-11-29 | 1996-11-29 | Aircraft wing |
| KR1019960059834A KR100236122B1 (en) | 1996-11-29 | 1996-11-29 | The wing of airplane |
| KR59834/96 | 1996-11-29 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1184056A true CN1184056A (en) | 1998-06-10 |
Family
ID=26632309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN97123068A Pending CN1184056A (en) | 1996-11-29 | 1997-11-28 | Airfoil of aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN1184056A (en) |
| FR (1) | FR2756540A1 (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101765539A (en) * | 2007-07-27 | 2010-06-30 | 波音公司 | Translating flap drive door |
| CN101346276B (en) * | 2005-12-29 | 2010-09-15 | 空中客车德国有限公司 | Airfoil for an aircraft and aircraft |
| CN102040002A (en) * | 2010-12-02 | 2011-05-04 | 北京航空航天大学 | Curve slide-connecting rod mechanism in high lift device of large aircraft |
| CN102267558A (en) * | 2011-05-07 | 2011-12-07 | 王志成 | Double speed moving plane airfoil |
| CN102787772A (en) * | 2011-08-05 | 2012-11-21 | 薛广振 | Space hinge |
| CN101484355B (en) * | 2006-06-30 | 2013-08-21 | 空中客车德国运营有限责任公司 | Adjusting device for adjusting a high-lift flap and airfoil wing comprising such an adjusting device |
| US8596584B2 (en) | 2007-12-20 | 2013-12-03 | Airbus Operations Gmbh | High-lift system for an aircraft with a main wing and an adjustable slat |
| CN106542081A (en) * | 2015-09-18 | 2017-03-29 | 哈尔滨飞机工业集团有限责任公司 | The single seam fowler formula wing flap design of one kind of (1) -0313 aerofoil profiles of NASA MS |
| CN113291458A (en) * | 2021-06-25 | 2021-08-24 | 庆安集团有限公司 | Inner and outer flap cross-linking device for high-lift system of airplane |
| CN117775272A (en) * | 2024-01-30 | 2024-03-29 | 中国商用飞机有限责任公司 | Leading edge slat and wing for aircraft |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6799739B1 (en) | 2003-11-24 | 2004-10-05 | The Boeing Company | Aircraft control surface drive system and associated methods |
| CA2522553C (en) * | 2004-10-11 | 2010-09-21 | Airbus Deutschland Gmbh | Aircraft wing, method for operating an aircraft wing, and use of a pivotable trailing edge on a main wing of an aircraft, for adjusting the shape and the width of an air gap |
| DE102004049504A1 (en) | 2004-10-11 | 2006-04-13 | Airbus Deutschland Gmbh | Wing for aircraft has a rear auxiliary lift flap coupled to main wing and able to lie against main wing in retracted position and form air gap with it when extended |
| US7338018B2 (en) | 2005-02-04 | 2008-03-04 | The Boeing Company | Systems and methods for controlling aircraft flaps and spoilers |
| US7721999B2 (en) | 2005-05-20 | 2010-05-25 | The Boeing Company | Aerospace vehicle fairing systems and associated methods |
| CN115384757B (en) * | 2022-10-31 | 2023-01-24 | 北京启时智航科技有限公司 | Flaperon actuating mechanism and wing structure |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3583660A (en) * | 1969-08-18 | 1971-06-08 | Lockheed Aircraft Corp | Lift and control augmenter for airfoils |
| US3767140A (en) * | 1971-11-03 | 1973-10-23 | Mc Donnell Douglas Corp | Airplane flaps |
| US3874617A (en) * | 1974-07-17 | 1975-04-01 | Mc Donnell Douglas Corp | Stol flaps |
| US4120470A (en) * | 1976-09-28 | 1978-10-17 | The Boeing Company | Efficient trailing edge system for an aircraft wing |
| US4705236A (en) * | 1981-09-29 | 1987-11-10 | The Boeing Company | Aileron system for aircraft and method of operating the same |
| US5094412A (en) * | 1989-10-13 | 1992-03-10 | Bell Helicopter Textron Inc. | Flaperon system for tilt rotor wings |
-
1997
- 1997-11-28 CN CN97123068A patent/CN1184056A/en active Pending
- 1997-11-28 FR FR9715045A patent/FR2756540A1/en active Pending
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101346276B (en) * | 2005-12-29 | 2010-09-15 | 空中客车德国有限公司 | Airfoil for an aircraft and aircraft |
| CN101484355B (en) * | 2006-06-30 | 2013-08-21 | 空中客车德国运营有限责任公司 | Adjusting device for adjusting a high-lift flap and airfoil wing comprising such an adjusting device |
| CN101765539A (en) * | 2007-07-27 | 2010-06-30 | 波音公司 | Translating flap drive door |
| CN101903239B (en) * | 2007-12-20 | 2014-06-18 | 空中客车营运有限公司 | Lift system comprising a main wing and an adjustable slat for an aircraft |
| US8596584B2 (en) | 2007-12-20 | 2013-12-03 | Airbus Operations Gmbh | High-lift system for an aircraft with a main wing and an adjustable slat |
| CN102040002A (en) * | 2010-12-02 | 2011-05-04 | 北京航空航天大学 | Curve slide-connecting rod mechanism in high lift device of large aircraft |
| CN102267558A (en) * | 2011-05-07 | 2011-12-07 | 王志成 | Double speed moving plane airfoil |
| CN102267558B (en) * | 2011-05-07 | 2013-06-19 | 王志成 | Double speed moving plane airfoil |
| CN102787772A (en) * | 2011-08-05 | 2012-11-21 | 薛广振 | Space hinge |
| CN106542081A (en) * | 2015-09-18 | 2017-03-29 | 哈尔滨飞机工业集团有限责任公司 | The single seam fowler formula wing flap design of one kind of (1) -0313 aerofoil profiles of NASA MS |
| CN113291458A (en) * | 2021-06-25 | 2021-08-24 | 庆安集团有限公司 | Inner and outer flap cross-linking device for high-lift system of airplane |
| CN117775272A (en) * | 2024-01-30 | 2024-03-29 | 中国商用飞机有限责任公司 | Leading edge slat and wing for aircraft |
| CN117775272B (en) * | 2024-01-30 | 2024-05-14 | 中国商用飞机有限责任公司 | Leading edge slat and wing for aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2756540A1 (en) | 1998-06-05 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C01 | Deemed withdrawal of patent application (patent law 1993) | ||
| WD01 | Invention patent application deemed withdrawn after publication |