CN104554709B - A kind of flap kinematics stopper mechanism - Google Patents
A kind of flap kinematics stopper mechanism Download PDFInfo
- Publication number
- CN104554709B CN104554709B CN201310492720.XA CN201310492720A CN104554709B CN 104554709 B CN104554709 B CN 104554709B CN 201310492720 A CN201310492720 A CN 201310492720A CN 104554709 B CN104554709 B CN 104554709B
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- China
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- group
- bearing
- wheel support
- restraint wheel
- restraint
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Abstract
The present invention relates to a kind of flap kinematics stopper mechanism；Including: restraint wheel support (1), clutch shaft bearing group (2), circlip for hole group (3), working shaft (4), the second bearing group (5), little axle group (6), holding screw group (7), tack axle group (8), the 3rd bearing group (9), opening pin bank (10).The gap width of present invention stopper mechanism up and down with slide rail web surface by changing two slide rail junctions, ensure that the wing flap spatial movement restriction orbiting motion along design, with the motion in other directions of the limit wing flap, and ensure that wing flap will not clamping stagnation in motion process.
Description
Technical field
The invention belongs to field of airplane design, relate to a kind of flap kinematics stopper mechanism.
Background technology
It is single that traditional flap kinematics stopper mechanism can only play restriction in the retrogressing or deflection of wing flap
The function of the motion in direction, and retrogressing or the deflection of wing flap can not be ensured simultaneously, and the outer wing flap requirement of type aircraft
Wing flap to be deflected outward by during retreating simultaneously, and this motion is more complicated spatial movement pattern, general limit
Motivation structure cannot meet this design requirement.
Aircraft flap is typically all and is supported by two or more slide rails, moves along slide rail direction, if respectively
The design of flap kinematics stopper mechanism is unreasonable, then wing flap is possible to clamping stagnation occur during motion, impact
Wing flap proper motion.
Summary of the invention
It is an object of the invention to design a kind of flap kinematics stopper mechanism, can guarantee that the wing flap retrogressing along slide rail direction
Or yaw motion, with the motion in other directions of the limit wing flap, and ensure that wing flap will not block in motion process
Stagnant.
The technical scheme is that a kind of flap kinematics stopper mechanism, including: restraint wheel support 1, the first axle
Hold group 2, circlip for hole group 3, working shaft 4, the second bearing group 5, little axle group 6, holding screw group 7,
Tack axle group 8, the 3rd bearing group 9, opening pin bank 10 is constituted.
The annexation of each several part is as follows:
Restraint wheel support 1 is the critical piece of this mechanism, and remaining part is all connected on restraint wheel support 1.
The top of restraint wheel support 1 have symmetry U-shaped groove 11 and axially through circular hole 12；Restraint is taken turns
The middle part of support 1 have M type groove 13 and axially through the first sets of vias 14；Restraint wheel support 1 time
Portion has ten type grooves 15, has the second the most through sets of vias 16, restraint in the both sides of ten type grooves 15
The left and right lateral surface of wheel support 1 is respectively arranged with the coaxial clyinder of same size.
Clutch shaft bearing group 2 is made up of the bearing of two same sizes, and bearing lays respectively at U-shaped groove 11 both sides
Groove in, clutch shaft bearing group 2 is connected with restraint wheel support 1 by working shaft 4, and working shaft 4 is positioned at circular hole
It is fixed on restraint wheel support 1 in 12 and by circlip for hole group 3；
Second bearing group 5 is made up of the bearing of four same sizes, in two side channels of M type groove 13 before difference
Two bearings of rear layout, the second bearing group 5 is connected with restraint wheel support 1 by little axle group 6, little axle group 6
It is positioned at the first sets of vias 14 and is fixed on restraint wheel support 1 by holding screw group 7；
3rd bearing group 9 is made up of the bearing of two same sizes, is respectively arranged in the axial of ten type grooves 15
Two side channels in, the 3rd bearing group 9 is connected on restraint wheel support 1 by tack axle group 8, tack axle group 8
It is positioned at the second sets of vias 16 and is fixed on restraint wheel support 1 by opening pin bank 10.
Invention effect is the gap by the stopper mechanism up and down with slide rail web surface changing two slide rail junctions
Value, it is ensured that wing flap spatial movement is along the restriction orbiting motion of design.
Accompanying drawing explanation
Fig. 1 is the structural front view of the present invention；
Fig. 2 is the structure right view of the present invention；
Fig. 3 is the sectional view of the A-A of the present invention；
Wherein, 1-restraint wheel support, 2-clutch shaft bearing group, 3-circlip for hole group, 4-working shaft, 5-
Second bearing group, 6-little axle group, 7-holding screw group, 8-tack axle group, 9-the 3rd bearing group, 10-opening
Pin bank, 11-U type groove, 12-circular hole, 13-M type groove, 14-the first sets of vias, 15-ten type groove, 16-
Second sets of vias, 17 cylinders.
Detailed description of the invention
Refer to Fig. 1-3, a kind of flap kinematics stopper mechanism, including: restraint wheel support 1, clutch shaft bearing group
2, circlip for hole group 3, working shaft 4, the second bearing group 5, little axle group 6, holding screw group 7, flat
Head axle group 8, the 3rd bearing group 9, opening pin bank 10.
The top of restraint wheel support 1 have symmetry U-shaped groove 11 and axially through circular hole 12；Restraint is taken turns
The middle part of support 1 have M type groove 13 and axially through the first sets of vias 14；Restraint wheel support 1 time
Portion has ten type grooves 15, has the second the most through sets of vias 16, restraint in the both sides of ten type grooves 15
The left and right lateral surface of wheel support 1 is respectively arranged with the coaxial clyinder 17 of same size.
Clutch shaft bearing group 2 is made up of the bearing of two same sizes, and bearing lays respectively at U-shaped groove 11 both sides
Groove in, clutch shaft bearing group 2 is connected with restraint wheel support 1 by working shaft 4, and working shaft 4 is positioned at circular hole
It is fixed on restraint wheel support 1 in 12 and by circlip for hole group 3；Clutch shaft bearing group 2 and slide rail
Upper working face or the contact of lower working face, roll on working face, be the active wheel of main load.
Second bearing group 5 is made up of the bearing of four same sizes, in two side channels of M type groove 13 before difference
Two bearings of rear layout, the second bearing group 5 is connected with restraint wheel support 1 by little axle group 6, little axle group 6
It is positioned at the first sets of vias 14 and is fixed on restraint wheel support 1 by holding screw group；Second bearing group 5
The back surfaces of four bearings and slide rail working face have certain gap width, restraint when being used for adjusting flap kinematics
The position of mechanism；Clutch shaft bearing group 2 and the cooperation of the second bearing group 5 can limit restraint wheel support 1 and be perpendicular to cunning
The motion in rail working face direction, and the elevating movement of restraint wheel support 1 can be limited.
3rd bearing group 9 is made up of the bearing of two same sizes, is respectively arranged in the axial of ten type grooves 15
Two side channels in, the 3rd bearing group 9 is connected on restraint wheel support 1 by tack axle group 8, tack axle group 8
It is positioned at the second sets of vias 16 and is fixed on restraint wheel support 1 by opening pin bank 10.3rd bearing group 9
Two bearings and slide rail side web be reserved with certain gap, and the stopper mechanism both sides of diverse location
Gap width is the most different, can limit restraint wheel support 1 and be perpendicular to the motion in web direction, slide rail side.
Claims (1)
1. a flap kinematics stopper mechanism, including: restraint wheel support (1), clutch shaft bearing group (2), circlip for hole
Group (3), working shaft (4), the second bearing group (5), little axle group (6), holding screw group (7), tack axle group (8), the
Three bearing group (9), opening pin bank (10), it is characterised in that:
The top of restraint wheel support (1) have symmetry U-shaped groove (11) and axially through circular hole (12)；Restraint wheel
The middle part of frame (1) have M type groove (13) and axially through the first sets of vias (14)；Under restraint wheel support (1)
Portion has ten type grooves (15), has the most through the second sets of vias (16) in the both sides of ten type grooves (15), and restraint is taken turns
The left and right lateral surface of support (1) is respectively arranged with the coaxial clyinder (17) of same size；
Clutch shaft bearing group (2) is made up of the bearing of two same sizes, and bearing lays respectively at the groove of U-shaped groove (11) both sides
In, clutch shaft bearing group (2) is connected with restraint wheel support (1) by working shaft (4), and working shaft (4) is positioned at circular hole (12)
In and pass through circlip for hole group (3) be fixed on restraint wheel support (1)；
Second bearing group (5) is made up of the bearing of four same sizes, cloth before and after difference in two side channels of M type groove (13)
Putting two bearings, the second bearing group (5) is connected with restraint wheel support (1) by little axle group (6), and little axle group (6) is positioned at
It is fixed on restraint wheel support (1) in first sets of vias (14) and by holding screw group (7)；
3rd bearing group (9) is made up of the bearing of two same sizes, is respectively arranged in axial two of ten type grooves (15)
In side channel, the 3rd bearing group (9) is connected on restraint wheel support (1) by tack axle group (8), tack axle group (8) position
It is fixed on restraint wheel support (1) in the second sets of vias (16) and by opening pin bank (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310492720.XA CN104554709B (en) | 2013-10-21 | 2013-10-21 | A kind of flap kinematics stopper mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310492720.XA CN104554709B (en) | 2013-10-21 | 2013-10-21 | A kind of flap kinematics stopper mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104554709A CN104554709A (en) | 2015-04-29 |
| CN104554709B true CN104554709B (en) | 2016-08-24 |
Family
ID=53071990
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310492720.XA Expired - Fee Related CN104554709B (en) | 2013-10-21 | 2013-10-21 | A kind of flap kinematics stopper mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104554709B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0303458A2 (en) * | 1987-08-11 | 1989-02-15 | British Aerospace Public Limited Company | Trailing edge flaps for aircraft wings |
| US5566910A (en) * | 1993-10-12 | 1996-10-22 | Daimler-Benz Aerospace Airbus Gmbh | Apparatus for adjusting aircraft wing flaps |
| US6149105A (en) * | 1995-08-26 | 2000-11-21 | British Aerospace Public Limited Company | Deployment mechanisms for aircraft auxiliary airfoils |
| RU2346229C2 (en) * | 2006-09-25 | 2009-02-10 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Steering assembly |
| CN101450712A (en) * | 2007-12-06 | 2009-06-10 | 滚动轴承美国公司 | Actuation system for a lift assisting device and roller bearings used therein |
| WO2013107656A1 (en) * | 2012-01-21 | 2013-07-25 | Liebherr-Aerospace Lindenberg Gmbh | Rotation lock |
-
2013
- 2013-10-21 CN CN201310492720.XA patent/CN104554709B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0303458A2 (en) * | 1987-08-11 | 1989-02-15 | British Aerospace Public Limited Company | Trailing edge flaps for aircraft wings |
| US5566910A (en) * | 1993-10-12 | 1996-10-22 | Daimler-Benz Aerospace Airbus Gmbh | Apparatus for adjusting aircraft wing flaps |
| US6149105A (en) * | 1995-08-26 | 2000-11-21 | British Aerospace Public Limited Company | Deployment mechanisms for aircraft auxiliary airfoils |
| RU2346229C2 (en) * | 2006-09-25 | 2009-02-10 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Steering assembly |
| CN101450712A (en) * | 2007-12-06 | 2009-06-10 | 滚动轴承美国公司 | Actuation system for a lift assisting device and roller bearings used therein |
| WO2013107656A1 (en) * | 2012-01-21 | 2013-07-25 | Liebherr-Aerospace Lindenberg Gmbh | Rotation lock |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104554709A (en) | 2015-04-29 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160824 Termination date: 20171021 |