CN109533285B - Moving wing surface stopping method - Google Patents
Moving wing surface stopping method Download PDFInfo
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- CN109533285B CN109533285B CN201811318880.1A CN201811318880A CN109533285B CN 109533285 B CN109533285 B CN 109533285B CN 201811318880 A CN201811318880 A CN 201811318880A CN 109533285 B CN109533285 B CN 109533285B
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- stop
- rocker arm
- stopping
- moving
- machine body
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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
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- 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
- Y02T50/40—Weight reduction
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- General Engineering & Computer Science (AREA)
- Computer Hardware Design (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
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- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Drilling And Exploitation, And Mining Machines And Methods (AREA)
- Transmission Devices (AREA)
Abstract
The invention belongs to the field of airplane structures, and particularly relates to a moving wing surface stopping method. The method comprises the following steps: the device comprises a machine body mechanism, a control rocker arm, a screw assembly, a stop block, a stop screw, a stop device and an installation part, wherein the machine body mechanism is used for simulating the motion track of the control rocker arm, the stop screw assembly is arranged on the machine body mechanism, the stop block is arranged on the control rocker arm, the length and the size of the stop screw are adjusted, the stop effect is verified, and the strength and the rigidity of the stop device and the installation part are optimized and checked. The invention has the advantages and positive effects, such as improvement of performance, reduction of cost and the like. The arrangement position of the stopping device is optimized, the load borne by the stopping device is reduced, and the design weight is reduced. The stop angle of the moving wing surface can be adjusted by the length of the stop screw protruding out of the machine body, and the stop angle error caused by assembly is eliminated. The reverse stopping reduces the size of the stop block, improves the rigidity of the operating rocker arm and lightens the weight of the operating rocker arm.
Description
Technical Field
The invention belongs to the field of airplane structures, and particularly relates to a moving wing surface stopping method.
Background
The moving wing surface of the airplane is generally required to be provided with a stopping device to limit the rotating stroke of the moving wing surface to a range capable of safely flying and landing. The stopping device for the elevator of the airplane is characterized in that four stopping blocks are arranged on an elevator joint, when the elevator rotates clockwise to a limited angle, two stopping blocks below the elevator joint are in contact with support arms at positions corresponding to the rear edge of a horizontal stabilizing surface, and the clockwise stopping of the elevator is realized. When the elevator rotates anticlockwise to a limited angle, the two stop blocks above the joint of the elevator are contacted with the support arm, so that the stop of the elevator in the anticlockwise direction is realized. After the positions of the four stop gears are set, the actual rotation range of the elevator is fixed, and due to machining and assembling errors, the stop angle and the theoretical stop angle have errors. The stop block is close to the elevator rotating shaft, the load is large during stopping, and the requirements on the strength and rigidity of the stop block, the joint and the support arm are high.
Disclosure of Invention
The problems of large error, non-adjustability and heavy weight of a conventional stop device of the moving wing surface of the airplane are solved.
Two groups of stop screws, an inner nut, an outer nut and an operating rocker arm with a stop dog are respectively arranged at two sides of the machine body fixing structure. Loosening the nut arranged on the outer side of the machine body, then screwing the screw forward or reversely to complete the adjustment of the protruding length of the screw relative to the machine body, and finally screwing the nut on the outer side of the machine body to prevent the screw from loosening. The adjustment of the stop angle of the moving airfoil surface is realized by adjusting the length of the bolt protruding out of the machine body. Two stopping blocks are respectively arranged on two sides of the operating rocker arm, and the positions of the stopping blocks are set by simulating the rotation condition of the moving wing surface through CAD software. When the moving wing surface rotates clockwise to a limited angle, the stop device at the anticlockwise position acts; the stop means in the clockwise position is active when the moving airfoil is turned anticlockwise to a defined angle.
Technical scheme
A method of stopping a moving airfoil comprising the steps of:
1 simulating the motion trail of the control rocker arm. And simulating the rotation process of the moving airfoil surface according to the limit rotation angle of the moving airfoil surface through CAD software, and drawing a motion envelope body of the control rocker arm.
2, a screw component is arranged on the machine body mechanism. A stop screw assembly is arranged on the machine body fixing structure at the position adjacent to the operating rocker arm and at the position closest to the motion envelope body of the operating rocker arm.
3, a stop block is arranged on the operating rocker arm. One side of the designed stop block is contacted with the stop screw, and the other side of the designed stop block is connected with the rocker arm deflected to the limit position into a whole.
4 adjusting the length of the stop screw and the size of the stop block. The length of the stop screw can be adjusted according to actual requirements so as to adjust the length of the stop block.
5 verifying the stopping effect. And simulating the rotation process of the moving wing surface according to the limit rotation angle of the moving wing surface through CAD software, and checking the effect of the stop device.
And 6, optimizing and checking the strength and rigidity of the stop device and the mounting part. Optimizing the stop block, operating the rocker arm and stopping the strength and rigidity, and checking the strength and rigidity of the stop screw assembly and the installation machine body part.
The length of the stop screw is at least 2mm, and the stop screw is threaded and protrudes out of the external nut, so that the stop angle can be adjusted after the moving wing surface is installed on the machine body.
Technical effects
The invention has the advantages and positive effects, such as improvement of performance, reduction of cost and the like. The arrangement position of the stopping device is optimized, the load borne by the stopping device is reduced, and the design weight is reduced. The stop angle of the moving wing surface can be adjusted by the length of the stop screw protruding out of the machine body, and the stop angle error caused by assembly is eliminated. The reverse stopping reduces the size of the stop block, improves the rigidity of the operating rocker arm and lightens the weight of the operating rocker arm.
Drawings
FIG. 1 is a schematic illustration (elevation view) of a conventional aircraft motion wing surface stop
FIG. 2 is a schematic illustration of a conventional aircraft motion wing stop (top view)
FIG. 3 is a schematic view of the rudder stop of the eagle-700 aircraft
FIG. 4 is a flow chart of the present immobilization method
Detailed Description
In fig. 3, the eagle-700 airplane rudder control rocker arm is provided with stop blocks, stop screws are correspondingly arranged on two sides of a frame of a fuselage, and the stop screws are fasteners for connecting the fuselage skin and the frame. The rotation angle of the rudder of the eagle-700 airplane is +/-20 degrees.
A method of stopping a moving airfoil comprising the steps of:
1 simulating the motion trail of the control rocker arm. And simulating the rotation process of the moving airfoil surface according to the limit rotation angle of the moving airfoil surface through CAD software, and drawing a motion envelope body of the control rocker arm.
2, a screw component is arranged on the machine body mechanism. A stop screw assembly is arranged on the machine body fixing structure at the position adjacent to the operating rocker arm and at the position closest to the motion envelope body of the operating rocker arm.
3, a stop block is arranged on the operating rocker arm. One side of the designed stop block is contacted with the stop screw, and the other side of the designed stop block is connected with the rocker arm deflected to the limit position into a whole.
4 adjusting the length of the stop screw and the size of the stop block. The length of the stop screw can be adjusted according to actual requirements so as to adjust the length of the stop block.
5 verifying the stopping effect. And simulating the rotation process of the moving wing surface according to the limit rotation angle of the moving wing surface through CAD software, and checking the effect of the stop device.
And 6, optimizing and checking the strength and rigidity of the stop device and the mounting part. Optimizing the stop block, operating the rocker arm and stopping the strength and rigidity, and checking the strength and rigidity of the stop screw assembly and the installation machine body part.
The length of the stop screw is at least 2mm, and the stop screw is threaded and protrudes out of the external nut, so that the stop angle can be adjusted after the moving wing surface is installed on the machine body.
Claims (2)
1. A method of stopping a moving airfoil, comprising the steps of:
1) simulating the motion trail of the control rocker arm: simulating the rotation process of the moving airfoil surface according to the limit rotation angle of the moving airfoil surface through CAD software, and drawing a motion envelope body of the control rocker arm;
2) set up stop screw subassembly on the organism mechanism: a stop screw component is arranged on the machine body fixing structure at the position close to the operating rocker arm and at the position closest to the motion envelope body of the operating rocker arm;
3) a stop block is arranged on the operating rocker arm: one side of the designed stop block is contacted with the stop screw, and the other side of the designed stop block is connected with the rocker arm deflected to the limit position into a whole;
4) adjusting the length of the stop screw and the size of the stop: according to actual requirements, the length of the stop screw is adjusted so as to adjust the length of the stop block;
5) and (3) verifying the stopping effect: and simulating the rotation process of the moving wing surface according to the limit rotation angle of the moving wing surface through CAD software, and checking the effect of the stop device.
2. A method for stopping a moving airfoil according to claim 1, wherein the stop screw has a length of at least 2mm and is threaded through an external nut to allow adjustment of the stop angle after the moving airfoil is mounted to the body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811318880.1A CN109533285B (en) | 2018-11-07 | 2018-11-07 | Moving wing surface stopping method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811318880.1A CN109533285B (en) | 2018-11-07 | 2018-11-07 | Moving wing surface stopping method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109533285A CN109533285A (en) | 2019-03-29 |
| CN109533285B true CN109533285B (en) | 2022-03-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811318880.1A Active CN109533285B (en) | 2018-11-07 | 2018-11-07 | Moving wing surface stopping method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109533285B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111191325B (en) * | 2019-12-24 | 2023-06-23 | 中国航空工业集团公司西安飞机设计研究所 | SysML-based airplane direct mission preparation modeling method |
| CN111122109A (en) * | 2020-01-16 | 2020-05-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind-tunnel aircraft model aileron angle adjusting device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2131562A1 (en) * | 1970-06-27 | 1972-01-13 | Pearce Terry Kenneth | Boat rudder |
| US5645250A (en) * | 1993-08-26 | 1997-07-08 | Gevers; David E. | Multi-purpose aircraft |
| CN202593853U (en) * | 2012-03-09 | 2012-12-12 | 陕西飞机工业（集团）有限公司 | Novel control surface control device |
| CN202863757U (en) * | 2012-07-13 | 2013-04-10 | 哈尔滨飞机工业集团有限责任公司 | Rudder surface stopper device of rudder |
| CN203567927U (en) * | 2013-09-26 | 2014-04-30 | 西安庆安电气控制有限责任公司 | Adjustable limit device of fan-shaped wheel at terminal of flexible control system |
| CN107097935A (en) * | 2017-04-18 | 2017-08-29 | 河北天启通宇航空器材科技发展有限公司 | Rudder angle position governor motion and aircraft |
-
2018
- 2018-11-07 CN CN201811318880.1A patent/CN109533285B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2131562A1 (en) * | 1970-06-27 | 1972-01-13 | Pearce Terry Kenneth | Boat rudder |
| US5645250A (en) * | 1993-08-26 | 1997-07-08 | Gevers; David E. | Multi-purpose aircraft |
| CN202593853U (en) * | 2012-03-09 | 2012-12-12 | 陕西飞机工业（集团）有限公司 | Novel control surface control device |
| CN202863757U (en) * | 2012-07-13 | 2013-04-10 | 哈尔滨飞机工业集团有限责任公司 | Rudder surface stopper device of rudder |
| CN203567927U (en) * | 2013-09-26 | 2014-04-30 | 西安庆安电气控制有限责任公司 | Adjustable limit device of fan-shaped wheel at terminal of flexible control system |
| CN107097935A (en) * | 2017-04-18 | 2017-08-29 | 河北天启通宇航空器材科技发展有限公司 | Rudder angle position governor motion and aircraft |
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| Publication number | Publication date |
|---|---|
| CN109533285A (en) | 2019-03-29 |
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