CN102642616B - Airplane high lift device with fixed double slotted flaps - Google Patents
Airplane high lift device with fixed double slotted flaps Download PDFInfo
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- CN102642616B CN102642616B CN201210146287.XA CN201210146287A CN102642616B CN 102642616 B CN102642616 B CN 102642616B CN 201210146287 A CN201210146287 A CN 201210146287A CN 102642616 B CN102642616 B CN 102642616B
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Abstract
The invention belongs to the field of design and relates to an airplane high lift device with fixed double slotted flaps for increasing the lift force of an airplane to take off and land. The high lift device comprises a main flap, a rear flap, a Y-shaped bracket, a main wing rear spar fixed link, an actuator cylinder, a first linkage rod, a second linkage rod, a third linkage rod, a spoiler, a lower baffle plate and a stripper rubber. The structural weight of the high lift device provided by the invention is 60%-75% of that of the airplane high lift device with a non-fixed main/rear slotted flap. Compared with the airplane high lift device with the non-fixed main/rear slotted flap, the high lift device provided by the invention enables the production cost of the airplane to be decreased by 1.5%-3.5%, the loading capacity of passengers or cargos to be increased by 0.5%-1.5%, the fuel oil consumption in unit loading of the airplane to be decreased by 0.5%-1.5% and the operating cost of the airplane to be decreased by 0.5%-1.5%. A fixed-axis rotation movement mechanism provided by the invention is better than the traditional sliding rail movement mechanism.
Description
Technical field:
The invention belongs to design field, relate to a kind of aircraft high lift device of the fixing double slit wing flap of band that increases airplane ascensional force when taking off and land.
Background technology
The existing aircraft high lift device (as shown in Figure 1) with on-fixed main wing flap/rear wing flap, because main wing flap and rear wing flap are separate, in order to ensure that, in the time being subject to maximum aerodynamic loading, their structural distortion can meet design requirement, their structural weight all needs larger; The strength and stiffness of their kinematic mechanism also all must meet design requirement, thereby their kinematic mechanism weight is also larger.The weight of the aircraft high lift device with on-fixed main wing flap/rear wing flap is 1.8～2.4 times of weight of the aircraft high lift device of the single seam of band wing flap, this part weight increasing is 1%～2% of take-off weight, this causes the productive costs of aircraft to increase by 2%～5%, passenger or charging burden reduce 1%～2%, and the fuel consumption that the unit of aircraft loads increases by 1%～2%.
Summary of the invention
The object of the invention is to propose a kind of in improving lift-rising ability, ensure that wing flap kinematic mechanism relatively simply be with the aircraft high lift device of fixing double slit wing flap.Technical solution of the present invention is, high lift device comprises main wing flap, rear wing flap, Y shaped bracket, main wing back rest fixed link, pressurized strut, the first gangbar, the second gangbar, the 3rd gangbar, spoiler, lower baffle plate, stripper rubber, one end of main wing back rest fixed link is fixed on edge strip place under the back rest on main wing, the width of this one end of main wing back rest fixed link is identical with the lower edge strip width of the back rest, the other end of main wing back rest fixed link is hinged by one end of main hinge and Y shaped bracket, the smooth gradual change of width of main wing back rest fixed link is to identical with the diameter of main hinge, two other end face of Y shaped bracket is separately fixed at the back of robe spar bottom in main wing flap beam bottom and the rear wing flap in main wing flap, the end face width that Y shaped bracket is fixed on the main wing flap beam bottom in main wing flap is 2 times of edge strip width under main wing flap beam, and the end face width that Y shaped bracket is fixed on the back of robe spar bottom in rear wing flap is 2.5 times of edge strip width under back of robe spar, one end of connecting rod is fixed on close main hinge place on main wing back rest fixed link, and this fixed position is 10%～25% of main wing back rest fixed link length to the distance of main hinge, and one end of the other end of connecting rod and the first gangbar is hinged, the other end while of the first gangbar is hinged with one end of one end of the second gangbar, the 3rd gangbar, the other end of the second gangbar is hinged on the inwall of main wing flap one side on Y shaped bracket, this articulated position is the lower surface that under the main wing flap back rest, edge strip is hinged on lower baffle plate to the other end of the 15%～25%, three gangbar of the distance of main hinge to the distance of main flap lower surface,
The distance of this articulated position and main flap hinge is 25%～50% of lower baffle plate length;
One end of lower baffle plate is hinged on main wing flap the rear of edge strip under main wing flap beam by main flap hinge, and the other end of lower baffle plate is fixed with a stripper rubber, and stripper rubber and the laminating of back of robe nose of wing will part sealings under back of robe wing tank;
The fixed end of pressurized strut is hinged on main wing back rest fixed link, this articulated position is 5%～30% of back rest fixed link length to the distance of edge strip under the back rest on main wing, the movable end of pressurized strut is hinged on Y shaped bracket, and this articulated position is 20%～60% of the main hinge distance that arrives edge strip under main wing flap beam to the distance of edge strip under main wing flap beam;
The afterbody of the spoiler on main wing rides over edge strip place on the back of robe spar in rear wing flap, and back of robe wing tank is covered, and the afterbody of spoiler and main wing flap is gapped.
The advantage that the present invention has and beneficial effect, what the present invention adopted is the aircraft high lift device with the fixing master/rear double slit wing flap of fixed-axis rotation trailing edge, the lift-rising ability of high lift device of the present invention, is not less than the lift-rising ability of the aircraft high lift device with on-fixed master/rear double slit wing flap.The structural weight of high lift device of the present invention be the aircraft high lift device with on-fixed master/rear double slit wing flap weight 60%～75%.With respect to the aircraft high lift device of on-fixed master/rear double slit wing flap, adopt high lift device of the present invention, the productive costs of aircraft can reduce by 1.5%～3.5%, passenger or charging burden increase by 0.5%～1.5%, the fuel consumption that the unit of aircraft loads reduces by 0.5%～1.5%, and the operation cost of aircraft reduces by 0.5%～1.5%.Compared with traditional slide rail kinematic mechanism, the fixed-axis rotation kinematic mechanism that the present invention adopts is lighter, reliability is higher, control response is faster.
Brief description of the drawings
The structural representation of Fig. 1 prior art;
Fig. 2 is structural representation of the present invention;
Fig. 3 is takeoff condition schematic diagram of the present invention;
Fig. 4 is landing state schematic diagram of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is elaborated.
As shown in the figure, high lift device comprises main wing flap 2, rear wing flap 3, Y shaped bracket 8, main wing back rest fixed link 9, pressurized strut 10, the first gangbar 11, the second gangbar 15, the 3rd gangbar 16, spoiler 4, lower baffle plate 6, stripper rubber 7,
One end of main wing back rest fixed link 9 is fixed on the 12 times edge strip places of the back rest on main wing 1, the width of this one end of main wing back rest fixed link 9 is identical with the lower edge strip width of the back rest 7, the other end of main wing back rest fixed link 9 is hinged with one end of Y shaped bracket 8 by main hinge 13, and the smooth gradual change of width of main wing back rest fixed link 9 is to identical with the diameter of main hinge 13; Two other end face of Y shaped bracket 8 is separately fixed at the back of robe spar bottom in main wing flap beam bottom and the rear wing flap 3 in main wing flap 2, the end face width that Y shaped bracket 8 is fixed on the main wing flap beam bottom in main wing flap 2 is 2 times of edge strip width under main wing flap beam, and the end face width that Y shaped bracket 8 is fixed on the back of robe spar bottom in rear wing flap 3 is 2.5 times of edge strip width under back of robe spar; One end of connecting rod 14 is fixed on close main hinge 13 places on main wing back rest fixed link 9, and this fixed position is 10%～25% of main wing back rest fixed link 9 length to the distance of main hinge 13, and one end of the other end of connecting rod 14 and the first gangbar 11 is hinged; The other end while of the first gangbar 11 is hinged with one end of one end of the second gangbar 15, the 3rd gangbar 16, the other end of the second gangbar 15 is hinged on the inwall of main wing flap 2 one sides on Y shaped bracket 8, this articulated position is the lower surface that under the main wing flap back rest, edge strip is hinged on lower baffle plate 6 to the other end of the 15%～25%, three gangbar 16 of the distance of main hinge 13 to the distance of main flap lower surface;
The distance of this articulated position and main flap hinge 17 is 25%～50% of lower baffle plate 6 length;
One end of lower baffle plate 6 is hinged on main wing flap 2 rear of edge strip under main wing flap beam by main flap hinge 17, and the other end of lower baffle plate 6 is fixed with a stripper rubber 7, and stripper rubber 7 and rear wing flap 3 leading edges laminatings, by 5 times part sealings of back of robe wing tank;
The fixed end of pressurized strut 10 is hinged on main wing back rest fixed link 9, this articulated position is 5%～30% of back rest fixed link 9 length to the distance of the 12 times edge strips of the back rest on main wing 1, the movable end of pressurized strut 10 is hinged on Y shaped bracket 8, and this articulated position is main hinge 13 to 20%～60% of the distance of edge strip under main wing flap beam to the distance of edge strip under main wing flap beam;
The afterbody of the spoiler 4 on main wing 1 rides over edge strip place on the back of robe spar in rear wing flap 3, and back of robe wing tank 5 is covered, and spoiler 4 is gapped with the afterbody of main wing flap 2.
The present invention can divide 6 steps to realize:
(1) as shown in the figure, according to general design requirement, determine respectively the length of main wing 1 and spoiler 4, determine the total length of main wing flap 2 leading edges to rear wing flap 3 trailing edges;
(2) length of spoiler 4 can cover main wing flap 2 and interplane back of robe wing tank 5 tops of the back of robe as standard completely taking spoiler 4, determines the size of main wing flap 2 and rear wing flap 3;
(3) design the cross-sectional profile of main wing flap 2 and rear wing flap 3, main wing flap 2 and rear wing flap 3 are all fixed on Y shaped bracket 8, Y shaped bracket 8 is hinged on main wing back rest fixed link 9 by main hinge 13;
(4) one end of connecting rod 14 is fixed on main wing back rest fixed link 9, the other end and the first gangbar 11 are hinged, one end of the other end of the first gangbar 11 and the second gangbar 15, one end of the 3rd gangbar 16 are hinged, the other end of the second gangbar 15 is hinged on Y shaped bracket 8, and the other end of the 3rd gangbar 16 is hinged on lower baffle plate 6;
(5) stripper rubber 7 is fixed on one end of close rear wing flap 3 heads of lower baffle plate 6.
(6) fixed end of pressurized strut 10 is hinged on main wing back rest fixed link 9, the movable end of pressurized strut 10 is hinged on Y shaped bracket 8, the fore and aft motion of the movable end by pressurized strut 10, drive Y shaped bracket 8, main wing flap 2 and rear wing flap 3 to rotate simultaneously, Y shaped bracket 8 drives the second gangbar 15, the first gangbar 11 and the 3rd gangbar 16 to rotate, and the 3rd gangbar 16 drives lower baffle plate 6 to carry out deflection around main flap hinge 17.
The present invention realizes the yaw motion of aircraft flap by following steps:
(1) aircraft is in the time of cruising condition, and main wing flap 2 and rear wing flap 3 are in collapsed state, and lower baffle plate 6 and stripper rubber 7 seal back of robe wing tank 5;
(2) aircraft is in the time of takeoff condition, and the movable end of pressurized strut 10 is protruding, promotes Y shaped bracket 8, main wing flap 2, rear wing flap 3 and lower baffle plate 6 deflections simultaneously, until main wing flap 2 deflects into the predetermined angle of takeoff condition, and the movable end stop motion of start 10;
(3) aircraft is in the time of landing state, the movable end of pressurized strut 10 continues protruding, promote Y shaped bracket 8, main wing flap 2, rear wing flap 3 and lower baffle plate 6 deflections simultaneously, until main wing flap 2 deflects into the predetermined angle of landing state, the movable end stop motion of start 10;
(4), when the ground roll-out of aircraft before stopping, the inside indentation of movable end of pressurized strut 10, promotes Y shaped bracket 8, main wing flap 2, rear wing flap 3 and lower baffle plate 6 deflections simultaneously, until main wing flap 2 deflects into collapsed state, and the movable end stop motion of start 10.
Claims (1)
1. the aircraft high lift device of the fixing double slit wing flap of band, it is characterized in that, high lift device comprises main wing flap (2), rear wing flap (3), Y shaped bracket (8), main wing back rest fixed link (9), pressurized strut (10), the first gangbar (11), the second gangbar (15), the 3rd gangbar (16), spoiler (4), lower baffle plate (6), stripper rubber (7), one end of main wing back rest fixed link (9) is fixed on the lower edge strip of the back rest (12) place on main wing (1), the width of this one end of main wing back rest fixed link (9) is identical with the lower edge strip width of the back rest (12), the other end of main wing back rest fixed link (9) is hinged with one end of Y shaped bracket (8) by main hinge (13), the smooth gradual change of width of main wing back rest fixed link (9) is to identical with the diameter of main hinge (13), two other end face of Y shaped bracket (8) is separately fixed at the back of robe spar bottom in main wing flap beam bottom and the rear wing flap (3) in main wing flap (2), the end face width that Y shaped bracket (8) is fixed on the main wing flap beam bottom in main wing flap (2) is 2 times of edge strip width under main wing flap beam, and the end face width that Y shaped bracket (8) is fixed on the back of robe spar bottom in rear wing flap (3) is 2.5 times of edge strip width under back of robe spar, one end of connecting rod (14) is fixed on the upper close main hinge (13) of main wing back rest fixed link (9) and locates, this fixed position is 10%～25% of main wing back rest fixed link (9) length to the distance of main hinge (13), and one end of the other end of connecting rod (14) and the first gangbar (11) is hinged, the other end while of the first gangbar (11) is hinged with one end of one end of the second gangbar (15), the 3rd gangbar (16), the other end of the second gangbar (15) is hinged on the inwall of main wing flap (2) one sides on Y shaped bracket (8), this articulated position is the lower surface that under the main wing flap back rest, edge strip is hinged on lower baffle plate (6) to the other end of the 15%～25%, three gangbar (16) of the distance of main hinge (13) to the distance of main flap lower surface, the distance of this articulated position and main flap hinge (17) is 25%～50% of lower baffle plate (6) length, one end of lower baffle plate (6) is hinged on the rear of edge strip under the upper main wing flap beam of main wing flap (2) by main flap hinge (17), the other end of lower baffle plate (6) is fixed with a stripper rubber (7), stripper rubber (7) and the laminating of rear wing flap (3) leading edge, by lower back of robe wing tank (5) part sealing, the fixed end of pressurized strut (10) is hinged on main wing back rest fixed link (9), it is 5%～30% of back rest fixed link (9) length that this articulated position is descended the distance of edge strip to the back rest (12) on main wing (1), it is upper that the movable end of pressurized strut (10) is hinged on Y shaped bracket (8), and this articulated position is 20%～60% of main hinge (13) distance that arrives edge strip under main wing flap beam to the distance of edge strip under main wing flap beam, the afterbody of the spoiler (4) on main wing (1) rides over edge strip place on the back of robe spar in rear wing flap (3), and back of robe wing tank (5) is covered, and spoiler (4) is gapped with the afterbody of main wing flap (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210146287.XA CN102642616B (en) | 2012-05-11 | 2012-05-11 | Airplane high lift device with fixed double slotted flaps |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210146287.XA CN102642616B (en) | 2012-05-11 | 2012-05-11 | Airplane high lift device with fixed double slotted flaps |
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| Publication Number | Publication Date |
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| CN102642616A CN102642616A (en) | 2012-08-22 |
| CN102642616B true CN102642616B (en) | 2014-09-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210146287.XA Active CN102642616B (en) | 2012-05-11 | 2012-05-11 | Airplane high lift device with fixed double slotted flaps |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9580168B2 (en) * | 2014-12-19 | 2017-02-28 | The Boeing Company | Cove lip door slaved to trailing edge control device |
| CN109018300B (en) * | 2018-08-16 | 2020-02-04 | 晨龙飞机（荆门）有限公司 | Adjustable wing slat on aircraft wing |
| CN110294102B (en) * | 2019-04-26 | 2023-05-23 | 庆安集团有限公司 | Composite motion mechanism of integrated flap aileron |
| CN112339987B (en) * | 2020-10-29 | 2022-06-28 | 中电科芜湖通用航空产业技术研究院有限公司 | Double-slit wing flap with wing flap fixedly connected with additional wing |
| CN112678150B (en) * | 2020-12-31 | 2024-04-26 | 中国商用飞机有限责任公司 | Aircraft trailing edge flap |
| CN113104196B (en) * | 2021-05-28 | 2022-05-24 | 中国商用飞机有限责任公司 | High-lift device and high-lift method for aircraft |
| 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 |
| CN115817795B (en) * | 2022-12-27 | 2023-08-01 | 江苏华阳重工股份有限公司 | High-performance flap rudder body |
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| CN1982157A (en) * | 2005-11-21 | 2007-06-20 | 波音公司 | Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods |
| WO2009067319A3 (en) * | 2007-11-16 | 2009-07-23 | Boeing Co | Method and apparatus for a multi-segment flap fence |
| CN101678893A (en) * | 2007-04-24 | 2010-03-24 | 空中客车运营有限公司 | Aircraft |
| CN102137793A (en) * | 2008-08-28 | 2011-07-27 | 空中客车营运有限公司 | High lift system for an aircraft with a high lift flap and method for adjusting the high lift flap |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007020870A1 (en) * | 2007-05-04 | 2008-11-13 | Airbus Deutschland Gmbh | High-lift system on the wing of an aircraft |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1982157A (en) * | 2005-11-21 | 2007-06-20 | 波音公司 | Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods |
| CN101678893A (en) * | 2007-04-24 | 2010-03-24 | 空中客车运营有限公司 | Aircraft |
| WO2009067319A3 (en) * | 2007-11-16 | 2009-07-23 | Boeing Co | Method and apparatus for a multi-segment flap fence |
| CN102137793A (en) * | 2008-08-28 | 2011-07-27 | 空中客车营运有限公司 | High lift system for an aircraft with a high lift flap and method for adjusting the high lift flap |
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| CN102642616A (en) | 2012-08-22 |
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