CN111003156B - Connecting device for airplane flap - Google Patents
Connecting device for airplane flap Download PDFInfo
- Publication number
- CN111003156B CN111003156B CN201911346474.0A CN201911346474A CN111003156B CN 111003156 B CN111003156 B CN 111003156B CN 201911346474 A CN201911346474 A CN 201911346474A CN 111003156 B CN111003156 B CN 111003156B
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- China
- Prior art keywords
- flap
- joint
- suspension
- rocker arm
- lug
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
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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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Axle Suspensions And Sidecars For Cycles (AREA)
- Connection Of Plates (AREA)
Abstract
The application provides a connecting device of aircraft flap, connecting device of aircraft flap includes: flap rocker 1, connection joint 2, suspension rib joint 3, front beam 4, rear beam 5, wherein: the flap rocker arm 1 is of a triangular truss type structure, the flap rocker arm 1 is provided with at least three suspension points, two suspension points arranged at the upper end of the flap rocker arm 1 are connected with a flap lower airfoil, and the suspension points arranged at the lower end of the flap rocker arm 1 are connected with support arms at the rear edge of the wing; the rear lower end of the suspension rib joint 3 is provided with a lug, the suspension rib joint 3 is connected with the front beam 4 relative to the front end of the course, and the suspension rib joint 3 is connected with the rear beam 5 relative to the rear end of the course; the connecting joint 2 is of an L-shaped structure, and lugs are arranged at the lower end of the L shape of the connecting joint 2; the lug of the suspension rib joint 3 is connected with one suspension point arranged at the upper end of the flap rocker arm 1, and the lug of the connection joint 2 is connected with the other suspension point arranged at the upper end of the flap rocker arm 1.
Description
Technical Field
The invention belongs to the technical field of aircraft structural design, and relates to a connecting device for aircraft flaps.
Background
In the structural design of the wing surface, a suspension joint of a flap rocker arm of an airplane is combined with a reinforcing rib, and two single lugs are added below the reinforcing rib to fix the rocker arm, so that the structure is shown in figure 1. The single lug is used as an important suspension joint, the structure is simple, the assembly manufacturability is poor, and due to the existence of part machining tolerance, once the distance or the position between the axes of the two lug holes on the suspension rib and the axes of the two lug holes on the upper end of the rocker arm deviate, the risk of incapability of mounting exists, so that the part is scrapped.
Disclosure of Invention
The invention designs a flap rocker arm and a connecting device thereof. The rocker arm has the advantages of simple structure, good processing manufacturability, convenient installation and good assembly manufacturability, and design compensation is considered in connection with the flap wing surface
The application provides a connecting device of aircraft flap, connecting device of aircraft flap includes: flap rocker 1, connection joint 2, suspension rib joint 3, front beam 4, rear beam 5, wherein:
the flap rocker arm 1 is of a triangular truss type structure, the flap rocker arm 1 is provided with at least three suspension points, two suspension points arranged at the upper end of the flap rocker arm 1 are connected with a flap lower airfoil, and the suspension points arranged at the lower end of the flap rocker arm 1 are connected with a support arm at the trailing edge of the wing; the lower end of the suspension rib joint 3 is provided with a lug, the suspension rib joint 3 is connected with the front beam 4 relative to the front end of the heading, and the suspension rib joint 3 is connected with the rear beam 5 relative to the rear end of the heading; the connecting joint 2 is of an L-shaped structure, and lugs are arranged at the lower end of the L shape of the connecting joint 2; the lug of the suspension rib joint 3 is connected with one suspension point arranged at the upper end of the flap rocker arm 1, and the lug of the connection joint 2 is connected with the other suspension point arranged at the upper end of the flap rocker arm 1.
Preferably, the position of the L-shaped structure of the connection joint 2 is adjusted according to the suspension point position provided at the upper end of the flap rocker arm 1.
Preferably, the position of the L-shaped structure of the connector 2 is adjusted by padding or filing the material at the abutment.
Preferably, the front beam 4 comprises a composite beam.
Preferably, the connection joint 2 is a titanium alloy joint.
Preferably, the tab of the suspension rib joint 3 is bolted to a suspension point provided at the upper end of the flap rocker arm 1.
Preferably, the lug of the connection joint 2 is connected with another suspension point arranged at the upper end of the flap rocker 1 by means of a bolt.
Preferably, the flap rocker arm 1 comprises an aluminium alloy flap rocker arm.
Compared with the prior art, the flap rocker arm has the advantages of simple structure, good processing manufacturability, design compensation in connection with the flap airfoil, convenience in installation and good assembly manufacturability, and is beneficial to improving the flap forming stability and assembly efficiency.
Drawings
FIG. 1 is a schematic illustration of a prior art flap rocker arm suspension joint;
FIG. 2 is a schematic view of a flap rocker arm and its attachment arrangement of the present invention;
wherein: 1-flap rocker arm, 2-connection joint, 3-suspension rib joint, 4-front beam, 5-rear beam.
Detailed Description
The invention belongs to the technical field of aircraft structural design, and relates to an aircraft flap and a connecting device thereof. The flap rocker arm has the advantages of simple structure, good processing manufacturability, design compensation in connection with the flap airfoil, convenience in installation and good assembly manufacturability, and is beneficial to improving the flap forming stability and assembly efficiency.
The technical scheme of the invention is further described through specific embodiments.
The connecting device of the flap rocker arm comprises a flap rocker arm 1, a connecting joint 2, a hanging rib joint 3, a front beam 4 and a rear beam 5.
The flap rocker arm 1 is of a triangular truss structure and is formed by adding an aluminum alloy thick plate machine and is connected with the lower wing surface of the flap through front and rear points. The connecting joint 2 is made of titanium alloy material and is used for connecting the front point of the flap rocker arm 1, the front side of the connecting joint is fixed on the web plate of the front beam 4, and the lower side of the connecting joint is fixed on the lower surface of the aluminum alloy hanging rib joint 3. The hanging rib joint 3 is sleeved between the composite material front beam 4 and the rear beam 5, and the rear side is provided with a downward extending lug for connecting the rear point of the flap rocker arm 1. When the structure is assembled, the hanging rib joint 3 and the flap rocker arm 1 are positioned on the frame, and the connecting bolt penetrates through the rear point in the heading direction. The front beam 4 and the rear beam 5 are sleeved on the hanging rib joint 3, and the connecting joint 2 is installed. When the connecting joint 2 is installed, the position of the connecting joint 2 can be adjusted by adding a cushion at the joint surface or filing the material at the joint surface so as to facilitate the installation of the front connecting bolt in the heading direction.
Claims (6)
1. An aircraft flap attachment device, characterized in that the aircraft flap attachment device comprises: flap rocking arm (1), attach fitting (2), hang rib joint (3), front beam (4), back beam (5), wherein:
the flap rocker arm (1) is of a triangular truss structure, the flap rocker arm (1) is provided with at least three suspension points, two suspension points arranged at the upper end of the flap rocker arm (1) are connected with the lower wing surface of the flap, and the suspension points arranged at the lower end of the flap rocker arm (1) are connected with the support arm of the trailing edge of the wing; the lower end of the suspension rib joint (3) is provided with a lug, the front end of the suspension rib joint (3) relative to the course is connected with the front beam (4), and the rear end of the suspension rib joint (3) relative to the course is connected with the rear beam (5); the connecting joint (2) is of an L-shaped structure, and the lower end of the L-shaped connecting joint (2) is provided with lugs; the lug of the suspension rib joint (3) is connected with one suspension point arranged at the upper end of the flap rocker arm (1), and the lug of the connection joint (2) is connected with the other suspension point arranged at the upper end of the flap rocker arm (1); the position of the L-shaped structure of the connecting joint (2) is adjusted according to a hanging point position arranged at the upper end of the flap rocker arm (1); the position of the L-shaped structure of the connecting joint (2) is adjusted by adding a cushion or filing the material at the joint surface; when the structure is assembled, a hanging rib joint and a flap rocker arm are positioned on a frame, and a connecting bolt at the rear point of the heading direction is penetrated; then the front beam and the rear beam are arranged on the hanging rib joint, and the connecting joint is arranged; when the connecting joint is installed, the position of the connecting joint is adjusted by adding a cushion at the joint surface or filing materials at the joint surface so as to facilitate the installation of the front connecting bolt in the heading direction.
2. The aircraft flap connection device according to claim 1, characterized in that the front beam (4) comprises a composite beam.
3. The aircraft flap connection device according to claim 1, characterized in that the connection joint (2) is a titanium alloy joint.
4. The aircraft flap connection according to claim 1, characterized in that the lug of the suspension rib joint (3) is connected to a suspension point provided at the upper end of the flap rocker arm (1) by means of a bolt.
5. The connection device of aircraft flaps according to claim 4, characterized in that the lug of the connection joint (2) is connected by means of a bolt to another suspension point provided at the upper end of the flap rocker (1).
6. The aircraft flap connection device according to claim 1, characterized in that the flap rocker (1) comprises an aluminum alloy flap rocker.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911346474.0A CN111003156B (en) | 2019-12-24 | 2019-12-24 | Connecting device for airplane flap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911346474.0A CN111003156B (en) | 2019-12-24 | 2019-12-24 | Connecting device for airplane flap |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111003156A CN111003156A (en) | 2020-04-14 |
| CN111003156B true CN111003156B (en) | 2023-06-23 |
Family
ID=70116080
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911346474.0A Active CN111003156B (en) | 2019-12-24 | 2019-12-24 | Connecting device for airplane flap |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111003156B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112623190B (en) * | 2020-12-29 | 2023-11-21 | 中国航空工业集团公司西安飞机设计研究所 | Butt joint device for box sections of plane stabilizer |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428529A (en) * | 2016-09-23 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Control mechanism for trailing edge flap of agriculture light airplane |
| CN108100235A (en) * | 2017-11-22 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of flap configuration control mechanism |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0215522D0 (en) * | 2002-07-04 | 2002-08-14 | Smiths Wolverhampton Ltd | Flight surface actuator |
| CN101596935B (en) * | 2009-06-01 | 2011-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Airplane trailing edge flap retracting mechanism |
| CN104260606A (en) * | 2014-10-21 | 2015-01-07 | 宁波润轴汽配有限公司 | Unmanned vehicle suspension system |
| NL2016119B1 (en) * | 2016-01-19 | 2017-07-25 | Walraven Holding Bv J Van | Pipe hanger. |
| CN109383758A (en) * | 2017-08-02 | 2019-02-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of plane spoiler auxiliary connecting device |
| US10882601B2 (en) * | 2017-10-13 | 2021-01-05 | The Boeing Company | Aircraft wings having improved deflection control ribs |
| CN108216577A (en) * | 2017-12-08 | 2018-06-29 | 西安飞机工业（集团）有限责任公司 | A kind of safety structure of aircraft flap connector connection |
| CN109606638B (en) * | 2018-11-07 | 2022-05-27 | 中国航空工业集团公司西安飞机设计研究所 | Sunken hinge type flap rocker arm supporting structure |
-
2019
- 2019-12-24 CN CN201911346474.0A patent/CN111003156B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428529A (en) * | 2016-09-23 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Control mechanism for trailing edge flap of agriculture light airplane |
| CN108100235A (en) * | 2017-11-22 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of flap configuration control mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111003156A (en) | 2020-04-14 |
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