CN114134738A - Airplane part directional double-sided rapid pressing sleeve machining process and device - Google Patents
Airplane part directional double-sided rapid pressing sleeve machining process and device Download PDFInfo
- Publication number
- CN114134738A CN114134738A CN202111468787.0A CN202111468787A CN114134738A CN 114134738 A CN114134738 A CN 114134738A CN 202111468787 A CN202111468787 A CN 202111468787A CN 114134738 A CN114134738 A CN 114134738A
- Authority
- CN
- China
- Prior art keywords
- fixedly connected
- pressing
- sleeve
- rotating
- block
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- D—TEXTILES; PAPER
- D07—ROPES; CABLES OTHER THAN ELECTRIC
- D07B—ROPES OR CABLES IN GENERAL
- D07B7/00—Details of, or auxiliary devices incorporated in, rope- or cable-making machines; Auxiliary apparatus associated with such machines
- D07B7/16—Auxiliary apparatus
Landscapes
- Toys (AREA)
- Press Drives And Press Lines (AREA)
Abstract
The invention discloses a directional double-sided rapid sleeve pressing machining device for airplane parts, which comprises a vertical mounting plate, wherein a device fixing plate is fixedly connected to the lower end of one side of the vertical mounting plate, a gear disc is fixedly connected to the upper end of the vertical mounting plate, a limiting fixed gear is fixedly connected to one side of the gear disc, a motor through hole is formed in the center of the limiting fixed gear, a rotating motor is fixedly connected to one side of the vertical mounting plate, the rotating motor is connected with a motor output shaft, the motor output shaft penetrates through the motor through hole and is fixedly connected with a constant-speed rotating rod, a pipe connecting plate is fixedly connected to one side of the vertical mounting plate, and a rod fixing sliding barrel is fixedly connected to the pipe connecting plate. The invention adopts the combined structure of the pressing sleeve spring and the solid load bearing block, so that when the non-return rotating bayonet lock is separated from the limit fixed gear, the non-return rotating bayonet lock can descend at an accelerated speed, sufficient pressing sleeve power is provided, meanwhile, the side pressing page block can have sufficient power to carry out compaction operation on airplane parts from two sides, and the structure has rationality.
Description
Technical Field
The invention relates to the technical field of sleeve pressing devices, in particular to a directional double-sided rapid sleeve pressing processing technology and device for airplane parts.
Background
The sleeve pressing machine is a more popular international processing device for steel wire rope rigging. The hydraulic power-driven device is widely used in domestic enterprises after equipment manufacturing, introduction, research, development, improvement and production in China, and is compact in structure, stable in operation, low in noise and high in working efficiency. The steel wire rope sleeve pressing machine adopts a non-cutting plastic processing technology, so that the soft metal can flow in the die cavity fully on the premise of not damaging the strength of the steel wire, the steel wire of the steel wire rope is tightened, and the purpose of forming is achieved through the friction force between the steel wires.
The hydraulic pressure is mostly adopted to press the cover for the quick pressure cover of aircraft part at present, presses the cover inefficiency, and when pressing the cover, only unilateral ascending pressure cover, presses the cover structure probably to appear becoming flexible, causes the disconnection, produces the potential safety hazard.
Disclosure of Invention
The invention aims to: in order to solve the problems, the invention provides a process and a device for the directional double-sided rapid press sleeve processing of airplane parts.
In order to achieve the purpose, the invention adopts the following technical scheme:
a device for processing an oriented double-sided rapid pressing sleeve of an airplane part comprises a vertical mounting plate, a device fixing plate is fixedly connected at the lower end of one side of the vertical mounting plate, a gear disc is fixedly connected at the upper end of the vertical mounting plate, a limit fixed gear is fixedly connected at one side of the gear disc, a motor through hole is formed in the center of the limit fixed gear, a rotating motor is fixedly connected at one side of the vertical mounting plate and is connected with a motor output shaft, the motor output shaft penetrates through the motor through hole and is fixedly connected with a constant-speed rotating rod, a pipe connecting plate is fixedly connected at one side of the vertical mounting plate and is fixedly connected with a rod fixing sliding cylinder, the rod fixing sliding cylinder is fixedly connected with a lower pressing sleeve base, a side hinge connecting block is fixedly connected at the upper end of the rod fixing sliding cylinder, and a side pressing hinge block is rotatably connected with a side pressing hinge block, an upper pressing sleeve block is arranged right above the lower pressing sleeve base, and a linkage mechanism for driving the upper pressing sleeve block to lift is arranged at the upper end of the upper pressing sleeve block.
Preferably, the linkage mechanism comprises a lifting connecting plate, a deflection connecting piece is fixedly connected to the lower end of the lifting connecting plate, an angle deflection shaft is fixedly connected to the inside of the deflection connecting piece, the angle deflection shaft is rotatably connected with a deflection limiting fastener, and the lower end of the deflection limiting fastener is fixedly connected with an upper pressing sleeve block.
Preferably, the hinge accommodating grooves are formed in the upper pressing sleeve block, the hinge accommodating grooves are two and are symmetrically arranged in the upper pressing sleeve block, the hinge accommodating grooves and the side pressing hinge blocks are matched with each other, the side pressing hinge blocks between the side hinge connecting blocks are two and are rotatably connected with each other.
Preferably, go up and press the vertical slide bar of cover piece lower extreme fixedly connected with, vertical slide bar is provided with four, vertical slide bar runs through the fixed slide cartridge of pole and extends to the solid burden heavy piece of the fixed slide cartridge lower extreme fixedly connected with of pole, be connected with between the fixed slide cartridge of pole and the solid burden heavy piece and press the cover spring, press the cover spring to encircle and set up in the vertical slide bar outside.
Preferably, promote connecting plate upper end fixedly connected with hub connection piece, through connection has the swivelling joint axle in the hub connection piece, it is connected with variable speed rotating vane and the rotatory bayonet lock of non return to rotate on the swivelling joint axle, variable speed rotating vane sets up between hub connection piece and the rotatory bayonet lock of non return.
Preferably, one end of the variable-speed rotating blade is rotatably connected to an output shaft of the motor, one side of the variable-speed rotating blade is fixedly connected with a belt-off catch, the belt-off catch and the uniform-speed rotating rod are both arranged between the variable-speed rotating blade and the lifting connecting plate, and one end of the non-return rotating bayonet lock can be meshed with the limiting fixed gear.
A directional double-sided rapid pressing sleeve processing technology for airplane parts comprises the following specific steps:
s1: under a natural state, the non-return rotating bayonet lock is meshed with one tooth at the upper end of the limiting fixed gear, the pressing sleeve spring is in a contracted state at the moment, the side pressing hinge block is in an unfolded state, and the airplane part needing pressing sleeve is placed on the lower pressing sleeve base;
s2: controlling the rotating motor to rotate so that the constant-speed rotating rod rotates at a constant speed, and when the constant-speed rotating rod contacts the belt-off retaining pillar, driving the variable-speed rotating blades fixedly connected with the belt-off retaining pillar to rotate, wherein the non-return rotating bayonet lock is separated from the limiting fixed gear and rotates around the limiting fixed gear;
s3: under the action of the solid negative weight block and the pressing sleeve spring, the upper pressing sleeve block descends in an accelerated manner and collides with the lower pressing sleeve base, the side pressing hinge blocks are collided by the upper surface of the hinge receiving groove, and the pressing page blocks on the two sides are bent, so that the airplane parts can be pressed from the two sides, and the pressing sleeve is guaranteed to be compact;
s4: when the upper sleeve pressing block descends in an accelerating mode, the belt-separating retaining column rotating in a variable speed mode is separated from the uniform rotating rod rotating in a uniform speed mode, after sleeve pressing is completed, the upper sleeve pressing block ascends in a decelerating mode when moving to the lowest end under the action of inertia force, finally, the non-return rotating bayonet lock is meshed with the limiting fixed gear, the whole set of sleeve pressing operation is completed, the initial state is recovered, and the next driving of the uniform rotating rod is waited.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. this application is through adopting pressing cover spring and solid heavy burden piece integrated configuration for when the rotatory bayonet lock of non return breaks away from spacing fixed gear, can descend with higher speed, provide sufficient pressure cover power, make simultaneously that side pressfitting page or leaf piece can have sufficient power to carry out the compaction operation to the aircraft part from both sides, the structure has the rationality.
2. This application utilizes mechanical structure to replace traditional hydraulic structure through adopting interlock mechanism for press set efficiency to improve, and reserve sufficient time and place aircraft part, through the rotation cycle of control rotating electrical machines promptly, reach the pressure set effect of different efficiency.
Drawings
Fig. 1 is a schematic structural diagram illustrating an overall sleeve pressing device provided according to an embodiment of the present invention;
fig. 2 is a schematic diagram illustrating an explosive structure of a sleeve pressing device according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a lower pressure sleeve base provided in accordance with an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a linkage mechanism according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram illustrating connection of an upper press sleeve block and a lower press sleeve base according to an embodiment of the present invention.
Illustration of the drawings:
1. a vertical mounting plate; 2. a device fixing plate; 3. a rotating electric machine; 4. a pipe connecting plate; 5. the rod fixes the sliding cylinder; 6. pressing the sleeve spring; 7. a solid negative weight block; 8. a vertical slide bar; 9. pressing a sleeve block upwards; 10. a deflection link; 11. limiting and fixing a gear; 12. rotating the rod at a constant speed; 13. a shaft connecting block; 14. a gear plate; 15. a motor through hole; 16. pressing the sleeve base downwards; 17. a deflection limit fastener; 18. an output shaft of the motor; 19. the non-return rotating bayonet lock; 20. a side hinge connecting block; 21. pressing page blocks laterally; 22. variable speed rotating blades; 23. rotating the connecting shaft; 24. a belt-off catch post; 25. lifting the connecting plate; 26. an angular yaw axis; 27. the hinge receiving groove.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-5, the present invention provides a technical solution:
an oriented double-sided rapid pressing sleeve processing device for airplane parts comprises a vertical mounting plate 1, a device fixing plate 2 is fixedly connected to the lower end of one side of the vertical mounting plate 1, a gear disc 14 is fixedly connected to the upper end of the vertical mounting plate 1, a limiting fixed gear 11 is fixedly connected to one side of the gear disc 14, a motor through hole 15 is formed in the center of the limiting fixed gear 11, a rotating motor 3 is fixedly connected to one side of the vertical mounting plate 1, the rotating motor 3 is connected with a motor output shaft 18, the motor output shaft 18 penetrates through the motor through hole 15 and is fixedly connected with a uniform rotating rod 12, a pipe connecting plate 4 is fixedly connected to one side of the vertical mounting plate 1, a rod fixing sliding cylinder 5 is fixedly connected with the pipe connecting plate 4, a lower pressing sleeve base 16 is fixedly connected with the rod fixing sliding cylinder 5, a side hinge connecting block 20 is fixedly connected to the upper end of the rod fixing sliding cylinder 5, and the side hinge connecting block 20 is rotatably connected with a side pressing hinge block 21, an upper sleeve pressing block 9 is arranged right above the lower sleeve pressing base 16, and a linkage mechanism for driving the upper sleeve pressing block 9 to lift is arranged at the upper end of the upper sleeve pressing block 9. The linkage mechanism comprises a lifting connecting plate 25, a deflection connecting piece 10 is fixedly connected to the lower end of the lifting connecting plate 25, an angle deflection shaft 26 is fixedly connected to the interior of the deflection connecting piece 10, the angle deflection shaft 26 is rotatably connected with a deflection limiting fastener 17, and the lower end of the deflection limiting fastener 17 is fixedly connected with an upper pressing sleeve block 9. The hinge accommodating grooves 27 are formed in the upper press sleeve block 9, the hinge accommodating grooves 27 are arranged in two numbers, the two hinge accommodating grooves 27 are symmetrically arranged in the upper press sleeve block 9, the hinge accommodating grooves 27 are matched with the side press hinge blocks 21, the side press hinge blocks 21 between the side hinge connecting blocks 20 are arranged in two numbers, and the two side press hinge blocks 21 are connected in a rotating mode. Go up and press the vertical slide bar 8 of 9 lower extreme fixedly connected with of cover piece, vertical slide bar 8 is provided with four, and vertical slide bar 8 runs through pole stationary sliding barrel 5 and extends to 5 lower extreme fixedly connected with solid burden pouring weight 7 of pole stationary sliding barrel, is connected with between pole stationary sliding barrel 5 and the solid burden pouring weight 7 and presses cover spring 6, presses cover spring 6 to encircle to set up in the vertical slide bar 8 outside. The upper end of the lifting connecting plate 25 is fixedly connected with a shaft connecting block 13, a rotating connecting shaft 23 penetrates through the shaft connecting block 13, a variable-speed rotating blade 22 and a non-return rotating bayonet 19 are rotatably connected to the rotating connecting shaft 23, and the variable-speed rotating blade 22 is arranged between the shaft connecting block 13 and the non-return rotating bayonet 19. One end of a variable-speed rotating blade 22 is rotatably connected to the motor output shaft 18, one side of the variable-speed rotating blade 22 is fixedly connected with a belt-off catch 24, the belt-off catch 24 and the uniform-speed rotating rod 12 are both arranged between the variable-speed rotating blade 22 and the lifting connecting plate 25, and one end of a non-return rotating bayonet 19 can be meshed with the limiting fixed gear 11.
Specifically, as shown in fig. 1, an oriented double-sided rapid sleeve pressing processing device for airplane parts comprises a vertical mounting plate 1, a device fixing plate 2 is fixedly connected to the lower end of one side of the vertical mounting plate 1, a gear plate 14 is fixedly connected to the upper end of the vertical mounting plate 1, a limiting fixed gear 11 is fixedly connected to one side of the gear plate 14, a motor through hole 15 is formed in the center of the limiting fixed gear 11, a rotating motor 3 is fixedly connected to one side of the vertical mounting plate 1, the rotating motor 3 is connected with a motor output shaft 18, the motor output shaft 18 penetrates through the motor through hole 15 and is fixedly connected with a constant-speed rotating rod 12, a pipe connecting plate 4 is fixedly connected to one side of the vertical mounting plate 1, the pipe connecting plate 4 is fixedly connected with a rod fixing sliding cylinder 5, the rod fixing sliding cylinder 5 is fixedly connected with a lower sleeve pressing base 16, a side hinge connecting block 20 is fixedly connected to the upper end of the rod fixing sliding cylinder 5, and the side hinge connecting block 20 is rotatably connected with a side hinge pressing block 21, an upper sleeve pressing block 9 is arranged right above the lower sleeve pressing base 16, and a linkage mechanism for driving the upper sleeve pressing block 9 to lift is arranged at the upper end of the upper sleeve pressing block 9.
Specifically, as shown in fig. 5, the linkage mechanism includes a lifting connection plate 25, a deflection connection member 10 is fixedly connected to the lower end of the lifting connection plate 25, an angle deflection shaft 26 is fixedly connected to the inside of the deflection connection member 10, the angle deflection shaft 26 is rotatably connected to a deflection limit fastener 17, and the lower end of the deflection limit fastener 17 is fixedly connected to the upper pressing sleeve block 9. The hinge accommodating grooves 27 are formed in the upper press sleeve block 9, the hinge accommodating grooves 27 are arranged in two numbers, the two hinge accommodating grooves 27 are symmetrically arranged in the upper press sleeve block 9, the hinge accommodating grooves 27 are matched with the side press hinge blocks 21, the side press hinge blocks 21 between the side hinge connecting blocks 20 are arranged in two numbers, and the two side press hinge blocks 21 are connected in a rotating mode. Go up the vertical slide bar 8 of 9 lower extreme fixedly connected with of cover piece, vertical slide bar 8 is provided with four, vertical slide bar 8 runs through the solid burden pouring weight 7 of 5 lower extreme fixedly connected with of pole fixed sliding barrel 5 of pole fixed sliding barrel, be connected with between the solid burden pouring weight 7 of pole fixed sliding barrel 5, it encircles and sets up in the vertical slide bar 8 outside to press cover spring 6, adopt and press cover spring 6 and solid burden pouring weight 7 integrated configuration, make when rotatory bayonet lock 19 of non return breaks away from spacing fixed gear 11, can descend with higher speed, provide sufficient pressure cover power, make side pressfitting page or leaf piece 21 can have sufficient power to carry out the compaction operation to the aircraft part from both sides simultaneously, the structure has the rationality.
Specifically, as shown in fig. 4, the upper end of the lifting connection plate 25 is fixedly connected with a shaft connection block 13, a rotation connection shaft 23 penetrates through the shaft connection block 13, a variable-speed rotation vane 22 and a non-return rotation bayonet 19 are rotatably connected to the rotation connection shaft 23, and the variable-speed rotation vane 22 is arranged between the shaft connection block 13 and the non-return rotation bayonet 19. Variable speed rotating vane 22 one end is rotated and is connected on motor output shaft 18, variable speed rotating vane 22 one side fixedly connected with area is from bumping post 24, the area is from bumping post 24 and all sets up between variable speed rotating vane 22 and promotion connecting plate 25 with rotary rod 12 at the uniform velocity, non return rotating bayonet 19 one end can with spacing fixed gear 11 between intermeshing, utilize mechanical structure to replace traditional hydraulic structure, make the pressure cover efficiency improve, and reserve sufficient time and place the aircraft part, the rotation cycle through control rotating motor 3 promptly, reach the pressure cover effect of different efficiency.
In summary, the process for processing the directional double-sided rapid press sleeve of the airplane part provided by the embodiment includes the following steps:
s1: under the natural state, the non-return rotating bayonet 19 is meshed with one tooth at the upper end of the limit fixed gear 11, the pressing sleeve spring 6 is in a contraction state at the moment, the side pressing page block 21 is in an expansion state, and the airplane part needing pressing sleeve is placed on the lower pressing sleeve base 16;
s2: controlling the rotating motor 3 to operate so that the constant-speed rotating rod 12 rotates at a constant speed, and when the constant-speed rotating rod 12 contacts the belt-off stop pillar 24, the variable-speed rotating blade 22 fixedly connected with the belt-off stop pillar 24 is driven to rotate, and the non-return rotating bayonet pin 19 is separated from the limit fixed gear 11 and rotates around the limit fixed gear;
s3: under the action of the solid negative weight 7 and the pressing sleeve spring 6, the upper pressing sleeve block 9 descends in an accelerated manner and finishes the collision with the lower pressing sleeve base 16, the side pressing page block 21 is collided by the upper surface of the hinge receiving groove 27, and the pressing page blocks 21 at the two sides are bent, so that the airplane parts can be pressed from the two sides, and the pressing sleeve is guaranteed to be compact;
s4: when the upper sleeve pressing block 9 descends in an accelerating mode, the belt-off column 24 rotating in a variable speed mode is separated from the uniform rotating rod 12 rotating in a uniform speed mode, after sleeve pressing is completed, the upper sleeve pressing block 9 ascends in a decelerating mode when moving to the lowest end under the action of inertia force, finally the non-return rotating bayonet lock 19 is meshed with the limiting fixed gear 11, whole sleeve pressing operation is completed, the initial state is recovered, and next driving of the uniform rotating rod 12 is waited.
The previous description of the embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (7)
1. The utility model provides an aircraft part directional two-sided quick pressure cover processingequipment, includes vertical mounting panel (1), its characterized in that, vertical mounting panel (1) one side lower extreme fixedly connected with device fixed plate (2), vertical mounting panel (1) upper end fixedly connected with toothed disc (14), toothed disc (14) one side fixedly connected with spacing fixed gear (11), motor through hole (15) have been seted up at spacing fixed gear (11) center, vertical mounting panel (1) one side fixedly connected with rotating electrical machines (3), rotating electrical machines (3) are connected with motor output shaft (18), motor output shaft (18) run through motor through hole (15) fixedly connected with at the uniform velocity rotary rod (12), vertical mounting panel (1) one side fixedly connected with tube connecting plate (4), tube connecting plate (4) fixedly connected with pole stationary sliding barrel (5), the fixed sliding barrel (5) of pole is fixedly connected with and presses set base (16) down, fixed sliding barrel (5) upper end fixedly connected with side hinge connecting block (20) of pole, side hinge connecting block (20) rotate and are connected with side pressfitting page or leaf piece (21), press set base (16) directly over to be provided with down and press set piece (9), it is provided with the interlock mechanism that drives to press set piece (9) to go up to press set piece (9) upper end.
2. The device for processing the directional double-sided quick pressing sleeve of the airplane part according to claim 1, wherein the linkage mechanism comprises a lifting connecting plate (25), a deflection connecting piece (10) is fixedly connected to the lower end of the lifting connecting plate (25), an angle deflection shaft (26) is fixedly connected to the inside of the deflection connecting piece (10), the angle deflection shaft (26) is rotatably connected with a deflection limiting fastener (17), and the lower end of the deflection limiting fastener (17) is fixedly connected with an upper pressing sleeve block (9).
3. The directional double-sided rapid press sleeve processing device for the airplane parts as claimed in claim 2, wherein two hinge accommodating grooves (27) are formed in the upper press sleeve block (9), the hinge accommodating grooves (27) are symmetrically formed in the upper press sleeve block (9), the hinge accommodating grooves (27) are matched with the side press hinge blocks (21) mutually, two side press hinge blocks (21) between the side hinge connecting blocks (20) are formed, and the two side press hinge blocks (21) are connected in a rotating mode.
4. The directional double-sided rapid press sleeve processing device for the airplane parts as claimed in claim 3, wherein the lower end of the upper press sleeve block (9) is fixedly connected with a vertical slide rod (8), the number of the vertical slide rods (8) is four, the vertical slide rods (8) extend through the rod fixing slide cylinder (5) to reach the lower end of the rod fixing slide cylinder (5) to be fixedly connected with a solid negative weight block (7), a press sleeve spring (6) is connected between the rod fixing slide cylinder (5) and the solid negative weight block (7), and the press sleeve spring (6) is arranged around the outer side of the vertical slide rod (8).
5. The directional double-sided rapid press sleeve processing device for the airplane parts according to claim 4, wherein a shaft connecting block (13) is fixedly connected to the upper end of the lifting connecting plate (25), a rotating connecting shaft (23) penetrates through the shaft connecting block (13), a variable-speed rotating blade (22) and a non-return rotating bayonet lock (19) are rotatably connected to the rotating connecting shaft (23), and the variable-speed rotating blade (22) is arranged between the shaft connecting block (13) and the non-return rotating bayonet lock (19).
6. The machine for directional double-sided rapid sleeve pressing of airplane parts according to claim 5, wherein one end of the variable-speed rotating blade (22) is rotatably connected to the motor output shaft (18), one side of the variable-speed rotating blade (22) is fixedly connected with a belt-off pillar (24), the belt-off pillar (24) and the uniform-speed rotating rod (12) are both arranged between the variable-speed rotating blade (22) and the lifting connecting plate (25), and one end of the check rotating bayonet lock (19) can be meshed with the limit fixed gear (11).
7. A directional double-sided rapid pressing sleeve processing technology for airplane parts is characterized by comprising the following specific steps:
s1: under the natural state, the non-return rotary bayonet lock (19) is meshed with one tooth at the upper end of the limit fixed gear (11), the pressing sleeve spring (6) is in a contraction state at the moment, the side pressing page block (21) is in an expansion state, and the airplane part needing pressing sleeve is placed on the lower pressing sleeve base (16);
s2: controlling the rotating motor (3) to operate to enable the constant-speed rotating rod (12) to rotate at a constant speed, when the constant-speed rotating rod (12) contacts the belt-off blocking column (24), driving the variable-speed rotating blade (22) fixedly connected with the belt-off blocking column (24) to rotate, and enabling the non-return rotating bayonet lock (19) to be separated from the limiting fixed gear (11) and rotate around the limiting fixed gear;
s3: under the action of the solid negative weight (7) and the pressing sleeve spring (6), the upper pressing sleeve block (9) descends in an accelerated manner, the collision between the upper pressing sleeve block and the lower pressing sleeve base (16) is completed, the side pressing hinge block (21) is collided by the upper surface of the hinge accommodating groove (27), and the pressing page blocks (21) on the two sides are bent, so that the airplane parts can be pressed from the two sides, and the pressing sleeve is guaranteed to be compact;
s4: when the upper sleeve pressing block (9) descends in an accelerated mode, the belt-separating stop column (24) rotating in a variable speed mode is separated from the uniform rotating rod (12) rotating in a uniform speed mode, after sleeve pressing is completed, the upper sleeve pressing block (9) ascends in a decelerated mode when moving to the lowest end under the action of inertia force, finally, the non-return rotating bayonet lock (19) is meshed with the limiting fixed gear (11), the whole set of sleeve pressing operation is completed, the initial state is recovered, and next driving of the uniform rotating rod (12) is waited.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111468787.0A CN114134738B (en) | 2021-12-03 | 2021-12-03 | Airplane part directional double-sided rapid pressing sleeve machining process and device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111468787.0A CN114134738B (en) | 2021-12-03 | 2021-12-03 | Airplane part directional double-sided rapid pressing sleeve machining process and device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114134738A true CN114134738A (en) | 2022-03-04 |
| CN114134738B CN114134738B (en) | 2023-01-17 |
Family
ID=80388105
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111468787.0A Active CN114134738B (en) | 2021-12-03 | 2021-12-03 | Airplane part directional double-sided rapid pressing sleeve machining process and device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114134738B (en) |
Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202039234U (en) * | 2011-04-10 | 2011-11-16 | 张继刚 | Steel wire loop pressing machine |
| KR101119223B1 (en) * | 2011-07-29 | 2012-03-21 | (주)대성기업디에스 | Rope twisting apparatus |
| CN202719074U (en) * | 2012-07-27 | 2013-02-06 | 力福汀钢绳（上海）有限公司 | Pressing inhaul cable of steel rope aluminium sheath joint |
| CN105710262A (en) * | 2014-12-03 | 2016-06-29 | 丁克芳 | Steel rope pressing and sleeving machine |
| CN207031901U (en) * | 2017-06-30 | 2018-02-23 | 江苏艾可森钢绳有限公司 | A kind of steel wire rope sleeve pressing machine |
| CN207619707U (en) * | 2017-10-10 | 2018-07-17 | 江苏星泰液压机械设备制造有限公司 | A kind of steel wire rope sleeve pressing machine |
| CN208279941U (en) * | 2018-04-12 | 2018-12-25 | 青岛建邦士金属制品有限公司 | Steel wire rope sleeve pressing machine |
| CN209048355U (en) * | 2018-09-20 | 2019-07-02 | 深圳市泉晟生物科技有限公司 | A kind of semi-automatic semen collection device |
| CN110039489A (en) * | 2019-05-17 | 2019-07-23 | 黑龙江泓瑞科技有限公司 | A kind of core tube acts device |
| CN209869784U (en) * | 2019-03-20 | 2019-12-31 | 李文 | A invoice finishing device for financial accounting |
| CN211036944U (en) * | 2019-11-13 | 2020-07-17 | 广东中交纵横建设咨询有限公司 | Highway engineering roadbed compactness field detection device |
| CN212235735U (en) * | 2020-05-07 | 2020-12-29 | 山东亚安建筑工程有限公司 | Elevating system for fire control |
| CN212270518U (en) * | 2020-01-15 | 2021-01-01 | 上海鸣士工业科技有限公司 | Wear-resisting corrosion-resistant wire rope pre-compression device |
| CN112298601A (en) * | 2020-10-16 | 2021-02-02 | 游加明 | Automatic horizontal calibration device for unmanned aerial vehicle landing |
| CN213196638U (en) * | 2020-09-22 | 2021-05-14 | 广州速益电气机械有限公司 | Hydraulic clamp with high clamping stability for machine tool |
| CN213585440U (en) * | 2020-11-27 | 2021-06-29 | 黄靖仪 | Mechanical energy storage structure convenient to install on motor shaft |
| CN113086805A (en) * | 2021-03-24 | 2021-07-09 | 苏州东方富力电梯部件有限公司 | Eccentric wheel and brake disc meshed throwing type machine room-free speed limiter |
| CN113356576A (en) * | 2021-06-30 | 2021-09-07 | 东莞市九豪投资有限公司 | Support device and protection device for early-dismantling template |
| CN113427533A (en) * | 2021-05-25 | 2021-09-24 | 佛山市巧弁科技有限公司 | A cutting equipment that is used for internet commodity to sell wrapping bag is moulded to paper |
-
2021
- 2021-12-03 CN CN202111468787.0A patent/CN114134738B/en active Active
Patent Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202039234U (en) * | 2011-04-10 | 2011-11-16 | 张继刚 | Steel wire loop pressing machine |
| KR101119223B1 (en) * | 2011-07-29 | 2012-03-21 | (주)대성기업디에스 | Rope twisting apparatus |
| CN202719074U (en) * | 2012-07-27 | 2013-02-06 | 力福汀钢绳（上海）有限公司 | Pressing inhaul cable of steel rope aluminium sheath joint |
| CN105710262A (en) * | 2014-12-03 | 2016-06-29 | 丁克芳 | Steel rope pressing and sleeving machine |
| CN207031901U (en) * | 2017-06-30 | 2018-02-23 | 江苏艾可森钢绳有限公司 | A kind of steel wire rope sleeve pressing machine |
| CN207619707U (en) * | 2017-10-10 | 2018-07-17 | 江苏星泰液压机械设备制造有限公司 | A kind of steel wire rope sleeve pressing machine |
| CN208279941U (en) * | 2018-04-12 | 2018-12-25 | 青岛建邦士金属制品有限公司 | Steel wire rope sleeve pressing machine |
| CN209048355U (en) * | 2018-09-20 | 2019-07-02 | 深圳市泉晟生物科技有限公司 | A kind of semi-automatic semen collection device |
| CN209869784U (en) * | 2019-03-20 | 2019-12-31 | 李文 | A invoice finishing device for financial accounting |
| CN110039489A (en) * | 2019-05-17 | 2019-07-23 | 黑龙江泓瑞科技有限公司 | A kind of core tube acts device |
| CN211036944U (en) * | 2019-11-13 | 2020-07-17 | 广东中交纵横建设咨询有限公司 | Highway engineering roadbed compactness field detection device |
| CN212270518U (en) * | 2020-01-15 | 2021-01-01 | 上海鸣士工业科技有限公司 | Wear-resisting corrosion-resistant wire rope pre-compression device |
| CN212235735U (en) * | 2020-05-07 | 2020-12-29 | 山东亚安建筑工程有限公司 | Elevating system for fire control |
| CN213196638U (en) * | 2020-09-22 | 2021-05-14 | 广州速益电气机械有限公司 | Hydraulic clamp with high clamping stability for machine tool |
| CN112298601A (en) * | 2020-10-16 | 2021-02-02 | 游加明 | Automatic horizontal calibration device for unmanned aerial vehicle landing |
| CN213585440U (en) * | 2020-11-27 | 2021-06-29 | 黄靖仪 | Mechanical energy storage structure convenient to install on motor shaft |
| CN113086805A (en) * | 2021-03-24 | 2021-07-09 | 苏州东方富力电梯部件有限公司 | Eccentric wheel and brake disc meshed throwing type machine room-free speed limiter |
| CN113427533A (en) * | 2021-05-25 | 2021-09-24 | 佛山市巧弁科技有限公司 | A cutting equipment that is used for internet commodity to sell wrapping bag is moulded to paper |
| CN113356576A (en) * | 2021-06-30 | 2021-09-07 | 东莞市九豪投资有限公司 | Support device and protection device for early-dismantling template |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114134738B (en) | 2023-01-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201702965U (en) | Servo press transmission device | |
| CN204412956U (en) | A kind of single armed multi-spindle machining hand | |
| CN206484276U (en) | A kind of new two stations panoramic table | |
| CN208410818U (en) | A kind of knuckle joint press of bias fluted disc driving | |
| CN108789480A (en) | Cooperate Robot Modular Joint and cooperation robot | |
| CN114134738B (en) | Airplane part directional double-sided rapid pressing sleeve machining process and device | |
| CN103879003B (en) | A kind of escapement forcing press | |
| CN112593900A (en) | Tower type oil pumping unit | |
| CN102717018A (en) | Connecting rod press machine with swinging guide rod | |
| CN202571046U (en) | Small precision squeeze riveter | |
| CN213980765U (en) | Tower type oil pumping unit | |
| CN215704303U (en) | Novel servo punch press | |
| CN110077190A (en) | A kind of single direction rotation power generator for Vibration of Vehicle Suspensions energy regenerating | |
| CN201720075U (en) | Energy-saving jaw crusher | |
| CN212762112U (en) | Drilling and tapping device for motorcycle brake drum production | |
| CN103084526B (en) | Frequency conversion type double disk friction screw press | |
| CN113500804A (en) | Crank press with overload protection | |
| CN101722667B (en) | Jacking and slewing mechanism for packing machine | |
| CN102688948B (en) | Small-sized precision squeeze riveter | |
| CN202064899U (en) | Energy-saving oil pumping unit | |
| CN216175672U (en) | Hydraulic punching machine for processing metal iron ring | |
| CN211971559U (en) | Manual control cantilever crane | |
| CN204003301U (en) | Directional force-generating device | |
| CN216328310U (en) | Lower limb exoskeleton power assisting device | |
| CN216371878U (en) | Large-stroke clamping jaw |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |