Synchronous lifting mechanism of telescopic machine

Abstract

The synchronous lifting mechanism is located on the telescopic machine, the telescopic machine comprises a base and a machine body, one end of the machine body is connected to the base in a pivoted mode, and the other end of the machine body can ascend and descend under the action of the synchronous lifting mechanism. The synchronous lifting mechanism comprises a lifting cross beam which is fixedly mounted at the bottom of the machine body; the lifting supporting assembly is located between the base and the lifting cross beam and comprises two supporting parts arranged in the width direction of the machine body, each supporting part comprises a supporting base and a moving part installed on the supporting base, and the moving parts are hinged to the lifting cross beam; the two moving parts can synchronously ascend and descend under the action of the synchronous driving part; and the auxiliary supporting assembly is located between the two supporting parts and comprises at least one set of telescopic rods arranged in the width direction of the machine body, and the two ends of each telescopic rod are hinged to the base and the lifting cross beam correspondingly. According to the utility model, the inclination phenomenon of the machine body caused by unbalance loading is effectively reduced, and the reliability of cargo transportation of the telescopic machine is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of telescopic conveyors, in particular to a synchronous lifting mechanism of a telescopic conveyor. Background Art

[0002] Telescopic conveyors are ordinary conveyors with telescopic conveying sections added to them, so that the conveyor can be freely extended and retracted in the length direction, and the length of the conveyor can be controlled at any time. Telescopic conveyors can transport materials in both directions, and can be used in conjunction with other conveying equipment and material sorting systems to achieve automated production of material storage or vehicle loading and unloading, and have been widely used in various industries.

[0003] In order to match the height of the cargo platform, a telescopic crane is usually equipped with a lifting mechanism to realize the lifting and movement of the fuselage. However, the existing lifting mechanism is usually set in the middle of the lower end of the fuselage, and the lifting of the fuselage is achieved by a single-point lifting drive assisted by side support. However, once this method occurs with an unbalanced load or a side support failure, it will cause the fuselage to tilt or even the cargo to fall. Utility Model Content

[0004] In order to overcome the above-mentioned shortcomings, the purpose of the utility model is to provide a synchronous lifting mechanism of a telescopic machine, which effectively reduces the body tilt phenomenon caused by unbalanced loading and improves the reliability of cargo transportation of the telescopic machine.

[0005] In order to achieve the above purpose, the technical solution adopted by the utility model is: a synchronous lifting mechanism of a telescopic machine, located on the telescopic machine, the telescopic machine includes a base and a fuselage, one end of the fuselage is pivotally connected to the base, and the other end can be lifted and moved under the action of the synchronous lifting mechanism; the synchronous lifting mechanism includes:

[0006] A lifting beam, fixedly mounted on the bottom of the fuselage;

[0007] A lifting support assembly is located between the base and the lifting beam, and includes two support parts arranged along the width direction of the fuselage, each of the support parts includes a support base and a moving part installed on the support base, and the moving part is hinged to the lifting beam; and the two moving parts can be lifted and lowered synchronously under the action of a synchronous driving part;

[0008] The auxiliary support assembly is located between the two support parts, and includes at least one group of telescopic rods arranged along the width direction of the fuselage, and the two ends of the telescopic rods are respectively hinged to the base and the lifting beam.

[0009] The beneficial effects of the synchronous lifting mechanism of the utility model are:

[0010] The cooperation between the lifting support assembly and the auxiliary support assembly can ensure the stable support of the lifting beam, and then ensure the stability of the fuselage fixed to the lifting beam; and the two support parts are arranged along the width direction of the fuselage, and the moving parts of the two support parts are driven to rise and fall synchronously through the synchronous driving parts, which not only ensures the stable support of the fuselage by the two support parts to avoid the fuselage from tilting along its width direction, but also ensures the uniformity of the lifting range on both sides of the width direction of the fuselage. Among them, the moving parts are hinged to the lifting beam, and the two ends of the telescopic rod are hinged to the base and the lifting beam to ensure the smooth lifting and swinging of the fuselage.

[0011] Compared with the single-point support in the prior art, the present application improves the stable support for the fuselage by setting up two support parts, effectively reduces the fuselage tilting phenomenon caused by unbalanced loading, and improves the reliability of telescopic crane cargo transportation.

[0012] Specifically, the moving part includes a screw lift, and the synchronous driving part includes a synchronous shaft arranged in the horizontal direction, and the two ends of the synchronous shaft are respectively connected to the two screw lifts through couplings to synchronously drive the screws of the two screw lifts to move. The synchronous shaft is connected to the two screw lifts through the coupling, which ensures the synchronous shaft's driving synchronization of the two screw lifts, thereby ensuring the synchronization of the screw movement of the two screw lifts.

[0013] Furthermore, one end of the synchronous shaft passes through the screw lifter and is connected to a driving hand wheel to facilitate driving the synchronous shaft.

[0014] Furthermore, the screw of the screw lift is coaxially arranged in the support base, and the upper end thereof is provided with a hinge joint for being hinged to the lifting beam. The moving direction of the screw can be guided by the support base.

[0015] Furthermore, the base is provided with a mounting seat corresponding to the support base; the support base includes a hollow seat body, and the lower end of the seat body is integrally provided with a bending sleeve plate that can be mounted on the corresponding mounting seat and pivotally connected to the mounting seat. The pivot connection between the bending sleeve plate and the mounting seat can cooperate with the lifting and swinging of the fuselage.

[0016] Furthermore, two limit parts are arranged along the width direction of the fuselage and can be folded between the fuselage and the base, and the two free ends of each limit part are respectively pivotally connected to the lifting beam and the base, and the two limit parts are fixedly connected by a connecting beam. The setting of the limit parts can not only enhance the support stability of the lifting beam and the fuselage, but also ensure the stability of the distance between the two limit parts through the connecting beam, thereby suppressing the left and right shaking of the fuselage during the lifting process.

[0017] Further, the limiting part includes an upper support rod and a lower support rod, the ends of the upper support rod and the lower support rod that are close to each other are pivotally connected through a connecting structure, and the ends that are far away from each other are pivotally connected to the lifting beam and the base respectively; and the upper support rod and the lower support rod of any of the limiting parts are located on the same vertical plane.

[0018] When the fuselage swings downward, the upper support rod receives a downward driving force, and the upper support rod is immediately folded in the direction close to the lower support rod (i.e., the contraction action of the limiter); when the fuselage swings upward, the upper support rod receives an upward driving force, and the upper support rod is immediately expanded in the direction away from the lower support rod (i.e., the extension action of the limiter). The upper support rod and the lower support rod are pivotally connected to realize the vertical telescopic action of the limiter as a whole, so as to ensure the lifting and lowering movement of the fuselage; the upper support rod and the lower support rod of the limiter are limited to the same vertical plane, so that the upper support rod and the lower support rod can only receive the vertical driving force due to the lifting and lowering movement of the fuselage, thereby avoiding the influence of the left and right shaking of the fuselage caused by the inclination of the limiter itself.

[0019] Specifically, the connection structure includes a pivot plate, a pivot hole and an axle rod, wherein the pivot hole is arranged on the lower support rod along the width direction of the fuselage; the axle rod is inserted into the pivot hole, and the pivot plate is mounted thereon; the pivot plate is fixedly connected to the upper support rod. Specifically, one end of the axle rod is inserted into the pivot hole of one of the limiting parts, and the other end is inserted into the pivot hole of another limiting part. That is, the two limiting parts share one axle rod, and such an arrangement can limit the spacing between the two limiting parts and avoid the spacing between the two limiting parts from changing. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the structure of the telescopic machine according to an embodiment of the utility model;

[0021] Figure 2 for Figure 1 A partial enlarged view of the middle A area;

[0022] Figure 3 This is a structural schematic diagram of the synchronous lifting mechanism of an embodiment of the utility model;

[0023] Figure 4 This is a schematic diagram of the structure of the support base of an embodiment of the utility model;

[0024] Figure 5 It is a structural schematic diagram of the real-time limiting part of the utility model.

[0025] In the figure:

[0026] 1-base; 11-mounting seat;

[0027] 2- fuselage;

[0028] 3-Lifting beam;

[0029] 4-lifting support assembly; 41-support base; 411-seat body; 412-bending sleeve; 42-screw lifter; 421-screw; 43-synchronizing shaft; 431-driving hand wheel; 44-coupling;

[0030] 5- auxiliary support assembly; 51- telescopic rod;

[0031] 6-limiting part; 61-upper support rod; 62-lower support rod; 63-pivot plate; 64-axis rod;

[0032] 7- Connecting beam. DETAILED DESCRIPTION

[0033] The preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making a clearer and more definite definition of the protection scope of the present invention.

[0034] Example

[0035] See attached Figure 1-2 As shown, a synchronous lifting mechanism of a telescopic machine of the utility model is located on the telescopic machine, and the telescopic machine includes a base 1 and a fuselage 2. One end of the fuselage 2 is pivotally connected to the base 1, and the other end can be lifted and moved under the action of the synchronous lifting mechanism; the synchronous lifting mechanism includes a lifting beam 3, a lifting support assembly 4, and an auxiliary support assembly 5, wherein the lifting beam 3 is fixedly installed at the bottom of the fuselage 2. The lifting support assembly 4 is located between the base 1 and the lifting beam 3, and includes two support parts arranged along the width direction of the fuselage, each support part includes a support base 41 and a moving part installed on the support base 41, and the moving part is hinged to the lifting beam 3; and the two moving parts can be lifted and lowered synchronously under the action of the synchronous driving part. The auxiliary support assembly 5 is located between the two support parts, and includes at least one group of telescopic rods 51 arranged along the width direction of the fuselage, and the two ends of the telescopic rods 51 are respectively hinged to the base 1 and the lifting beam 3.

[0036] The lifting support assembly 4 cooperates with the auxiliary support assembly 5 to ensure stable support for the lifting beam 3, thereby ensuring the stability of the fuselage 2 fixed to the lifting beam 3; and the two support parts are arranged along the width direction of the fuselage, and the moving parts of the two support parts are driven to rise and fall synchronously by the synchronous driving parts, which not only ensures the stable support of the fuselage 2 by the two support parts to avoid the fuselage 2 from tilting along its width direction, but also ensures the uniformity of the lifting range on both sides of the width direction of the fuselage. Among them, the moving parts are hinged to the lifting beam 3, and the two ends of the telescopic rod 51 are hinged to the base 1 and the lifting beam 3 to ensure the smooth lifting and swinging of the fuselage 2.

[0037] In some embodiments, see Appendix Figure 2-3As shown, the moving part includes a screw lift 42, and the synchronous driving part includes a synchronous shaft 43 arranged in the horizontal direction. The two ends of the synchronous shaft 43 are respectively connected to the two screw lifts 42 through a coupling 44 to synchronously drive the screws 421 of the two screw lifts 42 to move. Furthermore, one end of the synchronous shaft 43 passes through the screw lift 42 and is connected to a driving hand wheel 431 to facilitate driving the synchronous shaft 43. The synchronous shaft 43 is connected to the two screw lifts 42 through the coupling 44, which ensures that when the driving hand wheel 431 is rotated, the synchronous shaft 43 can be driven to synchronously drive the two screw lifts 42, thereby ensuring the synchronization of the screw movement of the two screw lifts 42.

[0038] Furthermore, the screw of the screw lift 42 is coaxially inserted into the support base 41 , and an articulated joint is provided at the upper end thereof for being articulated with the lifting beam 3 .

[0039] In some embodiments, see Appendix Figure 5 As shown, the base 1 is provided with a mounting seat 11 corresponding to the support base 41. The support base 41 includes a hollow seat body 411, and the lower end of the seat body 411 is integrally provided with a bending sleeve 412 that can be mounted on the corresponding mounting seat 11 and is pivotally connected to the mounting seat 11. The pivot connection between the bending sleeve 412 and the mounting seat 11 realizes the rotation of the support base 41 relative to the base 1, so that the support base 41 and the screw lift 42 can cooperate with the lifting and lowering swing of the fuselage 2 in the process of driving the fuselage 2 to lift.

[0040] In the prior art, the fuselage may sway left and right (sway along its width direction) during the lifting process. In order to suppress the left and right swaying of the fuselage 2, in some embodiments, see the attached Figure 4-5 As shown, two limit parts 6 arranged along the width direction of the fuselage and capable of being folded are further provided between the fuselage 2 and the base 1, and the two free ends of each limit part 6 are respectively pivotally connected to the lifting beam 3 and the base 1, and the two limit parts 6 are fixedly connected by a connecting beam 7. The setting of the limit parts 6 can not only enhance the support stability of the lifting beam 3 and the fuselage 2, but also ensure the stability of the distance between the two limit parts 6 through the connecting beam 7, thereby suppressing the left and right shaking of the fuselage during the lifting process.

[0041] Specifically, the position-limiting part 6 includes an upper support rod 61 and a lower support rod 62. The ends of the upper support rod 61 and the lower support rod 62 that are close to each other are pivotally connected through a connecting structure, and the ends that are far away from each other are respectively pivotally connected to the lifting beam 3 and the base 1. The upper support rod 61 and the lower support rod 62 of any position-limiting part 6 are located on the same vertical plane.

[0042] When the fuselage 2 swings downward, the upper support rod 61 receives a downward driving force, and the upper support rod 61 is folded toward the lower support rod 62; when the fuselage 2 swings upward, the upper support rod 61 receives an upward driving force, and the upper support rod 61 is unfolded away from the lower support rod 62. The upper support rod 61 and the lower support rod 62 are pivotally connected to realize the folding and unfolding action of the limiting part 6 as a whole, so as to ensure the lifting and lowering movement of the fuselage 2; the upper support rod 61 and the lower support rod 62 of the limiting part 6 are limited to the same vertical plane, so that the upper support rod 61 and the lower support rod 62 can only receive the vertical driving force due to the lifting and lowering movement of the fuselage 2, thereby avoiding the influence of the left and right shaking of the fuselage 2 caused by the inclination of the limiting part 6 itself.

[0043] In some embodiments, see Appendix Figure 5 As shown, the connection structure includes a pivot plate 63, a pivot hole and a shaft rod 64, and the pivot hole is set on the lower support rod 62 along the width direction of the fuselage. The shaft rod 64 is inserted into the pivot hole, and the pivot plate 63 is mounted thereon. The pivot plate 63 is fixedly connected to the upper support rod 61. Furthermore, one end of the shaft rod 64 is inserted into the pivot hole of one limit part 6, and the other end is inserted into the pivot hole of the other limit part 6. That is, the two limit parts 6 share one shaft rod 64. Such a setting can not only ensure the synchronous folding of the two limit parts 6, but also enhance the stability of the spacing between the two limit parts 6 by using the shaft rod 64, so as to minimize the phenomenon of the left and right shaking of the fuselage caused by the left and right shaking between the two limit parts 6.

[0044] In the limiting portion 6, since the ends of the upper support rod 61 and the lower support rod 62 that are away from each other are limited by the lifting beam 3 and the base 1 respectively, the possibility of left and right shaking is low, but the ends of the upper support rod 61 and the lower support rod 62 that are close to each other lack a limit, and left and right shaking may occur during the movement. Therefore, in some embodiments, the connecting beam 7 is arranged near the junction of the upper support rod 61 and the lower support rod 62.

[0045] The above implementation modes are only for illustrating the technical concept and features of the utility model, and their purpose is to allow people familiar with this technology to understand the content of the utility model and implement it. It cannot be used to limit the protection scope of the utility model. Any equivalent changes or modifications made according to the spirit of the utility model should be included in the protection scope of the utility model.

Claims

1. A synchronous lifting mechanism of a telescopic machine, located on the telescopic machine, the telescopic machine comprises a base and a body, one end of the body is pivotally connected to the base, and the other end can be lifted and moved under the action of the synchronous lifting mechanism; characterized in that: The synchronous lifting mechanism comprises A lifting beam, fixedly mounted on the bottom of the fuselage; A lifting support assembly is located between the base and the lifting beam, and includes two support parts arranged along the width direction of the fuselage, each of the support parts includes a support base and a moving part installed on the support base, and the moving part is hinged to the lifting beam; and the two moving parts can be lifted and lowered synchronously under the action of a synchronous driving part; The auxiliary support assembly is located between the two support parts, and includes at least one group of telescopic rods arranged along the width direction of the fuselage, and the two ends of the telescopic rods are respectively hinged to the base and the lifting beam.

2. The synchronous lifting mechanism according to claim 1, characterized in that: The moving part includes a screw lift, and the synchronous driving part includes a synchronous shaft arranged in the horizontal direction. The two ends of the synchronous shaft are respectively connected to the two screw lifts through couplings to synchronously drive the screws of the two screw lifts to move.

3. The synchronous lifting mechanism according to claim 2, characterized in that: One end of the synchronous shaft passes through the screw lifter and is connected to a driving hand wheel.

4. The synchronous lifting mechanism according to claim 2, characterized in that: The screw of the screw lift is coaxially inserted into the support base, and the upper end of the screw is provided with a hinge joint for hinged connection with the lifting beam.

5. The synchronous lifting mechanism according to claim 1, characterized in that: The base is provided with a mounting seat corresponding to the supporting base one by one; the supporting base includes a hollow seat body, and the lower end of the seat body is integrally provided with a bending sleeve plate that can be sleeved on the corresponding mounting seat and is pivotally connected to the mounting seat.

6. The synchronous lifting mechanism according to claim 1, characterized in that: Two limiting parts are arranged along the width direction of the fuselage and can be folded between the fuselage and the base. The two free ends of each limiting part are pivotally connected to the lifting beam and the base respectively, and the two limiting parts are fixedly connected by a connecting beam.

7. The synchronous lifting mechanism according to claim 6, characterized in that: The limiting part includes an upper support rod and a lower support rod, the ends of the upper support rod and the lower support rod that are close to each other are pivotally connected through a connecting structure, and the ends that are far away from each other are pivotally connected to the lifting beam and the base respectively; and the upper support rod and the lower support rod of any of the limiting parts are located on the same vertical plane.

8. The synchronous lifting mechanism according to claim 7, characterized in that: The connection structure includes a pivot plate, a pivot hole and an axle rod, wherein the pivot hole is arranged on the lower support rod along the width direction of the fuselage; the axle rod is inserted into the pivot hole, and the pivot plate is mounted thereon; the pivot plate is fixedly connected to the upper support rod.

9. The synchronous lifting mechanism according to claim 8, characterized in that: One end of the shaft rod is inserted into the pivot hole of one of the limiting parts, and the other end is inserted into the pivot hole of the other limiting part.

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