CN209721257U - A kind of aircraft engine clip dampening assembly - Google Patents
A kind of aircraft engine clip dampening assembly Download PDFInfo
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- CN209721257U CN209721257U CN201920248009.2U CN201920248009U CN209721257U CN 209721257 U CN209721257 U CN 209721257U CN 201920248009 U CN201920248009 U CN 201920248009U CN 209721257 U CN209721257 U CN 209721257U
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- fixed
- clip
- aircraft engine
- dampening assembly
- shaped support
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Abstract
The utility model discloses a kind of aircraft engine clip dampening assemblies, belong to clip dampening assembly technical field.Including clip, the clip includes curved portion and fixed part, and the fixed part surface is equipped with fixation hole, and the inner surface of curved portion is fixed with the metal resilient cushion being process by coiling processing tool and stamping die.The beneficial effects of the utility model are: the processing of resilient cushion blank replaces manual work using processing tool, labor cost is reduced, improves working efficiency, guarantees the uniformity of winding, to guarantee the damping using effect of metal resilient cushion.
Description
Technical field
The utility model relates to a kind of aircraft engine dampening assemblies, belong to clip dampening assembly technical field.
Background technique
Machine engine clip dampening assembly includes resilient cushion, and manufacturing process includes carrying out the helix of spring like laterally
With longitudinal winding, blank is formed, blank passes through compacting again and forms resilient cushion, and existing blank is all by artificial hand
Dynamic winding is made, and production efficiency is low, and labor cost is high, and the elasticity and the uniformity that wind not can guarantee, and influence later period system
At resilient cushion quality.
Utility model content
To solve defect of the existing technology, the purpose of the utility model is to provide a kind of uniform aircraft engines of winding
Machine clip dampening assembly.
The technical solution of the utility model is: a kind of aircraft engine clip dampening assembly, including clip, the clip packet
Bracket portion and fixed part, the fixed part surface are equipped with fixation hole, and the inner surface of curved portion, which is fixed with, processes work by coiling
The metal resilient cushion that dress and stamping die are process.
The coiling processing tool includes coil winding machine, the winding bracket of the output end connection arc of the coil winding machine, described
The working end of winding bracket is equipped with the entrance hole passed through for tubular helical coil, and the coil winding machine opposite side is equipped with shaped support, institute
The end that shaped support is connected to pivoted arm is stated, pivoted arm one end is rotatablely connected sliding panel, pivoted arm other end hinge by rotary shaft
The output end of cylinder is connect, the cylinder is hingedly located at the cylinder block on sliding panel, and the sliding panel is driven by stepper motor and slided
Dynamic to be connected in linear guide, the coil winding machine, cylinder and stepper motor are all connected with control system.
The winding bracket end is equipped with coiling elasticity regulating device, and the coiling elasticity regulating device includes, Gu
Be scheduled on the working end of winding bracket and there is externally threaded stud, be equipped with wedge cavities in the stud, the wedge cavities be connected into
String holes, wedge shape rubber block and wedge cavities plug-in type cooperate, and the outer top of wedge cavities is extended at the top of the wedge shape rubber block, described
Through there is the through-hole passed through for tubular helical coil among wedge shape rubber block, stud is threadedly coupled adjusting nut, adjusting nut top
Portion is equipped with threading hole, and the threading hole is connected to through-hole, is bonded at the top of adjusting nut inner top and wedge shape rubber block.
The shaped support includes that, in four screw rods that groined type is distributed, the end of adjacent screw rod is solid through L shape two-by-two
Determine the both ends of block, and be fixed by fixing bolt, shaped support is detachable by the connecting end surface of L shape fixed block and pivoted arm
Connection.
The rectangle resilient cushion that the density of the metal resilient cushion is 2.1-2.3 grams/cc.
The stamping die includes upper die and lower die, and finishing die is located at the periphery of the upper die and lower die, the upper mold, under
Mould and finishing die material are Cr12MoV, hardness HRC58-62.
The linear guide is fixed on bottom plate, and stepper motor is fixed on motor fixing plate, the motor fixing plate bottom
Portion is fixed on bottom end, and the bottom plate and coil winding machine are separately fixed on the raised end face at matrix both ends.
The sliding panel bottom is fixed with the driving nut connecting with ball-screw, and the ball-screw is connected through shaft coupling
The stepper motor.
The pivoted arm includes the slave arm of actuating arm and bending, and the output end of the hinged cylinder in actuating arm end rotates axle position
In on slave arm.
The beneficial effects of the utility model are: the processing of resilient cushion blank replaces manual work, drop using processing tool
Low labor cost improves working efficiency, guarantees the uniformity of winding, to guarantee the damping using effect of metal resilient cushion.
Detailed description of the invention
Fig. 1 is the first working state figure of coiling processing tool and shaped support；
Fig. 2 is the second working state figure of coiling processing tool and shaped support；
Fig. 3 is winding bracket structure chart；
Fig. 4 is the partial enlarged view of Fig. 3；
Fig. 5 is clip dampening assembly structural schematic diagram.
Appended drawing reference is as follows in figure: a, curved portion, b, fixed part, c, fixation hole, d, metal resilient cushion；1, matrix, 2, around
Line machine, 3, winding bracket, 3.1, entrance hole, 4, shaped support, 4.1, screw rod, 4.2, L shape fixed block, 4.3, fixing bolt, 5,
Coiling elasticity regulating device, 5.1, stud, 5.2, wedge cavities, 5.3, wedge shape rubber block, 5.4, through-hole, 5.5, adjusting nut,
5.6, threading hole, 6, pivoted arm, 7, cylinder, 8, cylinder block, 9, sliding panel, 10, shaft coupling, 11, motor fixing plate, 12, stepping electricity
Machine, 13, linear guide, 14, bottom plate, 15, ball-screw, 16, rotary shaft, 17, driving nut.
Specific embodiment
1-5 is described further the utility model with reference to the accompanying drawing:
A kind of aircraft engine clip dampening assembly, including clip, the clip include curved portion a and fixed part b, institute
The surface fixed part b is stated equipped with fixation hole c, the inner surface of curved portion a is fixed with metal resilient cushion d.
The manufacturing process of the metal resilient cushion d includes the following steps:
Step S1: tubular helical coil is made in stainless steel metal wire using spiral winding molding equipment；
Step S2: coiling processing tool is utilized, tubular helical coil is processed as blank；
Step S3: punch forming is carried out to blank.
The coiling processing tool includes coil winding machine 2, the winding bracket 3 of the output end connection arc of the coil winding machine 2, institute
The working end for stating winding bracket 3 is equipped with the entrance hole 3.1 passed through for helix, and 2 opposite side of coil winding machine is equipped with shaped support 4,
The shaped support 4 includes that, in four screw rods 4.1 that groined type is distributed, the end of adjacent screw rod 4.1 is solid through L shape two-by-two
Determine the both ends of block 4.2, and be fixed by fixing bolt 4.3, shaped support 4 passes through the company of L shape fixed block 4.2 and pivoted arm 6
Contact surface is detachably connected, and the pivoted arm 6 includes the slave arm of actuating arm and bending, the output of the hinged cylinder 7 in actuating arm end
End, rotary shaft 16 are located on slave arm, and are rotatablely connected sliding panel 9 by rotary shaft 16, and the rotational angle of pivoted arm 6 is 90 °,
The output end of the hinged cylinder 7 of 6 other end of pivoted arm, the cylinder 7 are hingedly located at the cylinder block 8 on sliding panel 9, the sliding panel 9
Bottom is fixed with the driving nut 17 connecting with ball-screw 15, and the ball-screw 15 connects the stepping through shaft coupling 10
Motor 12, sliding panel 9 are slidably connected in linear guide 13 by the driving of stepper motor 12, and linear guide 13 is fixed on bottom plate 14
On, stepper motor 12 is fixed on motor fixing plate 11, and 11 bottom of motor fixing plate is fixed on 14 end of bottom plate, bottom plate 14
And coil winding machine 2 is separately fixed on the raised end face at 1 both ends of matrix, the coil winding machine 2, cylinder 7 and stepper motor 12 are equal
Connect control system；3 end of winding bracket is equipped with coiling elasticity regulating device 5, the coiling elasticity regulating device 5
Including, it is fixed on the working end of winding bracket 3 and there is externally threaded stud 5.1, be equipped with wedge cavities 5.2 in the stud 5.1,
The wedge cavities 5.2 are connected to entrance hole 3.1, and wedge shape rubber block 5.3 and 5.2 plug-in type of wedge cavities cooperate, and the wedge-shaped rubber
The outer top of wedge cavities 5.2 is extended at the top of block 5.3, running through among the wedge shape rubber block 5.3 has the through-hole passed through for helix
5.4, stud 5.1 is threadedly coupled adjusting nut 5.5, and threading hole 5.6 is equipped at the top of adjusting nut 5.5, and the threading hole 5.6 connects
It is bonded at the top of hole 5.4 all, 5.5 inner top of adjusting nut and wedge shape rubber block 5.3.
The step S2 is specifically included:
Step S2.1: sequentially passing through through-hole 5.4 and entrance hole 3.1 for tubular helical coil one end, and by tubular helical line
The end of circle is fixed on screw rod 4.1；
Step S2.2: rotating adjusting nut 5.5 pushes wedge shape rubber block 5.3 to move into wedge cavities 5.2, passes through wedge shape
5.2 inner wall of chamber changes the pore size of through-hole 5.4, to change 5.4 inner wall of through-hole to the squeezing action of wedge shape rubber block 5.3
To the size of the moving resistance of tubular helical line, and then adjust the elasticity of coiling；
Step S2.3: starting coil winding machine 2 and stepper motor 12, it is enterprising in the shaped support 4 under the first working condition
The coiling of row blank is processed, and first working condition is shaped support 4 when the connecting end surface of pivoted arm 6 is opposite with coil winding machine 2
Locating working condition, winding bracket 3 are rotated around 4 periphery of shaped support, and tubular helical coil is wound into shaped support 4
On, meanwhile, stepper motor 12 pushes the shaped support 4 being fixed on the pivoted arm 6 of sliding panel 9 to move along linear guide 13, thus
Make tubular helical coil one layer of uniform winding in shaped support 4；
Step S2.4: tubular helical coil is in shaped support 4 after one layer of uniform winding, coil winding machine 2 and stepper motor 12
Pause operating, cylinder 7 act, and pivoted arm 6 is pushed to rotate 90 degree around rotary shaft 16, and shaped support 4 is driven to rotate 90 degree to the second work
Make state；
Step S2.5: coil winding machine 2 and stepper motor 12 restart, and winding bracket 3 surrounds under the second working condition
4 periphery of shaped support rotation, tubular helical coil is wound into shaped support 4, meanwhile, stepper motor 12 promotion be fixed on
Shaped support 4 on the pivoted arm 6 of sliding panel 9 is moved along linear guide 13, to make tubular helical coil in shaped support 4
One layer of uniform winding, tubular helical coil is formed by winding layer perpendicular to second under the first working condition of shaped support 4
Winding layer is formed by under working condition；
Step S2.6: it repeats step S2.3- step S2.5 totally 8 times；
Step S2.7: pause coil winding machine 2, stepper motor 12 and cylinder 7, by tubular helical coil from shaped support 4 with around
It is cut off between line elasticity regulating device 5；
Step S2.8: the shaped support 4 for being wound with blank is unloaded from pivoted arm 6, rotary fixing screw bolt 4.3, by four
Root screw rod 4.1 is extracted out from blank, so that blank be unloaded；
Step S2.9: screw rod 4.1 and L shape fixed block are assembled into shaped support 4, are recycled to subsequent work.
Step S3 carries out punch forming to blank using stamping die, and forming density is 2.1-2.3 grams/cc
Rectangle vibration-absorbing pad structure.
The stamping die includes upper die and lower die, and finishing die is located at the periphery of the upper die and lower die, the upper mold, under
Mould and finishing die material are Cr12MoV, hardness HRC58-62.
The stainless steel metal wire is the 1Cr18Ni9Ti wire of diameter 0.09mm, and the tubular helical coil diameter is
1.15mm-1.3mm。
The above is only the preferred embodiment of the utility model, it is noted that for the common skill of the art
For art personnel, without deviating from the technical principle of the utility model, several improvements and modifications can also be made, these change
It also should be regarded as the protection scope of the utility model into modification.
Claims (8)
1. a kind of aircraft engine clip dampening assembly, which is characterized in that including clip, the clip include curved portion (a) and
Fixed part (b), fixed part (b) surface are equipped with fixation hole (c), and the inner surface of curved portion (a) is fixed with to be processed by coiling
The metal resilient cushion (d) that tooling and stamping die are process；
The coiling processing tool includes coil winding machine (2), the winding bracket (3) of the output end connection arc of the coil winding machine (2),
The working end of the winding bracket (3) is equipped with the entrance hole (3.1) passed through for tubular helical coil, coil winding machine (2) opposite side
Equipped with shaped support (4), the shaped support (4) is connected to the end of pivoted arm (6), and described pivoted arm (6) one end passes through rotary shaft
(16) sliding panel (9) are rotatablely connected, the output end of the hinged cylinder of pivoted arm (6) other end (7), the cylinder (7), which is hingedly located at, to be slided
Cylinder block (8) on movable plate (9), the sliding panel (9) are slidably connected at linear guide (13) by stepper motor (12) driving
On, the coil winding machine (2), cylinder (7) and stepper motor (12) are all connected with control system.
2. aircraft engine clip dampening assembly according to claim 1, which is characterized in that winding bracket (3) end
Portion is equipped with coiling elasticity regulating device (5), and the coiling elasticity regulating device (5) includes being fixed on winding bracket (3)
Working end and there are externally threaded stud (5.1), is equipped with wedge cavities (5.2) in the stud (5.1), the wedge cavities (5.2)
It is connected to entrance hole (3.1), wedge shape rubber block (5.3) and wedge cavities (5.2) plug-in type cooperate, and the wedge shape rubber block (5.3)
Top extends to wedge cavities (5.2) top outside, passes through for tubular helical coil through having among the wedge shape rubber block (5.3)
Through-hole (5.4), stud (5.1) are threadedly coupled adjusting nut (5.5), are equipped with threading hole (5.6) at the top of adjusting nut (5.5), institute
Threading hole (5.6) connection through-hole (5.4) is stated, is bonded at the top of adjusting nut (5.5) inner top and wedge shape rubber block (5.3).
3. aircraft engine clip dampening assembly according to claim 1, which is characterized in that shaped support (4) packet
It includes, in four screw rods (4.1) that groined type is distributed, the end of adjacent screw rod (4.1) is through L shape fixed block (4.2) two-by-two
Both ends, and be fixed by fixing bolt (4.3), shaped support (4) passes through the connection of L shape fixed block (4.2) and pivoted arm (6)
End face is detachably connected.
4. aircraft engine clip dampening assembly according to claim 1, which is characterized in that the metal resilient cushion (d)
Density be 2.1-2.3 grams/cc of rectangle resilient cushion.
5. aircraft engine clip dampening assembly according to claim 1, which is characterized in that the stamping die includes upper
Mould and lower die, finishing die are located at the periphery of the upper die and lower die, and the upper die and lower die and finishing die material are
Cr12MoV, hardness HRC58-62.
6. aircraft engine clip dampening assembly according to claim 1, which is characterized in that the linear guide (13) is solid
It is scheduled on bottom plate (14), stepper motor (12) is fixed on motor fixing plate (11), and motor fixing plate (11) bottom is fixed
In bottom plate (14) end, the bottom plate (14) and coil winding machine (2) are separately fixed on the raised end face at matrix (1) both ends.
7. aircraft engine clip dampening assembly according to claim 1, which is characterized in that sliding panel (9) bottom
It is fixed with the driving nut (17) connecting with ball-screw (15), the ball-screw (15) connects the step through shaft coupling (10)
Into motor (12).
8. aircraft engine clip dampening assembly according to claim 1, which is characterized in that the pivoted arm (6) includes driving
The slave arm of swing arm and bending, the output end of the hinged cylinder in actuating arm end (7), rotary shaft (16) are located on slave arm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920248009.2U CN209721257U (en) | 2019-02-27 | 2019-02-27 | A kind of aircraft engine clip dampening assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920248009.2U CN209721257U (en) | 2019-02-27 | 2019-02-27 | A kind of aircraft engine clip dampening assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209721257U true CN209721257U (en) | 2019-12-03 |
Family
ID=68684259
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920248009.2U Active CN209721257U (en) | 2019-02-27 | 2019-02-27 | A kind of aircraft engine clip dampening assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209721257U (en) |
-
2019
- 2019-02-27 CN CN201920248009.2U patent/CN209721257U/en active Active
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