Missile hoist

Abstract

The present application provides a kind of missile sling, including sling assembly, hanger beam and connecting seat, connecting seat is detachably installed at the both ends of hanger beam, sling assembly is at least provided with one at the both ends of connecting seat, sling assembly is detachably connected with connecting seat;Connecting seat includes lifting ring and mounting seat, lifting ring is set above mounting seat, and mounting seat is used to install missile container module;Sling assembly includes loop buckle assembly and sling, one end of sling is set at the end of hanger beam through lifting ring, the other end of sling is combined together through loop buckle assembly, and loop buckle assembly is used to adjust the angle of sling;Connecting ring is fixed on sling, connecting ring has first state and or second state, in first state, connecting ring is buckled with lifting ring, by setting multiple connecting rings of different positions on sling, connecting ring is buckled to lifting ring according to hoisting demand, the force length and angle of sling are changed, so as to realize the load hoisting of full load, half load working condition of standard missile container module.

Description

Technical Field

[0001] This invention relates to the field of missile lifting equipment technology, and more specifically, to a missile lifting equipment. Background Technology

[0002] To meet the requirements of sustained combat capability for missile weapon systems, it is necessary to provide efficient equipment support for the weapon systems and enable rapid loading of missile modules between missile transport and loading vehicles and combat vehicles.

[0003] Existing patent document CN204643707U discloses a missile lifting frame, including two liftable triangular supports, a telescopic beam, two or more trolleys, two or more manual hoists, four brake casters, and a plurality of hooks; the beam is detachably connected to the top of the two supports; each of the two legs of the triangular supports is equipped with a jack at the bottom, and each leg is equipped with a brake caster to move the lifting frame; the trolleys are movably mounted on the beam and can slide back and forth, and each trolley is equipped with a manual hoist underneath.

[0004] The current method of loading weapons and equipment mainly uses cranes and slings to transfer missile modules, which has the following shortcomings:

[0005] 1. When lifting missiles, it is necessary to use slings such as steel wire ropes, and operators need to be on the vehicle to operate them. Locking the lifting equipment is cumbersome and poses safety hazards.

[0006] 2. Due to the different number of missiles in the missile container module, the center of gravity of the load changes, requiring the replacement of different types or lengths of slings, which complicates the equipment and consumes a lot of operation time, thus hindering the improvement of lifting efficiency. Summary of the Invention

[0007] In view of the deficiencies in the prior art, the purpose of this invention is to provide a missile hoisting device.

[0008] According to the present invention, a missile lifting device includes a sling assembly, a lifting beam, and a connecting seat. The connecting seat is detachably installed at both ends of the lifting beam. At least one sling assembly is provided at each end of the connecting seat, and the sling assembly is detachably connected to the connecting seat.

[0009] The connecting seat includes a lifting ring and a mounting seat. The lifting ring is positioned above the mounting seat, and the mounting seat is used to install the missile assembly module.

[0010] The sling assembly includes a ring fastener assembly and a sling. One end of the sling is set at the end of the lifting beam via a lifting ring, and the other end of the sling is joined together by the ring fastener assembly. The ring fastener assembly is used to adjust the angle of the sling.

[0011] A connecting ring is fixed to the sling. The connecting ring has a first state and / or a second state. In the first state, the connecting ring is engaged with the lifting ring.

[0012] Preferably, the ring fastener assembly includes a combination ring and a shackle, the combination ring being fastened to the sling via the shackle, and the sling sliding via the combination ring.

[0013] Preferably, the combined ring includes a large ring and a small ring, wherein the small ring is fastened to the sling by a shackle;

[0014] The small ring comprises two smaller rings, and the larger ring is interlocked with each of the two smaller rings;

[0015] The two straps on the same side are locked in the same small ring.

[0016] Preferably, the sling assembly further includes a traction rope fixed to a connecting ring, wherein in the second state, the traction rope pulls the sling through the connecting ring.

[0017] Preferably, the suspension beam includes longitudinal beams, transverse beams, curved beams, and a skin, wherein the longitudinal beams, transverse beams, and curved beams form a suspension beam frame, and the skin covers the suspension beam frame.

[0018] Preferably, the skin is provided with weight-reducing holes, and the weight-reducing holes include a plurality of holes, which are evenly distributed on the skin.

[0019] Preferably, the mounting base includes a hinge bolt adapter mounting base, which is connected to the hinge bolt pin seat on the missile assembly module.

[0020] Preferably, the connecting ring also has a third state in which the connecting ring is engaged with the shackle.

[0021] Preferably, the sling includes a flexible sling.

[0022] Preferably, the lifting beam includes a rigid lifting beam.

[0023] Compared with the prior art, the present invention has the following beneficial effects:

[0024] 1. This invention achieves full-load and half-load lifting of standard missile assembly modules by setting multiple connecting rings at different positions on the sling and locking the connecting rings to the lifting ring according to the lifting requirements, thereby changing the force-bearing length and angle of the sling.

[0025] 2. This invention improves the stability of hoisting by setting a traction rope fixed on a connecting ring, with the connecting ring serving as the force-bearing point of the traction rope. According to the change in the center of gravity during the hoisting process, the sling can be manually adjusted by the traction rope.

[0026] 3. According to the present invention, a plurality of connection rings at different positions are arranged on the sling, and the connection rings can be buckled with lock catches to retract the sling, so as to prevent the slings from being intertwined with each other;

[0027] 4. According to the present invention, a bent beam is arranged in the lifting beam, and the shape of the bent beam is bent according to the outline shape of the missile containerized module to be lifted, so that the lifting beam can be adapted to lift the missile containerized modules stacked in a triangular arrangement;

[0028] 5. According to the present invention, the sling is configured as a flexible sling, and after the rigid lifting beam is removed, the flexible sling can be wound around the barrel-mounted missile and locked with the connection ring, so as to realize the load hoisting of a single barrel-mounted missile. Brief Description of the Drawings

[0029] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of the non-restrictive embodiments with reference to the following accompanying drawings.

[0030] Figure 1 is a left view of the lifting appliance in a full-load state;

[0031] Figure 2 is a front view of the lifting appliance in a full-load state;

[0032] Figure 3 is a top view of the lifting beam;

[0033] Figure 4 is a front view of the lifting beam;

[0034] Figure 5 is a left view of the lifting beam;

[0035] Figure 6 is an isometric view of the lifting appliance;

[0036] Figure 7 is a schematic view of hoisting in a half-load state.

[0037] As shown in the drawings:

[0038] Sling assembly 1 Longitudinal beam 21

[0039] Combined ring 11 Transverse beam 22

[0040] Large ring 111 Bent beam 23

[0041] Small ring 112 Skin 24

[0042] Shackle 12 Weight-reducing hole 25

[0043] Sling 13 Connection base 3

[0044] Connection ring 131 Mounting base 31

[0045] Pull rope 14 Lifting ring 32

[0046] Hanging beam 2 Missile containerized module 4 DETAILED DESCRIPTION

[0047] The present invention will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that several changes and modifications can be made by those of ordinary skill in the art without departing from the concept of the present invention, and these shall all fall within the protection scope of the present invention.

[0048] As shown in Figures 1 to 5 , a missile lifting sling provided according to the present invention includes a sling assembly 1, a hanging beam 2 and connecting seats 3. The connecting seats 3 are detachably mounted at both ends of the hanging beam 2. At least one sling assembly 1 is respectively arranged at both ends of each connecting seat 3, and the sling assembly 1 is detachably connected with the connecting seat 3. The connecting seat 3 includes a lifting ring 32 and a mounting seat 31. The lifting ring 32 is arranged above the mounting seat 31, and the mounting seat 31 is used for mounting the missile containerized module 4. The sling assembly 1 includes a ring buckle assembly and a sling belt 13. One end of the sling belt 13 is arranged at the end of the hanging beam 2 through the lifting ring 32, and the other end of the sling belt 13 is combined together through the ring buckle assembly, which is used for adjusting the angle of the sling belt 13. A connecting ring 131 is fixed on the sling belt 13, and the connecting ring 131 has a first state and / or a second state. In the first state, the connecting ring 131 is detachably connected with the lifting ring 32.

[0049] Specifically, as shown in Figure 5 , the connecting seat 3 includes a lifting ring 32 and a mounting seat 31, the lifting ring 32 is arranged above the mounting seat 31, the mounting seat 31 at the lower part of the connecting seat 3 is a swing bolt adaptive mounting seat, and the upper part is the lifting ring 32. The swing bolt adaptive mounting seat is connected in a matching manner with the swing bolt pin seat on the missile containerized module 4 for adaptive mounting, so as to fasten the missile containerized module 4 to the lifting sling.

[0050] Specifically, as shown in Figures 3 to 5 , the hanging beam 2 includes longitudinal beams 21, transverse beams 22, bent beams 23 and a skin 24. The longitudinal beams 21, the transverse beams 22 and the bent beams 23 form the frame of the hanging beam 2, and the skin 24 covers the frame of the hanging beam 2. The shape of the bent beam 23 in the hanging beam 2 is bent according to the outer contour shape of the missile containerized module 4 to be lifted, which ensures that the hanging beam 2 can be adapted to lift the missile containerized modules 4 stacked in a delta shape. A plurality of lightening holes 25 are arranged on the skin 24 of the hanging beam 2, and the plurality of lightening holes 25 are evenly arranged on the skin 24, so that the function of the skin 24 to bear the missile containerized module 4 is realized while the weight borne by the lifting sling is reduced.

[0051] Specifically, the sling assembly 1 includes a ring fastener assembly and slings 13. The ring fastener assembly includes a combination ring 11 and a shackle 12. The combination ring 11 is fastened to the slings 13 via the shackle 12, and the slings 13 slide through the combination ring 11. The combination ring 11 includes a large ring 111 and a small ring 112. The small ring 112 is fastened to the slings 13 via the shackle 12. There are two small rings 112, and the large ring 111 is fastened to each of the two small rings 112. The two slings 13 on the same side are locked within the same small ring 112. The angle of the slings 13 can be flexibly adjusted by the sliding of the small ring 112 within the space of the large ring 111. The sling assembly 1 also includes a traction rope 14, which is fixed to a connecting ring 131. In the second state, the traction rope 14 pulls the slings 13 through the connecting ring 131. The connecting ring 131 has a first state and / or a second state. In the first state, the connecting ring 131 is engaged with the lifting ring 32, changing the force-bearing length and angle of the sling 13, thereby enabling full-load and half-load lifting of the missile assembly module 4. In the second state, the traction rope 14 pulls the sling 13 through the connecting ring 131. The connecting ring 131 serves as the force point of the traction rope 14. During the lifting process, if the center of gravity of the load changes, the sling 13 can be manually fine-tuned through the traction rope 14, improving the ease of operation and safety stability of the lifting. The connecting ring 131 also has a third state. In the third state, the connecting ring 131 is engaged with the shackle 12, allowing the sling 13 to be retracted to prevent it from becoming tangled.

[0052] This application employs a lifting device composed of a sling assembly 1 and a lifting beam 2. Specifically, the sling assembly 1 is a flexible sling assembly, the sling 13 includes a flexible sling, and the lifting beam 2 includes a rigid lifting beam. The flexible sling assembly and the rigid lifting beam are combined to form a semi-rigid lifting device. Multiple connecting rings 131 are provided on the sling 13. In addition to the connecting rings 131 at the beginning and end of the sling 13, two to three connecting rings 131 are also provided in the lower middle section of the sling 13. The connecting rings 131 in the middle section can be locked to the lifting ring 32 according to the lifting requirements, or serve as the force point of the traction rope 14. Alternatively, one connecting ring 131 in the middle section can be fastened to the lifting ring 32, and the other connecting ring 131 in the middle section can serve as the force point of the traction rope 14, thereby changing the force-bearing length and angle of the sling 13. This allows for the full-load and half-load lifting of the standard missile container module 4. After removing the rigid lifting beam, the flexible sling 13 can be used to wrap around the bullet and lock it with the connecting ring 131 in the middle section of the sling 13, thus achieving the load lifting of a single bullet. During the lifting process, if the center of gravity of the load changes, the sling 13 can be manually fine-tuned using the traction rope 14 to improve the lifting stability. The semi-rigid multi-purpose lifting device of this invention has a simplified structural design, ensuring the ease, speed, safety, and stability of the lifting operation.

[0053] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0054] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0055] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A missile hoist, characterized in that, It includes a sling assembly (1), a lifting beam (2) and a connecting seat (3). The connecting seat (3) is detachably installed at both ends of the lifting beam (2). At least one sling assembly (1) is provided at each end of the connecting seat (3). The sling assembly (1) and the connecting seat (3) are detachably connected. The connecting seat (3) includes a lifting ring (32) and a mounting seat (31). The lifting ring (32) is positioned above the mounting seat (31), and the mounting seat (31) is used to install the missile assembly module (4). The sling assembly (1) includes a ring fastener assembly and a sling (13). One end of the sling (13) is set at the end of the lifting beam (2) via a lifting ring (32), and the other end of the sling (13) is joined together by the ring fastener assembly. The ring fastener assembly is used to adjust the angle of the sling (13). A connecting ring (131) is fixed on the sling (13). The connecting ring (131) has a first state and / or a second state. In the first state, the connecting ring (131) is fastened to the lifting ring (32). The sling assembly (1) also includes a traction rope (14) which is fixed to a connecting ring (131). In the second state, the traction rope (14) pulls the sling (13) through the connecting ring (131). The suspension beam (2) includes longitudinal beams (21), transverse beams (22), curved beams (23) and skin (24). The longitudinal beams (21), transverse beams (22) and curved beams (23) form the suspension beam (2) frame, and the skin (24) covers the suspension beam (2) frame. The lower part of the mounting base (31) is a hinge bolt adapter mounting base, which is connected to the hinge bolt pin seat on the missile assembly module (4).

2. The missile hoist as described in claim 1, characterized in that, The ring fastener assembly includes a combination ring (11) and a shackle (12). The combination ring (11) is fastened to the sling (13) via the shackle (12), and the sling (13) slides through the combination ring (11).

3. The missile hoist as described in claim 2, characterized in that, The combined ring (11) includes a large ring (111) and a small ring (112), wherein the small ring (112) is fastened to the sling (13) by a shackle (12); The small ring (112) includes two, and the large ring (111) is interlocked with the two small rings (112) respectively; The two straps (13) on the same side are locked in the same small ring (112).

4. The missile hoist as described in claim 1, characterized in that, The skin (24) is provided with weight reduction holes (25), and the weight reduction holes (25) include a plurality of holes, which are evenly arranged on the skin (24).

5. The missile hoist as described in claim 2, characterized in that, The connecting ring (131) also has a third state in which the connecting ring (131) is engaged with the shackle (12).

6. The missile hoist as described in claim 1, characterized in that, The sling (13) includes a flexible sling.

7. The missile hoist as described in claim 1, characterized in that, The lifting beam (2) includes a rigid lifting beam.

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