CN110775251B - Method for maintaining movement gap between movable airfoil surface and fixed airfoil surface of wing - Google Patents
Method for maintaining movement gap between movable airfoil surface and fixed airfoil surface of wing Download PDFInfo
- Publication number
- CN110775251B CN110775251B CN201911270694.XA CN201911270694A CN110775251B CN 110775251 B CN110775251 B CN 110775251B CN 201911270694 A CN201911270694 A CN 201911270694A CN 110775251 B CN110775251 B CN 110775251B
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- airfoil
- support arm
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- sliding
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 230000009471 action Effects 0.000 claims abstract description 9
- 230000003993 interaction Effects 0.000 claims abstract description 9
- 230000008569 process Effects 0.000 claims description 5
- 238000005096 rolling process Methods 0.000 claims description 3
- 230000006872 improvement Effects 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
The invention discloses a method for maintaining a motion gap between a movable airfoil surface and a fixed airfoil surface of a wing, which comprises the following steps: a support arm is additionally arranged at the position with the maximum disturbance degree under the aerodynamic force action of the movable airfoil; correspondingly, a sliding surface in sliding fit with the support arm is added at the fixed airfoil surface; according to the invention, through the interaction of the sliding contact of the support arm and the sliding surface, the disturbance degree of the movable airfoil is restrained by means of the structural rigidity of the fixed airfoil, and meanwhile, the movement gap between the movable airfoil and the fixed airfoil is maintained, so that the smooth retraction of the movable airfoil is ensured; after the support arm is contacted with the sliding surface, the abundant strength and rigidity of the fixed airfoil surface structure are utilized to share aerodynamic force born by the movable airfoil surface through the interaction force of the support arm and the sliding surface, so that the comprehensive efficiency of the structure is improved; meanwhile, the structural strength and rigidity of the movable airfoil are not required to be enhanced and improved, the disturbance degree of the movable airfoil is restrained through the interaction of the support arm and the sliding surface, and the situation that the structural utilization rate is reduced due to the weight increase caused by the structural enhancement and improvement of the movable airfoil can be avoided.
Description
Technical Field
The invention belongs to the technical field of aircraft structural design and repair, and particularly relates to a method for maintaining a moving gap between a movable airfoil surface and a fixed airfoil surface of an airfoil.
Background
The movable wing surface is positioned in the fixed wing surface, the two ends of the movable wing surface are suspended on the fixed wing surface by guide rails, the guide rails of the movable wing surface rotate under the drive of the control system, the middle part of the movable wing surface generates larger disturbance degree under the action of aerodynamic force in flight, and the movable wing surface is larger than the movement gap between the movable wing surface and the fixed wing surface, so that the movable wing surface and the fixed wing surface generate interference, rub-touch and other unsmooth retraction conditions. Because of the restrictions of overall layout, pneumatic design and the like, the span of the movable airfoil is large, the height of the airfoil is low, the structural design needs to pay more weight to ensure the strength and rigidity, and the structural efficiency is low.
Disclosure of Invention
In order to solve the problems, the invention aims to provide a method for maintaining the movement gap between a movable airfoil surface and a fixed airfoil surface of a wing, by which the movement gap between the movable airfoil surface and the fixed airfoil surface under the disturbance degree generated by the aerodynamic force in the movement process of the movable airfoil surface can be effectively maintained, and the smooth retraction and extension of the movable airfoil surface is ensured. The specific technical scheme is as follows:
a method of maintaining a moving gap between a moving airfoil and a stationary airfoil of a wing, comprising the steps of: a support arm is additionally arranged at the position with the maximum disturbance degree under the aerodynamic force action of the movable airfoil; correspondingly, a sliding surface in sliding fit with the support arm is added at the fixed airfoil surface; through the interaction of the sliding contact of the support arm and the sliding surface, the disturbance degree of the movable airfoil surface is restrained by the structural rigidity of the fixed airfoil surface, and meanwhile, the movement gap between the movable airfoil surface and the fixed airfoil surface is maintained.
Further, the support arm is fixedly connected to the movable wing surface and moves along with the movable wing surface, and the movement profile surface of the support arm is higher than the highest movement profile surface of the movable wing surface.
Further, the sliding surface is fixed on the fixed airfoil surface and covers a movement profile area of the support arm during the movement process of the follow-up airfoil surface.
Further, after the movable wing surface generates upward deflection under the action of pneumatic load, the support arm is contacted with the sliding surface and can slide on the sliding surface.
Further, the contact mode between the support arm and the sliding surface is sliding contact or rolling contact.
The invention has the beneficial effects that:
the invention can effectively maintain the movement gap between the fixed airfoil surface and the movable airfoil surface under the disturbance degree generated by the aerodynamic force action in the movement process of the movable airfoil surface, and ensure the smooth retraction of the movable airfoil surface; after the support arm is contacted with the sliding surface, the abundant strength and rigidity of the fixed airfoil structure are utilized to share the aerodynamic force born by the movable airfoil (namely, the strength and rigidity of the fixed airfoil structure are used for compensation) through the interaction force of the support arm and the sliding surface, so that the comprehensive utilization of the structure is realized, and the comprehensive efficiency of the structure is improved; meanwhile, the structural strength and rigidity of the movable airfoil are not required to be enhanced and improved, the disturbance degree of the movable airfoil is restrained through the interaction of the support arm and the sliding surface, and the situation that the structural utilization rate is reduced due to the weight increase caused by the structural enhancement and improvement of the movable airfoil can be avoided.
Drawings
The invention is described in further detail below with reference to the accompanying drawings.
FIG. 1 is a schematic diagram of the present invention (with the moving airfoil in a lowered state or during deployment);
FIG. 2 is a schematic view of the movable airfoil in a stowed condition
The figure shows: 1-fixed airfoil surface, 2-sliding surface, 3-support arm and 4-movable airfoil surface.
Detailed Description
The principles and features of the present invention are described below with reference to the drawings and examples, which are provided for illustration only and are not intended to limit the scope of the invention.
Examples:
as shown in FIG. 1, the method for maintaining the motion clearance between the movable airfoil surface and the fixed airfoil surface of the wing comprises the following steps: the support arm 3 is additionally arranged at the position with the maximum disturbance degree under the aerodynamic force action of the movable airfoil 4; correspondingly, a sliding surface 2 which is in sliding fit with the support arm 3 is added at the fixed airfoil surface 1; by the interaction of the arm 3 in sliding contact with the sliding surface 2, the deflection of the braking airfoil 4 is suppressed by means of the structural rigidity of the stationary airfoil 1, while the movement gap between the braking airfoil 4 and the stationary airfoil 1 is maintained. The support arm 3 is fixedly connected to the movable wing surface 4 and moves along with the movable wing surface 4, and the movement profile surface of the support arm 3 is higher than the highest movement profile surface of the movable wing surface 4. The sliding surface 2 is fixed on the fixed airfoil surface 1 and covers the movement contour area of the support arm 3 during the movement of the following airfoil surface 4. After the dynamic airfoil 4 is subjected to an aerodynamic load to generate an upward deflection, the arm 3 is in contact with the sliding surface 2 and is able to slide thereon (on the sliding surface). The contact mode between the support arm 3 and the sliding surface 2 is sliding contact or rolling contact.
As shown in fig. 1, when the movable wing surface 4 is in use, i.e. in a put-down state or in a retraction process, the movable wing surface 4 generates disturbance under the aerodynamic force action, drives the support arm 3 to contact with the sliding surface 2 on the fixed wing surface 1 and can slide, the disturbance of the movable wing surface can be restrained through the interaction of the support arm 3 and the sliding surface 2, meanwhile, a movement gap between the movable wing surface 4 and the fixed wing surface 1 is maintained, and the retraction of the movable wing surface is ensured to be smooth. And can avoid the occurrence of weight increase and structure utilization reduction caused by the structural reinforcement improvement of the movable airfoil 4.
As shown in fig. 2, the movable wing surface 4 and the support arm 3 are in the retracted state, and the support arm 3 is not in contact with the sliding surface 2 on the fixed wing surface 1.
The protection scope of the present invention is not limited to the technical solutions disclosed in the specific embodiments, and any modification, equivalent replacement, improvement, etc. made to the above embodiments according to the technical substance of the present invention falls within the protection scope of the present invention.
Claims (5)
1. A method of maintaining a moving gap between a moving airfoil and a stationary airfoil of a wing, comprising the steps of: a support arm (3) is additionally arranged at the position with the maximum disturbance degree under the aerodynamic force action of the movable airfoil surface (4); correspondingly, a sliding surface (2) which is in sliding fit with the support arm (3) is added at the fixed airfoil surface (1); by the interaction of the support arm (3) and the sliding surface (2) in sliding contact, the disturbance degree of the movable wing surface (4) is restrained by the structural rigidity of the fixed wing surface (1), and meanwhile, the movement gap between the movable wing surface (4) and the fixed wing surface (1) is maintained.
2. The method of maintaining a moving airfoil to stationary airfoil gap as set forth in claim 1 wherein: the support arm (3) is fixedly connected to the movable wing surface (4) and moves along with the movable wing surface (4), and the movement profile surface of the support arm (3) is higher than the highest movement profile surface of the movable wing surface (4).
3. The method of maintaining a moving airfoil to stationary airfoil gap as set forth in claim 2 wherein: the sliding surface (2) is fixed on the fixed wing surface (1) and covers a movement contour area of the support arm (3) in the movement process of the following moving wing surface (4).
4. A method of maintaining a moving airfoil to stationary airfoil gap as claimed in any one of claims 1 to 3 in which: after the dynamic wing surface (4) generates upward disturbance under the action of pneumatic load, the support arm (3) is contacted with the sliding surface (2) and can slide on the sliding surface.
5. The method of maintaining a moving airfoil to stationary airfoil movement gap of a wing according to claim 4, wherein: the contact mode between the support arm (3) and the sliding surface (2) is sliding contact or rolling contact.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911270694.XA CN110775251B (en) | 2019-12-12 | 2019-12-12 | Method for maintaining movement gap between movable airfoil surface and fixed airfoil surface of wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911270694.XA CN110775251B (en) | 2019-12-12 | 2019-12-12 | Method for maintaining movement gap between movable airfoil surface and fixed airfoil surface of wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110775251A CN110775251A (en) | 2020-02-11 |
| CN110775251B true CN110775251B (en) | 2023-12-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911270694.XA Active CN110775251B (en) | 2019-12-12 | 2019-12-12 | Method for maintaining movement gap between movable airfoil surface and fixed airfoil surface of wing |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116923686B (en) * | 2023-08-08 | 2024-06-18 | 哈尔滨工业大学 | Expandable airfoil surface deformation front and rear rigidity enhancement device and working method |
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| CN102582825A (en) * | 2012-02-14 | 2012-07-18 | 西北工业大学 | Sealing mechanism for plane wing surfaces |
| CN103097241A (en) * | 2010-05-26 | 2013-05-08 | 空中客车运作有限责任公司 | A device for an adjustable flap of a wing |
| CN104044728A (en) * | 2014-06-23 | 2014-09-17 | 西北工业大学 | Spring type flap sealing mechanism |
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| CN104691740A (en) * | 2014-07-04 | 2015-06-10 | 贵州贵航飞机设计研究所 | Structure for trailing edge slat of thin-airfoil-profile aircraft and linkage method of structure |
| CN105620723A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Flaperon |
| US9688384B1 (en) * | 2012-09-20 | 2017-06-27 | The Boeing Company | Methods and apparatus to control a gap between movable aircraft wing components |
| CN207773431U (en) * | 2018-01-23 | 2018-08-28 | 西安鼎宣机电科技有限公司 | A kind of aerofoil of sealing structure |
| CN109515686A (en) * | 2018-11-07 | 2019-03-26 | 西安航空学院 | A kind of adaptive trail-edge flap mechanism |
| CN109606640A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft flexible trailing edge upper limb surface seal structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US7611099B2 (en) * | 2005-09-07 | 2009-11-03 | The Boeing Company | Seal assemblies for use with drooped spoilers and other control surfaces on aircraft |
| GB201522486D0 (en) * | 2015-12-21 | 2016-02-03 | Airbus Operations Ltd | Seal assembly |
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2019
- 2019-12-12 CN CN201911270694.XA patent/CN110775251B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103097241A (en) * | 2010-05-26 | 2013-05-08 | 空中客车运作有限责任公司 | A device for an adjustable flap of a wing |
| CN102582825A (en) * | 2012-02-14 | 2012-07-18 | 西北工业大学 | Sealing mechanism for plane wing surfaces |
| US9688384B1 (en) * | 2012-09-20 | 2017-06-27 | The Boeing Company | Methods and apparatus to control a gap between movable aircraft wing components |
| CN104044728A (en) * | 2014-06-23 | 2014-09-17 | 西北工业大学 | Spring type flap sealing mechanism |
| CN104691745A (en) * | 2014-07-04 | 2015-06-10 | 贵州贵航飞机设计研究所 | Method and device for completing movement of double slotted flaps by using one actuating cylinder under thin airfoil profile |
| CN104691740A (en) * | 2014-07-04 | 2015-06-10 | 贵州贵航飞机设计研究所 | Structure for trailing edge slat of thin-airfoil-profile aircraft and linkage method of structure |
| CN105620723A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Flaperon |
| CN207773431U (en) * | 2018-01-23 | 2018-08-28 | 西安鼎宣机电科技有限公司 | A kind of aerofoil of sealing structure |
| CN109515686A (en) * | 2018-11-07 | 2019-03-26 | 西安航空学院 | A kind of adaptive trail-edge flap mechanism |
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| Publication number | Publication date |
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| CN110775251A (en) | 2020-02-11 |
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| PB01 | Publication | ||
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| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20230714 Address after: 561000 Anshun economic and Technological Development Zone, Guizhou Applicant after: Guizhou Guifei aircraft design and Research Institute Co.,Ltd. Address before: 561000 Anshun economic and Technological Development Zone, Guizhou Applicant before: GUIZHOU AVIATION AIRCRAFT DESIGN INSTITUTE |
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| CI02 | Correction of invention patent application | ||
| CI02 | Correction of invention patent application |
Correction item: Applicant|Address Correct: GUIZHOU AVIATION AIRCRAFT DESIGN INSTITUTE|561000 Anshun economic and Technological Development Zone, Guizhou False: Guizhou Guifei aircraft design and Research Institute Co.,Ltd.|561000 Anshun economic and Technological Development Zone, Guizhou Number: 30-02 Volume: 39 |
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| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20230918 Address after: 561000 Songqi Town, Anshun economic and Technological Development Zone, Guizhou Province Applicant after: AVIC GUIZHOU AIRPLANE Co.,Ltd. Address before: 561000 Anshun economic and Technological Development Zone, Guizhou Applicant before: GUIZHOU AVIATION AIRCRAFT DESIGN INSTITUTE |
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| GR01 | Patent grant |