CN104691740A - Structure for trailing edge slat of thin-airfoil-profile aircraft and linkage method of structure - Google Patents
Structure for trailing edge slat of thin-airfoil-profile aircraft and linkage method of structure Download PDFInfo
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- CN104691740A CN104691740A CN201410316272.2A CN201410316272A CN104691740A CN 104691740 A CN104691740 A CN 104691740A CN 201410316272 A CN201410316272 A CN 201410316272A CN 104691740 A CN104691740 A CN 104691740A
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Abstract
The invention discloses a structure for a trailing edge slat of a thin-airfoil-profile aircraft and a linkage method of the structure. The trailing edge slat comprises a main foil and two sub-foils, wherein two flap runners are symmetrically arranged at the two sides of the trailing edge slat, sub-foil rotating shaft holes are respectively formed in the two flap runners, and a sub-foil rotating shaft penetrates through the sub-foil rotating shaft holes and is rotatably connected with the front ends of the two sub-foils; main foil rotation pin slide rings are arranged in the sub-foils, and the front end of the main foil is in sliding and rotating connection with the main foil rotation pin slide rings through a main foil rotation pin; the two ends of the main foil rotation pin are in sliding connection with arc-shaped main foil sliding grooves in the flap runners; a driving lug which is located at a joint gap of the two sub-foils is arranged at the front end of the main foil and is hinged to a telescopic rod which is located on an actuating cylinder between the two sub-foils, and a cylinder body of the actuating cylinder is hinged to an airfoil. According to the structure for the trailing edge slat of the thin-airfoil aircraft and the linkage method of the structure, the linkage of the main foil and the sub-foils in the trailing edge slat is realized through one actuating cylinder, the whole mechanism can be completely hidden in the airfoil of the trailing edge slat, and the smoothness of the appearance of the whole trailing edge slat is ensured, so that the aerodynamic characteristics of the trailing edge slat are improved.
Description
Technical field
the present invention relates to a kind of structure and interlock method of thin airfoil aircraft trailing edge slat, belong to aircraft wing actuation techniques field.
Background technology
trailing edge slat is widely deployed on airline carriers of passengers due to its good aerodynamic characteristic, to the aircraft using thin airfoil wing, due to the restriction of aerofoil profile height, on airline carriers of passengers, the drive system of trailing edge slat is as being transplanted on thin airfoil aircraft, will inevitably under the wings of an airplane aerofoil arrange larger fairing, have a strong impact on aeroperformance, offset the aerodynamic advantages of trailing edge slat.Therefore it is compact to small-sized thin airfoil aircraft wing inner space, when simultaneously high to shape requirement, the structure of existing trailing edge slat can not meet the requirement of use, needs another kind of simple for structure, all drive elements not give prominence to the novel trailing edge slat drive system of airfoil as far as possible.
Summary of the invention
the object of the invention is to, a kind of structure and interlock method of thin airfoil aircraft trailing edge slat are provided, to realize the interlock of thin airfoil aircraft main plane and sub-aerofoil when the fairing of guarantee wing profile does not affect high-lift systems, thus overcome the deficiencies in the prior art.
technical scheme of the present invention:
the structure of a kind of thin airfoil aircraft trailing edge slat of the present invention is that this trailing edge slat comprises main wing and the sub-wing; Trailing edge slat both sides are provided with symmetrical flap-track, and two pieces of flap-tracks are provided with sub-wing shaft hole, and sub-wing rotating shaft is rotationally connected through sub-wing shaft hole and two pieces of sub-wing front ends; Be provided with main wing in the sub-wing to ship and resell on another market slip ring, main wing nose to slide from slip ring of shipping and reselling on another market with main wing from shipping and reselling on another market through main wing and is rotationally connected; Main wing is connected with the arc main wing slide on flap-track from two ends of shipping and reselling on another market; Main wing nose is positioned at two pieces of sub-wing gaping of joints places and is provided with driving auricle, and drive the expansion link in auricle and the pressurized strut between two pieces of sub-wings hinged, cylindrical shell and the wing of pressurized strut are hinged.
of the present invention a kind of interlock method for the structure of above-mentioned thin airfoil aircraft trailing edge slat is, the method is by being located at pressurized strut push-and-pull main wing between the two cross-talk wings along the arc main wing slide on flap-track; In main wing sliding process, certainly ship and resell on another market with the main wing in the sub-wing from slip ring band mover wing rotation of shipping and reselling on another market, to realize the interlock between main wing and the sub-wing by the main wing of main wing nose.
in preceding method, when described pressurized strut promotes main wing along arc main wing chute slide downward on flap-track, main wing with the main wing of its front end from shipping and reselling on another market as axis both clockwise rotation.
in preceding method, when described main wing is along arc main wing chute slide downward on flap-track, the main wing of main wing nose slides to the right in slip ring of shipping and reselling on another market from the main wing of shipping and reselling on another market in the sub-wing, from slip ring of shipping and reselling on another market, downward pressure is applied to main wing simultaneously, force the sub-wing with sub-wing rotating shaft for axle center clickwise by main wing from slip ring of shipping and reselling on another market.
in preceding method, when described pressurized strut pulls main wing along arc main wing chute upward sliding on flap-track, main wing with the main wing of its front end from shipping and reselling on another market as the rotation of axis conter clockwise.
in preceding method, when described main wing is along arc main wing chute upward sliding on flap-track, the main wing of main wing nose slides left in slip ring of shipping and reselling on another market from the main wing of shipping and reselling on another market in the sub-wing, from slip ring of shipping and reselling on another market, upward pressure is applied to main wing simultaneously, force the sub-wing with sub-wing rotating shaft for axle center left-hand revolution by main wing from slip ring of shipping and reselling on another market.
owing to have employed technique scheme, the present invention compared with prior art, the present invention is mainly for the control of thin airfoil wing airplane trailing edge slat, the wing of existing aircraft is thicker, if the control structure of thick wing airplane is directly used in thin airfoil wing airplane to incite somebody to action inevitably the larger fairing of aerofoil layout under the wings of an airplane, have a strong impact on aeroperformance, offset the aerodynamic advantages of trailing edge slat.The present invention achieves the interlock of main wing and the sub-wing in trailing edge slat by a pressurized strut, and whole mechanism can be hidden in the wing of trailing edge slat completely, ensure that the fairing of whole trailing edge slat profile thus improves the aerodynamic characteristic of trailing edge slat.Improve the aeroperformance of thin airfoil wing airplane trailing edge slat.
Accompanying drawing explanation
fig. 1 is structural representation of the present invention;
fig. 2 is the schematic diagram of trailing edge slat when packing up;
fig. 3 is the schematic diagram of trailing edge slat when putting down.
being labeled as in figure: 1-main wing, the 2-wing, 3-flap-track, the rotating shaft of the 4-wing, 5-main wing is from shipping and reselling on another market slip ring, and 6-main wing is from shipping and reselling on another market, and 7-arc main wing chute, 8-drives auricle, 9-pressurized strut, 10-wing.
Detailed description of the invention
below in conjunction with drawings and Examples, the present invention is described in further detail, but not as any limitation of the invention.
the structure of a kind of thin airfoil aircraft trailing edge slat of the present invention is, as shown in Figure 1, the trailing edge slat of the structure of this thin airfoil aircraft trailing edge slat comprises main wing 1 and the sub-wing 2 to the structural representation of this structure; Trailing edge slat both sides be provided with symmetrical flap-track 3(in order to see trailing edge slat clearly constructional drawing in only drawn the flap-track 3 in right side), two pieces of flap-tracks 3 are provided with sub-wing shaft hole, and sub-wing rotating shaft 4 is rotationally connected through sub-wing shaft hole and the two pieces of sub-wing 2 front ends; Being provided with main wing in the sub-wing 2 to ship and resell on another market slip ring 5, from shipping and reselling on another market through main wing 6 to slide from slip ring 5 of shipping and reselling on another market with main wing and is rotationally connected in main wing 1 front end; Arc main wing chute 7 sliding block joint of main wing on ship and resell on another market 6 two ends and flap-track 3; Main wing 1 front end is positioned at the two pieces of sub-wing 2 gaping of joints places and is provided with driving auricle 8, and drive the expansion link in auricle 8 and the pressurized strut 9 between two pieces of sub-wings 2 hinged, cylindrical shell and the wing 10 of pressurized strut 9 are hinged.
of the present invention a kind of interlock method for said structure is, as Figure 1-3, the method is slided along the arc main wing chute 7 on flap-track 3 by the pressurized strut 9 push-and-pull main wing 1 be located between the two cross-talk wings 2; In main wing 1 sliding process, the mover wing 2 is with to rotate, to realize interlock main wing 1 and the sub-wing 2 between from the main wing of shipping and reselling on another market in 6 and the sub-wing 2 from slip ring 5 of shipping and reselling on another market by the main wing of main wing 1 front end.When pressurized strut 9 promotes main wing 1 along arc main wing chute 7 slide downward on flap-track 3, main wing 1 with the main wing of its front end from shipping and reselling on another market 6 for axis both clockwise rotation.When main wing 1 is along arc main wing chute 7 slide downward on flap-track 3, the main wing of main wing 1 front end slides to the right in slip ring 5 of shipping and reselling on another market from 6 main wings in the sub-wing 1 of shipping and reselling on another market, from slip ring 5 of shipping and reselling on another market, downward pressure is applied to main wing simultaneously, force the sub-wing 2 with sub-wing rotating shaft 4 for axle center clickwise by main wing from slip ring 5 of shipping and reselling on another market.When pressurized strut 9 pulls main wing 1 along arc main wing chute 7 upward sliding on flap-track 3, main wing 1 with the main wing of its front end from shipping and reselling on another market 6 for the rotation of axis conter clockwise.When main wing 1 is along arc main wing chute 7 upward sliding on flap-track 3, the main wing of main wing 1 front end slides left in slip ring 5 of shipping and reselling on another market from 6 main wings in the sub-wing 1 of shipping and reselling on another market, from slip ring 5 of shipping and reselling on another market, upward pressure is applied to main wing simultaneously, force the sub-wing 2 with sub-wing rotating shaft 4 for axle center left-hand revolution by main wing from slip ring 5 of shipping and reselling on another market.Complete packing up of trailing edge slat, Fig. 3 is the schematic diagram of trailing edge slat collapsed state.
Claims (6)
1. a structure for thin airfoil aircraft trailing edge slat, trailing edge slat comprises main wing (1) and the sub-wing (2); It is characterized in that: be provided with symmetrical flap-track (3) in trailing edge slat both sides, two pieces of flap-tracks (3) are provided with sub-wing shaft hole, and sub-wing rotating shaft (4) is rotationally connected through sub-wing shaft hole and the two pieces of sub-wing (2) front ends; Being provided with main wing in the sub-wing (2) to ship and resell on another market slip ring (5), to slide from slip ring (5) of shipping and reselling on another market from ship and resell on another market (6) and main wing through main wing and is rotationally connected in main wing (1) front end; Arc main wing chute (7) sliding block joint of main wing on ship and resell on another market (6) two ends and flap-track (3); Main wing (1) front end is positioned at the two pieces of sub-wing (2) gaping of joints places and is provided with and drives auricle (8), and drive auricle (8) and be positioned between two pieces of sub-wings (2) the expansion link in pressurized strut (9) hinged, cylindrical shell and the wing (10) of pressurized strut (9) are hinged.
2. for an interlock method for structure described in claim 1, it is characterized in that: the method is by being located at pressurized strut push-and-pull main wing between the two cross-talk wings along the arc main wing slide on flap-track; In main wing sliding process, certainly ship and resell on another market with the main wing in the sub-wing from slip ring band mover wing rotation of shipping and reselling on another market, to realize the interlock between main wing and the sub-wing by the main wing of main wing nose.
3. interlock method according to claim 2, is characterized in that: when described pressurized strut promotes main wing along arc main wing chute slide downward on flap-track, main wing with the main wing of its front end from shipping and reselling on another market as axis both clockwise rotation.
4. interlock method according to claim 3, it is characterized in that: when described main wing is along arc main wing chute slide downward on flap-track, the main wing of main wing nose slides to the right in slip ring of shipping and reselling on another market from the main wing of shipping and reselling on another market in the sub-wing, from slip ring of shipping and reselling on another market, downward pressure is applied to main wing simultaneously, force the sub-wing with sub-wing rotating shaft for axle center clickwise by main wing from slip ring of shipping and reselling on another market.
5. interlock method according to claim 2, is characterized in that: when described pressurized strut pulls main wing along arc main wing chute upward sliding on flap-track, main wing with the main wing of its front end from shipping and reselling on another market as the rotation of axis conter clockwise.
6. interlock method according to claim 5, it is characterized in that: when described main wing is along arc main wing chute upward sliding on flap-track, the main wing of main wing nose slides left in slip ring of shipping and reselling on another market from the main wing of shipping and reselling on another market in the sub-wing, from slip ring of shipping and reselling on another market, upward pressure is applied to main wing simultaneously, force the sub-wing with sub-wing rotating shaft for axle center left-hand revolution by main wing from slip ring of shipping and reselling on another market.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410316272.2A CN104691740A (en) | 2014-07-04 | 2014-07-04 | Structure for trailing edge slat of thin-airfoil-profile aircraft and linkage method of structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410316272.2A CN104691740A (en) | 2014-07-04 | 2014-07-04 | Structure for trailing edge slat of thin-airfoil-profile aircraft and linkage method of structure |
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| CN104691740A true CN104691740A (en) | 2015-06-10 |
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| CN201410316272.2A Pending CN104691740A (en) | 2014-07-04 | 2014-07-04 | Structure for trailing edge slat of thin-airfoil-profile aircraft and linkage method of structure |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107585305A (en) * | 2017-10-10 | 2018-01-16 | 王根英 | A kind of light and handy unmanned plane |
| CN109018300A (en) * | 2018-08-16 | 2018-12-18 | 晨龙飞机（荆门）有限公司 | A kind of slat on adjustable aircraft wing |
| CN110775251A (en) * | 2019-12-12 | 2020-02-11 | 贵州贵航飞机设计研究所 | Method for maintaining moving gap between movable wing surface and fixed wing surface of wing |
| CN110861767A (en) * | 2019-12-13 | 2020-03-06 | 贵州贵航飞机设计研究所 | Method for combined driving of wing high-lift device |
| US11214354B2 (en) | 2018-04-27 | 2022-01-04 | Airbus Sas | Control surface actuation mechanism |
| CN114084340A (en) * | 2021-12-02 | 2022-02-25 | 成都市鸿侠科技有限责任公司 | Airplane flap slide rail structure with uniformly stressed slide rail and processing method thereof |
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| CN101959754A (en) * | 2007-08-06 | 2011-01-26 | 空中客车营运有限公司 | High lift system for an aircraft |
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| US6454219B1 (en) * | 2000-12-04 | 2002-09-24 | Rohr, Inc. | Aircraft wing and method for reducing airframe-generated noise |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107585305A (en) * | 2017-10-10 | 2018-01-16 | 王根英 | A kind of light and handy unmanned plane |
| US11214354B2 (en) | 2018-04-27 | 2022-01-04 | Airbus Sas | Control surface actuation mechanism |
| CN109018300A (en) * | 2018-08-16 | 2018-12-18 | 晨龙飞机（荆门）有限公司 | A kind of slat on adjustable aircraft wing |
| CN109018300B (en) * | 2018-08-16 | 2020-02-04 | 晨龙飞机（荆门）有限公司 | Adjustable wing slat on aircraft wing |
| CN110775251A (en) * | 2019-12-12 | 2020-02-11 | 贵州贵航飞机设计研究所 | Method for maintaining moving gap between movable wing surface and fixed wing surface of wing |
| CN110775251B (en) * | 2019-12-12 | 2023-12-08 | 中航贵州飞机有限责任公司 | Method for maintaining movement gap between movable airfoil surface and fixed airfoil surface of wing |
| CN110861767A (en) * | 2019-12-13 | 2020-03-06 | 贵州贵航飞机设计研究所 | Method for combined driving of wing high-lift device |
| CN114084340A (en) * | 2021-12-02 | 2022-02-25 | 成都市鸿侠科技有限责任公司 | Airplane flap slide rail structure with uniformly stressed slide rail and processing method thereof |
| CN114084340B (en) * | 2021-12-02 | 2023-07-21 | 成都市鸿侠科技有限责任公司 | Airplane flap sliding rail structure with even sliding rail stress and processing method thereof |
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Application publication date: 20150610 |