CN112455654A - Method for limiting movable wing surface of airplane in folding position - Google Patents
Method for limiting movable wing surface of airplane in folding position Download PDFInfo
- Publication number
- CN112455654A CN112455654A CN202011275587.9A CN202011275587A CN112455654A CN 112455654 A CN112455654 A CN 112455654A CN 202011275587 A CN202011275587 A CN 202011275587A CN 112455654 A CN112455654 A CN 112455654A
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- wing surface
- movable wing
- movable
- gasket
- screw rod
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- 238000000034 method Methods 0.000 title claims abstract description 38
- 238000005452 bending Methods 0.000 claims description 3
- 230000003247 decreasing effect Effects 0.000 claims description 3
- 238000001125 extrusion Methods 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 238000009434 installation Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 238000009825 accumulation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
Abstract
The invention discloses a limiting method for a movable wing surface of an airplane at a take-up position, which is characterized in that the limiting method is implemented between the movable wing surface and a fixed wing surface through a limiting device, the limiting device comprises a support, a screw rod and a gasket, and the specific limiting method is implemented by controlling the extending amount of the screw rod relative to the support through adjusting the thickness of the gasket; when the movable wing surface is in the folding position, interference magnitude is formed between the end part of the screw rod and the movable wing surface, the requirement that the movable wing surface is in the folding position can be met, and the movable clearance between the movable wing surface and the movable wing surface can be eliminated. The limiting method can not only ensure the requirement of the movable wing surface folding position, but also eliminate the movable gap, has the advantages of convenient and simple operation, easy implementation, safety and practicality, can improve the production efficiency and reduce the labor capacity, and is suitable for popularization and use.
Description
Technical Field
The invention relates to the technical field of airplane structure design, in particular to a limiting method of a movable wing surface of an airplane at a folding position.
Background
The movable wing surface refers to a wing surface which can be controlled by operation or follow-up control on the wings and the tail wing of the airplane, and the aerodynamic force can be changed by controlling the movable wing surface in the flying process of the airplane so as to adapt to the flying requirement of the current flying environment. The movable wing surface comprises airfoil surface types such as an elevator (full-motion horizontal tail), an aileron, a rudder, a leading edge slat, a flap and a spoiler. The movable wing surface is also called as a movable control surface, a plurality of movable control surfaces are arranged on the airplane, and some movable control surfaces are arranged at two positions of folding and putting down and need to be limited at the folding position. Due to the accumulation of part manufacturing and component assembly errors, the clearance between the movable control surface and the limiting device is too large or the interference between the movable control surface and the limiting device is too large when the movable control surface is in the retracted position. The phenomenon that the movable control surface is not in place when the movable control surface is folded due to excessive interference with the limiting device is caused; and the clearance with the limiting device is too large, and the vibration problem is easy to generate. In order to eliminate or reduce the influence to an acceptable range as much as possible, the problems caused by interference or clearance are usually accomplished through repeated measurement, adjustment and installation, and the like, thereby causing the problems of large work repetition and low work efficiency.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a limiting method which is simple to operate aiming at the problems in the background technology, so as to solve the problems that the clearance between a movable control surface and a fixed structure is often too large when the movable control surface is at a folding position or the movable control surface is not folded in place due to too large interference with the fixed structure, repeated measurement is carried out, the work repetition amount such as adjustment and installation is large, and the efficiency is low; the limiting method provided by the invention can ensure the requirement of the movable wing surface folding position and eliminate the movable clearance, is convenient and simple to operate and easy to implement, can improve the production efficiency and reduce the labor capacity, and particularly relates to the limiting method of the movable wing surface of the airplane in the folding position.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows: a limit method for an airplane movable wing surface at a folding position is characterized in that the limit is carried out between the movable wing surface and a fixed wing surface through a limit device, the limit device comprises a support, a screw rod and a gasket, a threaded through hole matched with the screw rod is arranged in the support, a spherical contact part is arranged at the end part of the screw rod, the support is fixedly connected to the fixed wing surface, and the screw rod penetrates through the gasket and the threaded through hole in the support and is in contact connection with the movable wing surface through the contact part; the specific limiting method is that the extending amount of the screw relative to the support is controlled by adjusting the thickness of the gasket; when the movable wing surface is in the folding position, interference magnitude is formed between the end part of the screw rod and the movable wing surface, the requirement that the movable wing surface is in the folding position can be met, and the movable clearance between the movable wing surface and the movable wing surface can be eliminated.
Further, the method for limiting the movable wing surface of the airplane in the retracted position is characterized in that the movable wing surface can only exist in two positions, namely the retracted position and the put-down position, relative to the fixed wing surface, and when the movable wing surface deflects from the put-down position to the retracted position or resets from the retracted position to the put-down position, the movable wing surface can only move or rotate in the same direction.
Further, the invention relates to a limit method for the movable wing surface of an airplane at the folding position, wherein when the end part of the screw rod and the movable wing surface are at the folding position and interference is generated, and the movable wing surface does not reach the folding position, the thickness of the gasket is adjusted to be adjusted towards a small direction by adjusting the thickness of the gasket, so that the protruding amount of the screw rod relative to the support is reduced to eliminate the interference, and the movable wing surface can reach the folding position.
Further, the invention relates to a limit method for the movable wing surface of the airplane at the folding position, wherein when a larger gap exists between the end part of the screw rod and the movable wing surface at the folding position, the thickness of the gasket is adjusted to be adjusted towards the larger direction by adjusting the thickness of the gasket, so that the extending amount of the screw rod relative to the support is increased, and the movable gap between the screw rod and the movable wing surface is eliminated.
The method for limiting the movable wing surface of the airplane at the take-up position comprises the steps that the thickness of the gasket is adjusted, the screw can be tightly connected with the support through the thread through hole in the support, the movable wing surface on the end of the screw acts, the generated axial load or tangential load can be correspondingly extruded by the gasket, and the bending load on the screw and the axial load on the part, connected with the support, of the thread are reduced through the gasket.
Further, the method for limiting the movable airfoil surface of the airplane in the retracted position is provided, wherein the thickness of the shim is adjusted by increasing or decreasing the number of shims, that is, the shim is a single shim or a plurality of shims, and the thickness of each shim may be the same or different.
Compared with the prior art, the limit method for the movable wing surface of the airplane at the folding position has the beneficial effects that: because the limiting device is arranged between the movable airfoil surface and the fixed airfoil surface and comprises the support, the screw and the gasket, the extending amount of the screw relative to the support is controlled by adjusting the thickness of the gasket, namely, the phenomenon of overlarge gap or overlarge interference is eliminated by utilizing the extending amount, and the problem that the movable airfoil surface is not folded in place due to overlarge gap or overlarge interference when the movable airfoil surface is folded in place is solved. The limiting method can not only ensure the requirement of the movable wing surface folding position, but also eliminate the movable gap, has the advantages of convenient and simple operation, easy implementation, safety and practicality, can improve the production efficiency and reduce the labor capacity, and is suitable for popularization and use.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings.
Fig. 1 is a schematic structural view of the limiting device of the present invention.
Shown in the figure: 1-support, 2-screw, 3-gasket, 4-movable wing surface and 5-fixed wing surface.
Detailed Description
As shown in fig. 1, the method for limiting the movable airfoil surface of an airplane at the stowing position according to the present invention is that a limiting device is used for limiting between a movable airfoil surface 4 and a fixed airfoil surface 5, the limiting device includes a support 1, a screw 2 and a gasket 3, a threaded through hole matched with the screw 2 is arranged in the support 1, a spherical contact portion is arranged at the end of the screw 2, the support 1 is fixedly connected to the fixed airfoil surface 5, and the screw 2 passes through the gasket 3 and the threaded through hole in the support 1 and is in contact connection with the movable airfoil surface 4 through a contact portion 21; the specific limiting method is that the extending amount of the screw rod 2 relative to the support 1 is controlled by adjusting the thickness of the gasket 3; when the movable wing surface 4 is at the folding position, interference magnitude is formed between the end part of the screw rod 2 and the movable wing surface 4, so that the requirement that the movable wing surface 4 is at the folding position can be met, and the movable gap between the movable wing surface 4 and the movable wing surface can be eliminated.
Further, the method for limiting the movable wing surface of the airplane in the retracted position is characterized in that the movable wing surface 4 can only exist in two positions of the retracted position or the lowered position relative to the fixed wing surface 5, and when the movable wing surface 4 deflects from the lowered position to the retracted position or returns from the retracted position to the lowered position, the movable wing surface 4 can only move or rotate in the same direction.
Further, the invention relates to a limit method for the movable wing surface of an airplane at the take-up position, wherein the end part of the screw rod 2 and the movable wing surface 4 are at the take-up position, interference is generated, when the movable wing surface 4 does not reach the take-up position, the thickness of the gasket 3 is adjusted in a small direction by adjusting the thickness of the gasket 3, so that the protruding amount of the screw rod 2 relative to the support 1 is reduced to eliminate the interference, and the movable wing surface 4 can reach the take-up position.
Further, according to the limiting method for the movable wing surface of the airplane at the folding position, when a larger gap exists between the end of the screw rod 2 and the movable wing surface 4 at the folding position, the thickness of the gasket 3 is adjusted by adjusting the thickness of the gasket 3, so that the extending amount of the screw rod 2 relative to the support 1 is increased, and the movable gap between the screw rod 2 and the movable wing surface 4 is eliminated.
The method for limiting the movable wing surface of the airplane at the take-up position comprises the steps that the thickness of the gasket 3 is adjusted, the screw rod 2 can be fixedly connected with the support 1 through a threaded through hole in the support 1, the movable wing surface 4 on the end of the screw rod 2 acts, the generated axial load or tangential load can be borne by the gasket 3 through the corresponding extrusion force P, and the bending load borne by the screw rod 2 and the axial load borne by the part of threads connected with the support 1 are reduced through the gasket 3.
Further, according to the method for limiting the movable airfoil surface of the aircraft in the stowed position, the thickness of the shims 3 is adjusted by increasing or decreasing the number of the shims 3, that is, the shims 3 are single shims or multiple shims, and the thickness of each shim may be the same or different.
In the actual installation process, due to the accumulation of part manufacturing and component assembly errors, the movable airfoil 4 is often too large in clearance with the fixed airfoil 5 when being folded, or too large in interference with the fixed airfoil 5 to cause that the movable airfoil is not folded in place, in the operation process, repeated measurement and adjustment installation are needed to be carried out, the use requirement can be met, the work repetition is large, and the efficiency is low. By adopting the limiting method for the movable wing surface of the airplane at the folding position, as the limiting device is arranged between the movable wing surface 4 and the fixed wing surface 5, the limiting device comprises the support 1, the screw rod 2 and the gasket 3, the extending amount of the screw rod 2 relative to the support 1 is controlled by adjusting the thickness of the gasket 3, the corresponding interference is counteracted by utilizing the extending amount, namely, the phenomenon of overlarge gap or overlarge interference is eliminated by utilizing the extending amount, and the problem that the movable wing surface 4 is not folded in place due to overlarge gap or overlarge interference at the folding position is avoided.
In conclusion, the limiting method provided by the invention can not only ensure the requirement on the folding position of the movable wing surface, but also eliminate the movable gap, is convenient and simple to operate, easy to implement, safe and practical, can improve the production efficiency and reduce the labor capacity, and is suitable for popularization and use.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art, and any modifications, equivalents, improvements, etc. made by using the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A method for limiting the movable wing surface of an airplane in a folding position is characterized in that: the limiting method comprises the steps that limiting is carried out between a movable wing surface (4) and a fixed wing surface (5) through a limiting device, the limiting device comprises a support (1), a screw rod (2) and a gasket (3), a threaded through hole matched with the screw rod (2) is formed in the support (1), a spherical contact part is arranged at the end part of the screw rod (2), the support (1) is fixedly connected to the fixed wing surface (5), and the screw rod (2) penetrates through the gasket (3) and the threaded through hole in the support (1) and is in contact connection with the movable wing surface (4) through a contact part (21); the specific limiting method is that the extending amount of the screw (2) relative to the support (1) is controlled by adjusting the thickness of the gasket (3); when the movable wing surface (4) is in the retracted position, interference magnitude is formed between the end part of the screw rod (2) and the movable wing surface (4), so that the requirement that the movable wing surface (4) is in the retracted position can be met, and a movable gap between the movable wing surface and the movable wing surface can be eliminated.
2. A method of limiting an aircraft movable aerofoil in a stowed position as claimed in claim 1 wherein: the movable wing surface (4) can only be in a state of being located at a folding position or a laying position relative to the fixed wing surface (5), and when the movable wing surface (4) deflects to the folding position from the laying position or resets to the laying position from the folding position, the movable wing surface (4) can only move or rotate along the same direction.
3. A method of limiting an aircraft movable aerofoil in a stowed position as claimed in claim 1 wherein: when the end part of the screw rod (2) and the movable wing surface (4) are in the retracted position and interference is generated to enable the movable wing surface (4) not to reach the retracted position, the thickness of the gasket (3) is adjusted in a small direction by adjusting the thickness of the gasket (3), so that the interference is eliminated by reducing the extending amount of the screw rod (2) relative to the support (1), and the movable wing surface (4) can reach the retracted position.
4. A method of limiting an aircraft movable aerofoil in a stowed position as claimed in claim 1 wherein: when the end part of the screw rod (2) and the movable wing surface (4) are in the retracted position and have larger clearance, the thickness of the gasket (3) is adjusted in the large direction by adjusting the thickness of the gasket (3), so that the extending amount of the screw rod (2) relative to the support (1) is increased, and the movable clearance between the screw rod (2) and the movable wing surface (4) is eliminated.
5. A method of limiting an aircraft movable aerofoil in a stowed position according to any one of claims 1 to 4 wherein: the thickness of the gasket (3) is adjusted, so that the screw (2) is fixedly connected with the support (1) through a threaded through hole in the support (1), the movable wing surface (4) on the end of the screw (2) acts, the generated axial load or tangential load can bear corresponding extrusion force by the gasket (3), and the bending load on the screw (2) and the axial load on the part of threads connected with the support (1) are reduced by the gasket (3).
6. A method of limiting an aircraft movable aerofoil in a stowed position as claimed in claim 5 wherein: the thickness of the gasket (3) is adjusted by increasing or decreasing the number of the gaskets (3), namely the gasket (3) is a single gasket or a plurality of gaskets, wherein the thickness of each gasket can be the same or different.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011275587.9A CN112455654A (en) | 2020-11-16 | 2020-11-16 | Method for limiting movable wing surface of airplane in folding position |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011275587.9A CN112455654A (en) | 2020-11-16 | 2020-11-16 | Method for limiting movable wing surface of airplane in folding position |
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| Publication Number | Publication Date |
|---|---|
| CN112455654A true CN112455654A (en) | 2021-03-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011275587.9A Pending CN112455654A (en) | 2020-11-16 | 2020-11-16 | Method for limiting movable wing surface of airplane in folding position |
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| Country | Link |
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| CN (1) | CN112455654A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114379769A (en) * | 2022-01-20 | 2022-04-22 | 中国商用飞机有限责任公司 | Slat supporting and limiting device |
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|---|---|---|---|---|
| RU2349498C1 (en) * | 2007-07-04 | 2009-03-20 | Открытое Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Folding aerodynamic surface |
| CN103090730A (en) * | 2011-10-27 | 2013-05-08 | 北京精密机电控制设备研究所 | Electric steering engine locking device |
| CN203732237U (en) * | 2013-12-30 | 2014-07-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Connecting device for folding wing surface folding gap of flutter wind tunnel model |
| CN104089547A (en) * | 2014-06-30 | 2014-10-08 | 中国航天时代电子公司 | Unfolding and locking device for foldable rudder face |
| CN109795617A (en) * | 2019-03-11 | 2019-05-24 | 江南造船(集团)有限责任公司 | The installation and debugging method of limiting device, steering mechanism and steering mechanism |
| 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 |
| US20200189718A1 (en) * | 2018-12-17 | 2020-06-18 | Airbus Operations, S.L. | Aerodynicamic surface for an aircraft |
| CN111380409A (en) * | 2020-03-30 | 2020-07-07 | 航天神舟飞行器有限公司 | Stealthy rudder face mounting structure of all-wing aircraft overall arrangement target drone aircraft |
-
2020
- 2020-11-16 CN CN202011275587.9A patent/CN112455654A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2349498C1 (en) * | 2007-07-04 | 2009-03-20 | Открытое Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Folding aerodynamic surface |
| CN103090730A (en) * | 2011-10-27 | 2013-05-08 | 北京精密机电控制设备研究所 | Electric steering engine locking device |
| CN203732237U (en) * | 2013-12-30 | 2014-07-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Connecting device for folding wing surface folding gap of flutter wind tunnel model |
| CN104089547A (en) * | 2014-06-30 | 2014-10-08 | 中国航天时代电子公司 | Unfolding and locking device for foldable rudder face |
| US20200189718A1 (en) * | 2018-12-17 | 2020-06-18 | Airbus Operations, S.L. | Aerodynicamic surface for an aircraft |
| CN109795617A (en) * | 2019-03-11 | 2019-05-24 | 江南造船(集团)有限责任公司 | The installation and debugging method of limiting device, steering mechanism and steering mechanism |
| 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 |
| CN111380409A (en) * | 2020-03-30 | 2020-07-07 | 航天神舟飞行器有限公司 | Stealthy rudder face mounting structure of all-wing aircraft overall arrangement target drone aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114379769A (en) * | 2022-01-20 | 2022-04-22 | 中国商用飞机有限责任公司 | Slat supporting and limiting device |
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Effective date of registration: 20230627 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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