CN113104780A - Automatic decoupling aircraft inlet channel internal working platform - Google Patents
Automatic decoupling aircraft inlet channel internal working platform Download PDFInfo
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- CN113104780A CN113104780A CN202110343994.7A CN202110343994A CN113104780A CN 113104780 A CN113104780 A CN 113104780A CN 202110343994 A CN202110343994 A CN 202110343994A CN 113104780 A CN113104780 A CN 113104780A
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- linear guide
- guide rail
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- assembly
- operation assembly
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
- B66F11/00—Lifting devices specially adapted for particular uses not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Manufacturing & Machinery (AREA)
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- Aviation & Aerospace Engineering (AREA)
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- Mechanical Engineering (AREA)
- Structural Engineering (AREA)
- Automatic Assembly (AREA)
Abstract
The invention discloses an automatic decoupling aircraft inlet internal working platform, which comprises: the top operation table is provided with an edge at the upper end, a primary operation assembly is arranged below the top operation table, the top operation table is connected with the primary operation assembly through a coupling mechanism, the primary operation assembly is in sliding sleeve connection with a secondary operation assembly, and the secondary operation assembly is in sliding sleeve connection with a tertiary operation assembly; the three-level operation assembly comprises a three-level sleeve with a bottom surface, a driving module is fixed on the bottom surface of the three-level sleeve, the driving module comprises an oil cylinder top seat, and the oil cylinder top seat is fixed at the upper end of the one-level operation assembly. The invention adopts a three-level structure, has a large working range and is suitable for the working condition that the operation space of the air inlet channel is narrow; automatic decoupling is realized, and two working states of air inlet channel disassembly and assembly and station transfer can be quickly switched; meanwhile, the invention has simple structure, stable operation and easy maintenance.
Description
Technical Field
The invention relates to the technical field of aviation manufacturing and maintenance, in particular to an automatic decoupling aircraft air inlet internal working platform.
Background
The assembly of the aircraft wing body can be divided into the stages of positioning preassembly, automatic hole making, mounting sealing, undercarriage overturning, finish machining, undercarriage arranging and the like in sequence, wherein the positioning preassembly stage relates to repeated disassembly and assembly of the composite material integral air inlet channel, and the automatic hole making and mounting sealing stage relates to the station transfer of the composite material integral air inlet channel.
In order to ensure that the product can be quickly and accurately transferred between the traditional assembly station and the automatic station, a special track transfer system is designed at the bottom of the automatic assembly production line. In the positioning preassembly stage, the working platform in the air inlet channel is lifted along the Z axis, in the automatic hole making and sealing mounting stage, the air inlet channel moves along the X axis along with the transfer station system, and the switching speed of the product in different working states is influenced by the coupling relation between the air inlet channel and the transfer station system. Therefore, the assembly efficiency of the wing body of the airplane can be improved by rapidly switching the two working states of the air inlet channel disassembly and assembly and the station transfer.
The specification with the publication number of CN209739384U discloses a lifting platform for aircraft maintenance, which comprises a base and an operating platform, wherein a hydraulic telescopic arm is vertically arranged on the base, the top end of the hydraulic telescopic arm is detachably connected with a fixed seat, and a slide rail is arranged on the fixed seat; the bottom surface of the operating platform is provided with a pulley matched with the slide rail, and the pulley is provided with a sliding motor; the bottom surface of the base is provided with a universal wheel with a self-locking structure. The lifting of the operating platform is controlled mainly by the hydraulic telescopic arm, so that the parts with different heights can be maintained conveniently; meanwhile, the operation platform can horizontally slide relative to the fixed seat, so that the horizontal maintenance range of the operation platform is further expanded, and the problem that the whole operation platform needs to be frequently moved when adjacent parts are maintained is avoided. The control switch controls the sliding motor to be turned on or off, and the horizontal position of the operation platform is moved.
The specification with the publication number of CN212581465U discloses a high-stability hydraulic lifting platform, which comprises a base, a lifting component, a working platform and a stabilizing component, wherein a hydraulic rod is arranged on the upper surface of the base, the top of the hydraulic rod is connected with a lifting support, the top of the lifting support is connected with the bottom surface of the working platform, the bottom of the lifting support is respectively connected with a first fixed block and a second fixed block, the first fixed block and the second fixed block are both arranged on the upper surface of the base, four corners of the bottom surface of the base are both connected with connecting rods, the bottom of each connecting rod is connected with a stabilizing component for enhancing the stability of the whole device, the device is moved by a wheel, a user presses a brake pad to abut against the wheel through the pressing pad, the wheel can be prevented from moving randomly, the potential safety hazard of the user is avoided, and the contact area, the lifting platform is prevented from moving and turning on one's side at will, the safety of the high-altitude operation of the operators is improved, and the practicability of the whole device is improved.
Disclosure of Invention
The invention aims to provide an automatic decoupling aircraft air inlet internal working platform which is used for dismounting and mounting a composite material integral air inlet of an aircraft, so that the product can be quickly and accurately transferred between different stations, and the assembly efficiency of an aircraft wing body is improved.
An automatically decoupled aircraft inlet internal work platform, comprising:
the top operation table is provided with an edge at the upper end, a primary operation assembly is arranged below the top operation table, the top operation table is connected with the primary operation assembly through a coupling mechanism, the primary operation assembly is in sliding sleeve connection with a secondary operation assembly, and the secondary operation assembly is in sliding sleeve connection with a tertiary operation assembly; the three-level operation assembly comprises a three-level sleeve with a bottom surface, a driving module is fixed on the bottom surface of the three-level sleeve, the driving module comprises an oil cylinder top seat, and the oil cylinder top seat is fixed at the upper end of the one-level operation assembly.
The driving module operates to push the primary operating assembly to ascend, and when the primary operating assembly ascends along the Z axis, the primary operating assembly is coupled with the top operating platform through the coupling mechanism to push the top operating platform to move upwards to a target position; after the operation is completed, the driving module runs, the primary operation assembly descends, the primary operation assembly and the secondary operation assembly sequentially contract, the working platform inside the aircraft air inlet channel contracts into the base of the rail system of the transfer station, the top operation platform is automatically decoupled through the coupling mechanism, and the edge of the top operation platform is clamped at the table top of the shape preserving system motion sliding table, so that the top operation platform stops on the shape preserving system motion sliding table.
The coupling mechanism comprises a clamping hook component connected with the lower end of the top operating platform and a connecting rod component connected with the upper end of the primary operating component; the two sides of the clamping hook component are respectively provided with a chute with a downward opening, the connecting rod component comprises a connecting rod base, a spring part, two rocking rods and a connecting rod, the two rocking rods are respectively hinged to the two sides of the connecting rod base, the connecting rod is connected with the two rocking rods, the spring part is pressed between the connecting rod and the connecting rod base, and the connecting rod is abutted to the chute in a coupling state of the coupling mechanism. When the first-stage operating assembly is jacked up along the Z axis, a hook assembly of a coupling mechanism connected to the lower end of the top operating platform is pressed downwards, and the connecting rod slides into the chute under the action of the spring part to form coupling; when one-level operation subassembly descended along the Z axle, top operation panel and the trip subassembly of being connected rather than stop on shape preserving system motion slip table, the spring part that one-level operation subassembly descends pulling and be connected with the connecting rod, the connecting rod slides out the chute under the action of gravity, carries out automatic decoupling to top operation panel and one-level operation subassembly.
The first-level operation assembly comprises a first-level sleeve, a first-level linear guide rail arranged on one side of the first-level sleeve and a first-level linear guide rail sliding block connected to the first-level linear guide rail, and the oil cylinder top seat is abutted to the top surface of the first-level sleeve through a coupling mechanism.
Preferably, the primary linear guide rail comprises two linear guide rails which are distributed in parallel and are respectively positioned in the middle of two parallel side surfaces of the primary sleeve, so that the sliding connection is more reliable.
Preferably, the top of top operation panel is equipped with the guardrail, guarantees personnel's safety and prevents to arrange the material on the top operation panel in and fall, the guardrail still is equipped with the opening that makes things convenient for personnel and material to come in and go out.
The secondary operation assembly comprises a secondary sleeve, a primary linear guide rail slider mounting seat is fixed at the upper part of the secondary sleeve, a secondary linear guide rail is arranged on one side of the secondary sleeve, and a secondary linear guide rail slider is connected onto the secondary linear guide rail; the first-stage linear guide rail and the second-stage linear guide rail are parallel to each other and are distributed in different planes respectively, and the first-stage linear guide rail slider mounting base is fixedly connected with the first-stage linear guide rail slider respectively, so that unnecessary degrees of freedom between the first-stage operation assembly and the second-stage operation assembly are restrained.
Preferably, the secondary linear guide rail comprises two linear guide rails distributed in parallel and respectively fixed in the middle of two parallel side surfaces of the secondary sleeve.
The three-stage operation assembly comprises a three-stage sleeve and a two-stage linear guide rail slider mounting seat fixed on the upper part of the three-stage sleeve, and the two-stage linear guide rail slider mounting seat is fixedly connected with a two-stage linear guide rail slider.
Preferably, the secondary operation assembly and the tertiary operation assembly are both provided with limiting collision blocks, and the limiting collision blocks are installed on the upper portions of the secondary operation assembly and the tertiary operation assembly and used for controlling and achieving graded ascending movement of a working platform in the air inlet channel of the airplane.
And a limit switch stop block and a limit switch are arranged in the mounting clearance between the tertiary operation assembly and the secondary operation assembly, the limit switch is fixedly connected to the tertiary sleeve through a limit switch seat, the limit switch stop block is fixed on the secondary sleeve, and the maximum working stroke of a working platform in the aircraft air inlet channel is identified through the interaction of the limit switch stop block and the limit switch, so that the operation safety is ensured.
Preferably, the driving module is driven by a hydraulic oil cylinder, an oil cylinder ejection rod of the hydraulic oil cylinder is connected with an oil cylinder ejection seat through a pin shaft and a bearing, the oil cylinder ejection seat is fixed at the upper end of the primary operation assembly, and an oil cylinder base of the hydraulic oil cylinder is fixed at the bottom of the tertiary operation assembly. The movable connection of the pin shaft and the bearing reduces the vibration transmitted to the top operating platform in the operation process of the oil cylinder, and ensures the stability of the top operating platform in motion; the hydraulic oil cylinder is adopted for driving, the running speed is adjustable, and the work is stable.
Compared with the prior art, the invention has the advantages that:
1) the three-stage structure is adopted, the working range is large, and the three-stage structure is suitable for the working condition that the operation space of the air inlet channel is narrow;
2) the first-level operation assembly is automatically separated from the top operation table in a contraction state, so that the coupling between the lifting motion of a working platform in the air inlet channel and the station transferring motion of the air inlet channel is eliminated, and the two working states of the air inlet channel disassembly and assembly and the station transferring are quickly switched;
3) relative motion is realized among all levels of operating platforms through linear guide rails, and the motion precision is high;
4) the invention is provided with a plurality of limiting devices, so that the safety coefficient is higher;
5) the invention has simple structure, stable operation and easy maintenance.
Drawings
FIG. 1 is a schematic structural diagram of an internal working platform of an aircraft air inlet according to an embodiment of the present invention;
FIG. 2 is a schematic cross-sectional view of the internal platform of the aircraft air scoop shown in FIG. 1;
FIG. 3 is an enlarged partial schematic view at A shown in FIG. 2;
FIG. 4 is a schematic structural view of the coupling mechanism shown in FIG. 3;
FIG. 5 is a schematic structural diagram of the driving module shown in FIG. 1;
FIG. 6 is a schematic view of the primary operations module and top station of FIG. 1;
FIG. 7 is a schematic diagram of the secondary operational components shown in FIG. 1;
FIG. 8 is a schematic diagram of the three stage operation assembly shown in FIG. 1.
Detailed Description
As shown in fig. 1 and 2, the platform for the interior of the aircraft air inlet comprises:
the top operation platform is provided with a top operation platform 1 at the edge, a primary operation assembly 2 is arranged below the top operation platform 1, the top operation platform 1 is connected with the primary operation assembly 2 through a coupling mechanism 5, and the primary operation assembly 2 is sequentially sleeved with a secondary operation assembly 3 and a tertiary operation assembly 4 in a sliding manner; the lower part of tertiary operation subassembly 4 is equipped with drive module 6, and drive module 6 drives primary operation subassembly, second grade operation subassembly and tertiary operation subassembly relative slip to top operation panel 1 is gone up and down.
As shown in fig. 3 and 4, the coupling mechanism 5 includes a hook assembly 51 fixed to the lower end of the top operating platform 1, and a link assembly 52 connected to the upper end of the primary operating assembly 2; two sides of the hook assembly 51 are respectively provided with a chute with a downward opening, and the connecting rod assembly 52 comprises a connecting rod base 521, a spring member 522, a rocker 523 and a connecting rod 524. The two rocker arms 523 are respectively hinged to two sides of the connecting rod base 521, the connecting rod 524 is fixed between the two rocker arms 523 and connected with the two rocker arms 523, the spring member 522 is pressed between the connecting rod 524 and the connecting rod base 521, and the connecting rod 524 is positioned in the inclined groove in a coupling state of the coupling mechanism 5.
When the first-stage operating assembly 2 is lifted along the Z axis, the hook assembly 51 of the coupling mechanism 5 connected to the lower end of the top operating platform 1 is pressed downwards, and the connecting rod 524 slides into the inclined groove under the action of the spring piece 522 to form coupling; when one-level operation subassembly 2 descends along the Z axle, top operation panel 1 and the trip subassembly 51 of being connected with it stop on the conformal system motion slip table, and spring part 522 that one-level operation subassembly 2 descends to stimulate to be connected with connecting rod 524, and connecting rod 524 slides out the chute under the action of gravity, carries out automatic decoupling to top operation panel 1 and one-level operation subassembly 2.
As shown in fig. 6, a guardrail is arranged above the top operating platform 1, and an opening is arranged on the side surface of the guardrail and used for entering of people and materials.
One-level operating assembly 2 is including the one-level sleeve pipe 21, one-level linear guide 22 and the one-level linear guide slider 23 that are equipped with the top surface, and one-level linear guide 22 includes two parallel distribution's linear guide, is fixed in the centre department of two sides that are parallel to each other of one-level sleeve pipe 21 respectively, all installs two one-level linear guide sliders 23 on single one-level linear guide 22.
As shown in fig. 7, the secondary operating assembly 3 includes a secondary sleeve 31, a primary linear guide slider mount 32, a secondary linear guide 33, and a secondary linear guide slider 34. The second-stage linear guide rail sliding blocks 34 are connected to the second-stage linear guide rail 33, the second-stage linear guide rail 33 comprises two linear guide rails which are distributed in parallel and fixed in the middle of two parallel side faces of the second-stage sleeve 31 respectively, and the single second-stage linear guide rail 33 is provided with the two second-stage linear guide rail sliding blocks 34. The primary linear guide 22 and the secondary linear guide 33 are parallel to each other and fixed in different planes, respectively.
The number of the first-stage linear guide rail slide block mounting seats 32 is four, and the first-stage linear guide rail slide block mounting seats are respectively fixedly connected with the first-stage linear guide rail slide block 23, so that unnecessary degrees of freedom between the first-stage operation assembly 2 and the second-stage operation assembly 3 are restrained.
As shown in fig. 8, four second-stage linear guide rail slider mounting seats 42 are further fixed to the upper end of the third-stage casing 41, and the second-stage linear guide rail slider mounting seats 42 are respectively fixedly connected to the second-stage linear guide rail sliders 34.
And the secondary operation assembly 3 and the tertiary operation assembly 4 are both provided with limiting collision blocks 7, and the limiting collision blocks 7 are arranged above the secondary operation assembly 3 and the tertiary operation assembly 4 and used for controlling and realizing the graded ascending motion of the working platform in the air inlet passage of the airplane.
Be equipped with limit switch dog and limit switch in tertiary operating assembly 4 and the installation clearance of second grade operating assembly 3, limit switch passes through limit switch seat fixed connection in tertiary sleeve pipe 41, and the limit switch dog is fixed in second grade sleeve pipe 31, through limit switch dog and limit switch's interact, discerns the inside work platform's of aircraft intake maximum working stroke, guarantees the security of operation.
As shown in fig. 5, the driving module 6 is driven by a hydraulic cylinder, a cylinder top rod 64 of the hydraulic cylinder is connected with a cylinder top seat 61 through a pin 62 and a bearing 63, the cylinder top seat 61 is fixed at the upper end of the primary operating assembly 2, and a cylinder base 65 of the hydraulic cylinder is fixed at the bottom of the tertiary operating assembly 4.
The working process of the embodiment is as follows:
1. the working platform in the air inlet channel of the airplane is contracted to an initial state;
2. the auxiliary installation equipment for the composite material integral air inlet channel sends the air inlet channel into position and adjusts the air inlet channel to the initial vertical position;
3. jacking a working platform in the air inlet channel of the airplane to push a top operating platform 1 and an operator to ascend, and completing the preassembling of the air inlet channel and disassembling the air inlet channel by the operator;
4. the working platform in the air inlet channel of the airplane is contracted into the system base;
5. the top operating platform 1 is decoupled from the primary operating assembly 2, the top operating platform 1 stays on the shape preserving system moving sliding table to perform station transfer, and the top operating platform returns to the traditional assembling station after other station positions work;
6. the auxiliary installation equipment for the composite material integral air inlet channel sends the air inlet channel into position and adjusts the air inlet channel to the initial vertical position;
7. the working platform in the air inlet channel of the airplane pushes the top operating platform 1 and operators to ascend, and the operators finish the installation work of the air inlet channel;
8. the working platform in the air inlet channel of the airplane is contracted into the system base;
9. top operation panel 1 and the decoupling zero of one-level operation subassembly 2, top operation panel 1 stops on the conformal system motion slip table, and the product is put on the shelf and is handled under the frame, and the system is ready for next frame assembly work.
Claims (10)
1. An automatic decoupling aircraft inlet internal work platform, comprising:
the top operation platform is provided with a top operation platform (1) with an edge, a primary operation assembly (2) is arranged below the top operation platform (1), the top operation platform (1) is connected with the primary operation assembly (2) through a coupling mechanism (5), and the primary operation assembly (2) is sequentially sleeved with a secondary operation assembly (3) and a tertiary operation assembly (4) in a sliding manner; the lower part of tertiary operation subassembly (4) is equipped with drive module (6), drive module (6) drive one-level operation subassembly, second grade operation subassembly and tertiary operation subassembly relative slip to lift top operation panel (1).
2. The automatically decoupled aircraft inlet internal work platform of claim 1, wherein: the coupling mechanism (5) comprises a clamping hook component (51) connected with the lower end of the top operating platform (1) and a connecting rod component (52) connected with the upper end of the primary operating component (2); the two sides of the hook component (51) are respectively provided with a chute with a downward opening, the connecting rod component (52) comprises a connecting rod base (521), a spring piece (522), two rocking rods (523) respectively hinged to the two sides of the connecting rod base and a connecting rod (524) connected with the two rocking rods (523), the spring piece (522) is pressed between the connecting rod (524) and the connecting rod base (521), and the connecting rod (524) is pressed in the chute in a coupling state of the coupling mechanism (5).
3. The automatically decoupled aircraft inlet internal work platform of claim 1, wherein: the primary operation assembly (2) comprises a primary sleeve (21), a primary linear guide rail (22) arranged on one side of the primary sleeve (21) and a primary linear guide rail sliding block (23) connected to the primary linear guide rail (22).
4. The automatically decoupled aircraft inlet internal work platform of claim 3, wherein: the primary linear guide rail (22) comprises two linear guide rails which are distributed in parallel and are respectively positioned in the middle of two parallel side surfaces of the primary sleeve (21).
5. The automatically decoupled aircraft inlet internal work platform of claim 4, wherein: the secondary operation assembly (3) comprises a secondary sleeve (31), a primary linear guide rail slide block mounting seat (32) is fixed on the upper portion of the secondary sleeve (31), a secondary linear guide rail (33) is arranged on one side of the secondary sleeve (31), and a secondary linear guide rail slide block (34) is connected onto the secondary linear guide rail (33); the first-stage linear guide rail (22) and the second-stage linear guide rail (33) are parallel to each other and distributed in different planes respectively, and the first-stage linear guide rail sliding block mounting seat (32) is fixedly connected with the first-stage linear guide rail sliding block (23) respectively.
6. The automatically decoupled aircraft air scoop internal work platform of claim 5, wherein: the secondary linear guide rail (33) comprises two linear guide rails which are distributed in parallel and are respectively fixed in the middle of two parallel side surfaces of the secondary sleeve (31).
7. The automatically decoupled aircraft air scoop internal work platform of claim 5, wherein: the three-stage operation assembly (4) comprises a three-stage casing pipe (41) and a two-stage linear guide rail slider mounting seat (42) fixed on the upper portion of the three-stage casing pipe (41), and the two-stage linear guide rail slider mounting seat (42) is fixedly connected with a two-stage linear guide rail slider (34).
8. The automatically decoupled aircraft inlet internal work platform of claim 1, wherein: and the upper parts of the secondary operation assembly (3) and the tertiary operation assembly (4) are respectively provided with a limiting collision block (7).
9. The automatically decoupled aircraft inlet internal work platform of claim 1, wherein: and a limit switch stop block and a limit switch are arranged in the mounting gap between the tertiary operation assembly (4) and the secondary operation assembly (3), the limit switch is fixedly connected to the tertiary sleeve (41) through a limit switch seat, and the limit switch stop block is fixed to the secondary sleeve (3).
10. The automatically decoupled aircraft inlet internal work platform of claim 1, wherein: the driving module (6) is driven by a hydraulic oil cylinder, an oil cylinder top rod (64) of the hydraulic oil cylinder is connected with an oil cylinder top seat (61) through a pin shaft (62) and a bearing (63), the oil cylinder top seat (61) is fixed at the upper end of the primary operation assembly (2), and an oil cylinder base (65) of the hydraulic oil cylinder is fixed at the bottom of the tertiary operation assembly (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110343994.7A CN113104780B (en) | 2021-03-31 | 2021-03-31 | Automatic decoupling aircraft air inlet channel internal working platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110343994.7A CN113104780B (en) | 2021-03-31 | 2021-03-31 | Automatic decoupling aircraft air inlet channel internal working platform |
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| Publication Number | Publication Date |
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| CN113104780A true CN113104780A (en) | 2021-07-13 |
| CN113104780B CN113104780B (en) | 2022-06-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110343994.7A Active CN113104780B (en) | 2021-03-31 | 2021-03-31 | Automatic decoupling aircraft air inlet channel internal working platform |
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| EP0038692A1 (en) * | 1980-04-18 | 1981-10-28 | Xerox Corporation | Print wheel aligning apparatus and rotary print wheel |
| JP2005206287A (en) * | 2004-01-21 | 2005-08-04 | Banzai Industries Ltd | Lifting device for vehicle maintenance |
| CN106185715A (en) * | 2016-08-25 | 2016-12-07 | 西安睿诺新能源有限公司 | A kind of mechanical balance counter weight type aircraft service ensures hoistable platform pulley assembly |
| CN206156677U (en) * | 2016-08-25 | 2017-05-10 | 西安睿诺新能源有限公司 | Mechanical balance counterweight type aircraft duties guarantee lift platform |
| CN107673267A (en) * | 2017-11-13 | 2018-02-09 | 佛山市恒爱网络科技有限公司 | Second level stroke device |
| CN207468116U (en) * | 2017-11-02 | 2018-06-08 | 天津宏信设备租赁有限公司 | A kind of movable combined lifting support |
| CN212198366U (en) * | 2020-04-24 | 2020-12-22 | 上海大界机器人科技有限公司 | Stable high-load lifting device |
-
2021
- 2021-03-31 CN CN202110343994.7A patent/CN113104780B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0038692A1 (en) * | 1980-04-18 | 1981-10-28 | Xerox Corporation | Print wheel aligning apparatus and rotary print wheel |
| JP2005206287A (en) * | 2004-01-21 | 2005-08-04 | Banzai Industries Ltd | Lifting device for vehicle maintenance |
| CN106185715A (en) * | 2016-08-25 | 2016-12-07 | 西安睿诺新能源有限公司 | A kind of mechanical balance counter weight type aircraft service ensures hoistable platform pulley assembly |
| CN206156677U (en) * | 2016-08-25 | 2017-05-10 | 西安睿诺新能源有限公司 | Mechanical balance counterweight type aircraft duties guarantee lift platform |
| CN207468116U (en) * | 2017-11-02 | 2018-06-08 | 天津宏信设备租赁有限公司 | A kind of movable combined lifting support |
| CN107673267A (en) * | 2017-11-13 | 2018-02-09 | 佛山市恒爱网络科技有限公司 | Second level stroke device |
| CN212198366U (en) * | 2020-04-24 | 2020-12-22 | 上海大界机器人科技有限公司 | Stable high-load lifting device |
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|---|---|
| CN113104780B (en) | 2022-06-28 |
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