A rocket sling

Abstract

This application provides a rocket lifting device, relating to the field of aerospace equipment technology, including a lifting beam with multiple mounting points; multiple first lifting lug assemblies, detachably connected to the lifting beam, which support the rocket to be lifted and, when subjected to traction force from the same lifting point, horizontally lift the rocket; the number of first lifting lug assemblies and their corresponding mounting points are determined according to the size and center of gravity of the rocket to be lifted; and multiple second lifting lug assemblies, detachably connected to the lifting beam, which connect to the lifting points of the rocket to be lifted and, when subjected to traction force, vertically lift the rocket. This rocket lifting device allows for the detachable installation of first and second lifting lug assemblies, and the lifting points providing traction force are located on the same vertical line as the center of gravity of the rocket to be lifted. By supporting the rocket body through the first lifting lug assemblies, the traction force is prevented from acting directly on the rocket body, thus protecting the rocket body and achieving single-vehicle lifting functionality.

Description

Technical Field

[0001] This application relates to the field of lifting equipment, and more particularly to a rocket lifting device. Background Technology

[0002] With the continuous advancement of aerospace technology, rockets, as the core launch vehicles or boosters for spaceflight, are also developing rapidly, currently classified into two main categories: liquid rockets and solid rockets. Generally, after final assembly, a rocket is transported from the technical facility to the launch site, where it needs to be loaded using a hoisting method. At the launch site, the rocket is erected, rotated, and vertically lifted using this method. Liquid rockets are fueled in a vertical position on the launch pad after assembly. The overall weight of the rocket is relatively light, and the hoisting work can usually be completed by installing standard universal rotating lifting rings or lugs at the lifting points on the rocket body. Solid rockets, however, require pre-loading of propellant into the solid rocket motor, resulting in a fully loaded rocket after assembly. The overall weight of the rocket is relatively heavy, and the front lifting point section cannot provide sufficient rigidity for lifting. Therefore, specialized auxiliary reinforcing beams are typically designed and manufactured. This requires two overhead cranes to complete the hoisting. However, due to varying support conditions and requirements at different launch sites, some launch sites cannot meet the requirements for double-hook hoisting.

[0003] Therefore, there is an urgent need for a rocket lifting device that can complete the vertical and horizontal lifting of liquid and solid rockets using a single overhead crane and a single point of lifting. Utility Model Content

[0004] The purpose of this application is to address the above problems by providing a rocket lifting device that enables the vertical and horizontal lifting of liquid and solid rockets by a single crane at a single point, thereby solving the problem that launch sites do not meet the requirements for simultaneous lifting by two cranes.

[0005] This application provides a rocket lifting device, comprising: A lifting beam, on which multiple mounting points are provided; Multiple first lifting lug assemblies are provided, and the first lifting lug assemblies are detachably connected to the lifting beam. The first lifting lug assemblies are used to support the rocket to be lifted and to perform horizontal lifting of the rocket when it is subjected to traction force from the same lifting point. The number of the first lifting lug assemblies and their corresponding installation points are determined according to the size and center of gravity of the rocket to be lifted. Multiple second lifting lug assemblies are provided, which are detachably connected to the lifting beam. The second lifting lug assemblies are used to connect with the lifting points of the rocket to be lifted and to vertically lift the rocket when subjected to traction force.

[0006] According to the technical solutions provided in some embodiments of this application, the rocket lifting device further includes a lifting ring and rigging, wherein the lifting ring and the center of mass of the rocket to be lifted in the lifting state are located on the same vertical line; One end of the rigging is connected to the lifting ring, and the other end is connected to the first lifting lug assembly or the second lifting lug assembly.

[0007] According to the technical solutions provided in certain embodiments of this application, the first lifting lug assembly includes: A first lifting component, which is used to connect to the rigging; The first lifting lug is detachably connected to the lifting beam, and the first lifting component is detachably mounted on the first lifting lug and can rotate relative to the first lifting lug; The hanging ear assembly is symmetrically arranged on both sides of the first hanging ear and is detachably connected to the first hanging ear; The sling has two ends that are detachably connected to the lug assembly, and the space between the first lug and the sling is used to support the rocket to be hoisted.

[0008] According to the technical solutions provided in certain embodiments of this application, a U-shaped mounting groove is provided on the side of the first lifting lug near the lifting beam. The opening of the U-shaped mounting groove faces the lifting beam, and its interior is used to accommodate the lifting beam. A plurality of connecting units are provided inside the groove. Each connecting unit includes a pair of mounting holes arranged coaxially on two sides of the U-shaped mounting groove and a fixing member that passes through the mounting holes. The connecting unit near the lifting beam is used to install the first lifting component, and the remaining mounting units are used to install the lifting beam.

[0009] According to the technical solutions provided in certain embodiments of this application, mounting plates are symmetrically arranged on both sides of the first lug for mounting the lug assembly.

[0010] According to the technical solutions provided in certain embodiments of this application, a symmetrically arranged arc-shaped limiting plate is provided on the side of the first lifting lug away from the lifting beam, which is used to abut against the outer surface of the rocket to be lifted during hoisting.

[0011] According to the technical solutions provided in certain embodiments of this application, the first lifting member is provided with mounting holes at both ends, one mounting hole is used to connect the rigging, and the other mounting hole is connected to the connecting unit of the first lifting lug near the lifting beam.

[0012] According to the technical solutions provided in certain embodiments of this application, the ear loop assembly includes: A connecting rod passes through the mounting plate, with one end near the lifting beam connected to the mounting plate and the other end away from the lifting beam detachably connected to a connecting ring for connecting to the lifting strap.

[0013] According to the technical solutions provided in certain embodiments of this application, the second lifting lug assembly includes: The second lifting component is used to connect to the rigging; The second lifting lug has a U-shaped main body, including two side plates and a connecting plate connecting the side plates. A protruding plate is integrally formed on the connecting plate. The opening of the U-shaped part faces the lifting beam, and its interior is used to accommodate the lifting beam. Multiple connecting units are provided inside the part. Each connecting unit includes a pair of mounting holes and a fixing member that passes through the mounting holes, which are coaxially arranged on the side plates. The connecting unit near the lifting beam is used to install the second lifting component, and the remaining mounting units are used to install the lifting beam. The second lifting component is detachably mounted on the second lifting lug and can rotate relative to the second lifting lug. At least one rigging connection hole is provided on the protruding plate.

[0014] According to the technical solutions provided in certain embodiments of this application, the mounting points are symmetrically distributed, and each mounting point is provided with a mounting hole.

[0015] Compared with the prior art, the beneficial effects of this application are as follows: The rocket lifting device includes a lifting beam, a first lifting lug assembly, and a second lifting lug assembly. The lifting beam is provided with multiple mounting points. When lifting liquid rockets, the second lifting lug assembly is selected and directly connected to the lifting point of the rocket body for vertical lifting. When lifting solid rockets horizontally under full load, the first lifting lug assembly is selected. The number of lifting lug assemblies and corresponding mounting points can be determined according to the rocket size and center of gravity. After the rocket is evenly stressed, it is lifted from a single point above the center of gravity. At the same time, the traction force of the rocket to be lifted can be distributed by multiple first lifting lug assemblies supporting the rocket body. This avoids the high requirements on the strength of the rocket's front lifting point section caused by direct connection with the lifting point of the rocket body, thus protecting the rocket body. It enables single-vehicle lifting, solving the problem of small launch sites that cannot support dual-vehicle lifting. Furthermore, the spacing between the first lifting lugs can be adjusted according to the rocket body, making it highly adaptable and widely applicable to various aerospace solid heavy-lift rockets.

[0016] It should be understood that the descriptions of technical features, technical solutions, beneficial effects, or similar language in this application do not imply that all features and advantages can be achieved in any single embodiment. Rather, it is understood that the description of a feature or beneficial effect means that a specific technical feature, technical solution, or beneficial effect is included in at least one embodiment. Therefore, the descriptions of technical features, technical solutions, or beneficial effects in this specification do not necessarily refer to the same embodiment. Furthermore, the technical features, technical solutions, and beneficial effects described in this embodiment can be combined in any suitable manner. Those skilled in the art will understand that embodiments can be implemented without one or more specific technical features, technical solutions, or beneficial effects of a particular embodiment. In other embodiments, additional technical features and beneficial effects may be identified in specific embodiments that do not embody all embodiments. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the overall structure of a rocket lifting device provided in an embodiment of this application; Figure 2 This is a schematic diagram of the structure of the lifting beam provided in the embodiments of this application; Figure 3 This is a schematic diagram of the horizontal hoisting of a rocket provided in an embodiment of this application; Figure 4 This is a schematic diagram of the vertical hoisting of a rocket provided in an embodiment of this application; Figure 5 This is a schematic diagram of the structure of the first lifting lug assembly provided in an embodiment of this application; Figure 6 This is a structural schematic diagram of the hoisting component provided in an embodiment of this application.

[0019] Figure 7 This is a schematic diagram of the ear loop assembly provided in an embodiment of this application.

[0020] Figure 8 A schematic diagram of the structure of the second lifting lug provided in the embodiments of this application. The text labels in the image represent: 1. Lifting beam; 2. First lifting lug assembly; 3. Lifting rocket; 4. Second lifting lug assembly; 5. Lifting ring; 6. Lock; 21. First lifting component; 22. First lifting lug; 23. Hanging lug assembly; 24. Lifting strap; 25. Fixing component; 41. Second lifting component; 42. Second lifting lug; 101. Mounting point; 102. Reinforcing block; 221. U-shaped mounting groove; 222. Mounting hole; 223. Mounting plate; 224. Arc-shaped limiting plate; 231. Connecting rod; 232. Connecting ring; 421. Side plate; 422. Connecting plate; 423. Protruding plate; 424. Connecting hole; 2311. Limiting component. Detailed Implementation

[0021] To enable those skilled in the art to better understand the technical solutions of this application, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. The descriptions in this section are merely illustrative and explanatory, and should not be construed as limiting the scope of protection of this application. Specifically, the described embodiments are only some embodiments of this application, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort should fall within the scope of protection of this invention.

[0022] It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such process, method, product, or apparatus.

[0023] As mentioned in the background section, in view of the problems in the prior art, this embodiment provides a rocket lifting device, including: The lifting beam 1 has multiple mounting points 101. Multiple first lifting lug assemblies 2 are detachably connected to the lifting beam 1. The first lifting lug assemblies 2 are used to support the rocket 3 to be lifted and to perform horizontal lifting of the rocket 3 to be lifted when it is subjected to traction force from the same lifting point. The number of the first lifting lug assemblies 2 and their corresponding mounting points 101 are determined according to the size and center of gravity of the rocket 3 to be lifted. Multiple second lifting lug assemblies 4 are provided. The second lifting lug assemblies 4 are detachably connected to the lifting beam 1. The second lifting lug assemblies 4 are used to connect with the lifting points of the rocket 3 to be lifted and to vertically lift the rocket 3 to be lifted when subjected to traction force.

[0024] like Figures 1 to 2 As shown, the lifting beam 1 is a rigid beam with a rectangular cross-section. Multiple mounting points 101 are provided on the lifting beam 1. Both the first lifting lug assembly 2 and the second lifting lug assembly 4 can be detachably connected to the lifting beam 1 at any of the mounting points 101, allowing for selection, disassembly, and installation according to actual lifting needs. Figure 3As shown, the first lifting lug assembly 2 is used for horizontal lifting of the rocket 3 (e.g., a fully loaded solid rocket). During use, the number and position of the mounting points 101 are determined based on the center of gravity and length of the rocket 3. The first lifting lug assembly 2 is installed on the mounting points 101 of the lifting beam 1 so that the lifting point providing traction is aligned vertically with the center of gravity of the rocket 3. The first lifting lug assembly 2 provides support for the rocket body, preventing the traction force from directly acting on the front lifting point of the fully loaded solid rocket body, thus avoiding damage to the rocket body due to insufficient strength. Figure 4 As shown, the second lifting lug assembly 4 is used for the vertical lifting of the rocket 3 (e.g., a liquid rocket before fueling). The second lifting lug assembly 4 is installed on the lifting beam 1. Since the entire rocket is relatively light before fueling, the second lifting lug assembly 4 can be directly connected to the front lifting point of the rocket body to complete the vertical lifting. It is understood that, to increase the strength of the lifting beam 1, a reinforcing block 102 is welded to the mounting point 101 near its centerline. The reinforcing block 102 is machined from a plate of a specific thickness and is integrally welded to the rectangular lifting beam 1 to improve overall strength.

[0025] This application allows for the detachable installation of a first lifting lug assembly for horizontal lifting and a second lifting lug assembly for vertical lifting at multiple mounting points on the lifting beam. When lifting a liquid rocket before fueling, the second lifting lug assembly is selected and directly connected to the lifting point of the rocket body for vertical lifting. For horizontal lifting of a fully loaded solid rocket, the first lifting lug assembly is selected. The number and corresponding mounting points of the first lifting lug assembly can be determined based on the rocket's size and center of gravity to ensure even force distribution on the rocket, allowing for single-point lifting above the center of gravity. Simultaneously, the multiple first lifting lug assemblies support the rocket body, distributing the traction force and preventing direct force application to the front lifting point of the fully loaded solid rocket body. This protects the rocket body from damage due to insufficient strength and enables single-vehicle lifting, solving the problem of limited launch sites preventing dual-vehicle lifting. Furthermore, the spacing between the first or second lifting lug assemblies can be adjusted according to the rocket body's condition, demonstrating strong adaptability and broad applicability to various aerospace solid heavy-lift rockets.

[0026] In a preferred embodiment, the rocket lifting device further includes a lifting ring 5 and a rigging 6, wherein the lifting ring 5 and the center of mass of the rocket 3 to be lifted in the lifting state are located on the same vertical line; One end of the rigging 6 is connected to the lifting ring 5, and the other end is connected to the first lifting lug assembly 2 or the second lifting lug assembly 4.

[0027] Specifically, the rocket lifting device also includes a lifting ring 5 and a rigging 6. The lifting ring 5 is located above the center of gravity of the rocket 3 to be lifted, and is on the same vertical line as the center of gravity of the rocket 3 in the lifting state. It is used to connect with the drive device (e.g., a crane) and provide stable traction force at a single point under its action. During horizontal lifting, one end of the rigging 6 is used to connect to the lifting ring 5, and the other end is used to connect to the first lifting lug assembly 2, for example, as shown in the image. Figure 3 As shown, four rigging 6 are selected, and the rigging 6 are symmetrically distributed on both sides of the lifting ring 5; during vertical lifting, one end of the rigging 6 is used to connect to the lifting ring 5, and the other end is used to connect to the second lifting lug assembly 4, for example, as... Figure 4 As shown, two rigging 6 are selected, with each rigging 6 located on either side of the lifting ring 5. It can be understood that, as... Figure 4 As shown, during vertical hoisting, two additional rigging 6 are selected. One end of rigging 6 is used to connect to the second lifting lug assembly 4, and the other end is used to connect to the lifting point on the rocket body to be hoisted. The two rigging 6 are located on both sides of the rocket 3 to be hoisted.

[0028] In a preferred embodiment, the first lug assembly 2 includes: The first lifting component 21 is used to connect with the rigging 6; The first lifting lug 22 is detachably connected to the lifting beam 1, and the first lifting component 21 is detachably mounted on the first lifting lug 22 and can rotate relative to the first lifting lug 22. The ear-hanging assembly 23 is symmetrically arranged on both sides of the first hanging ear 22 and is detachably connected to the first hanging ear 22; The sling 24 has two ends that are detachably connected to the lug assembly 23. The first lug 22 and the sling 24 form a space for supporting the rocket 3 to be hoisted.

[0029] like Figure 3 As shown, the first lifting component 21 is connected to the rigging 6; as Figure 5As shown, the first lifting lug 22 is the main body of the first lifting lug assembly 2. The first lifting lug 22 can be detachably connected to the lifting beam 1 at any of the installation points 101. It can be selected, disassembled, and installed according to actual lifting needs. The first lifting component 21 can rotate relative to the first lifting lug 22, so as to adaptively adjust according to the angle of the rigging 6 and the attitude of the rocket 3 during lifting. There are two hanging lug assemblies 23, which are symmetrically distributed relative to the center line of the first lifting lug 22. The hanging lug assembly 23 is detachably connected to the first lifting lug 22. The lifting strap 24 is flat and detachably connected to the hanging lug assembly 23 at both ends. Different lifting straps can be flexibly replaced according to the diameter of different rockets 3 to be lifted. Both ends are connected to the first lifting lug 22 through the hanging lug assembly 23, forming an annular space between them. The main body of the rocket is placed in this space and supported by the lifting strap 24.

[0030] In a preferred embodiment, the first lifting lug 22 is provided with a U-shaped mounting groove 221 on the side near the lifting beam 1. The opening of the U-shaped mounting groove 221 faces the lifting beam 1, and its interior is used to accommodate the lifting beam 1. It is provided with a plurality of connecting units. Each connecting unit includes a pair of mounting holes 222 arranged coaxially on two sides of the U-shaped mounting groove 221 and a fixing member 25 passing through the mounting holes 222. The connecting unit near the lifting beam 1 is used to install the first lifting member 21, and the remaining mounting units are used to install the lifting beam 1.

[0031] like Figure 5 As shown, the U-shaped mounting groove 221 is located on the center line of the first lifting lug 22, and the opening of the U-shaped mounting groove 221 faces the lifting beam 1, so that the lifting beam 1 can be inserted into the groove from the opening to achieve initial positioning; as shown Figure 8 As shown, the U-shaped mounting groove is provided with three connecting units. Each connecting unit includes a pair of mounting holes 222 penetrating the U-shaped mounting groove and a fastener 25 penetrating the mounting holes. The connecting unit near the lifting beam 1 is used to install the first lifting component 21 so that the first lifting component 21 can be connected to the first lifting lug 22. The other two are used to connect to the lifting beam 1 so that the first lifting lug 22 can be installed on the lifting beam 1. The fastener 25 can be a pin. Of course, the fastener 25 can also be set as other fasteners. The specific settings and adjustments can be made according to the actual situation. No specific limitation is made here.

[0032] In a preferred embodiment, mounting plates 223 are symmetrically arranged on both sides of the first lug 22 for mounting the lug assembly 23.

[0033] like Figure 5As shown, the mounting plate 223 is symmetrically distributed with respect to the center line of the first lifting lug 22. The mounting plate 223 is provided with mounting holes 222 so that the hanging lug assembly 23 can be detachably connected to the mounting plate through the mounting holes 222, which facilitates replacement and maintenance.

[0034] In a preferred embodiment, the first lifting lug 22 is provided with a symmetrically arranged arc-shaped limiting plate 224 on the side away from the lifting beam 1, which is used to abut against the outer surface of the rocket 3 to be lifted during hoisting.

[0035] like Figure 5 As shown, the arc-shaped limiting plate 224 is symmetrically arranged relative to the first lifting lug 22. The arc-shaped limiting plate 224 matches the outer contour of the rocket 3 to be lifted. During lifting, it abuts against the outer surface of the rocket 3 to be lifted, so as to provide balanced constraint on both sides of the rocket 3 to be lifted.

[0036] In a preferred embodiment, the first lifting member 21 is provided with mounting holes 222 at both ends, one mounting hole 222 is used to connect the rigging 6, and the other mounting hole 222 is connected to the connecting unit of the first lifting lug 22 near the lifting beam 1.

[0037] like Figure 6 As shown, one end of the first lifting component 21 is a rectangular block with a through mounting hole 222, and the other end is a cylinder with a through mounting hole 222. Figure 3 and Figure 5 As shown, the mounting hole 222 penetrating the rectangular block is used to connect with the rigging 6, and the mounting hole 222 penetrating the cylinder is used to connect with the first lifting lug 22 near the connecting unit of the lifting beam 1, so that the first lifting component 21 is connected with the first lifting lug 22. The first lifting component 21 is used to transmit traction force to realize the lifting operation of the rocket 3 to be lifted.

[0038] In a preferred embodiment, the ear loop assembly 23 includes: A connecting rod 231 passes through the mounting plate 223. One end of the connecting rod 231, which is close to the lifting beam 1, is connected to the mounting plate 223. The other end, which is away from the lifting beam 1, is detachably connected to a connecting ring 232 for connecting to the lifting strap 24.

[0039] Specifically, the ear-hook assembly 23 includes a connecting rod 231, such as... Figure 7 and Figure 5As shown, the connecting rod 231 has a cylindrical end near the lifting beam 1 and a U-shaped connecting ring 232 at the end away from the lifting beam 1. The cylindrical end passes through the mounting hole 222 of the mounting plate 223 and is detachably connected to the mounting plate 223. The connecting ring 232 can be a horseshoe ring, which is used to connect with the sling 24. The U-shaped structure and arc contour of the horseshoe ring evenly distribute the force on the sling, protecting the sling and improving the stability of the lifting. It is understood that a limiter 2311 is also provided on the cylinder to prevent the cylinder from slipping. The connecting ring 232 can also be set with other connection structures, which can be set and adjusted according to the actual situation. No specific limitation is made here.

[0040] In a preferred embodiment, the second lug assembly 4 includes: The second lifting component 41 is used to connect with the rigging 6; The second lifting lug 42 has a U-shaped main body, including two side plates 421 and a connecting plate 422 connecting the side plates 421. A protruding plate 423 is integrally formed on the connecting plate 422. The opening of the U-shaped part faces the lifting beam 1, and its interior is used to accommodate the lifting beam 1. Multiple connecting units are provided inside the part. Each connecting unit includes a pair of mounting holes 222 arranged coaxially on the side plate 421 and a fixing member 25 passing through the mounting holes 222. The connecting unit near the lifting beam 1 is used to install the second lifting member 41, and the remaining mounting units are used to install the lifting beam 1. The second lifting member 41 is detachably mounted on the second lifting lug 42 and can rotate relative to the second lifting lug 42. At least one rigging connection hole 424 is provided on the protruding plate.

[0041] like Figure 4 As shown, the second lifting component 41 is connected to the rigging 6; as Figure 8As shown, the main body of the second lifting lug 42 is a U-shaped component. The U-shaped component includes two rectangular side plates 421, a connecting plate 422, and an integrally formed semi-circular convex plate 423. The two side plates 421 are connected to the connecting plate 422, and the center lines of the convex plate 423 and the connecting plate 422 are coaxial. The two rectangular side plates 421 and the connecting plate 422 together form a U-shaped groove with a cavity. The opening of the cavity faces the lifting beam 1 and is used to accommodate the lifting beam 1. Three connecting units are provided inside the U-shaped groove. Each connecting unit includes a pair of mounting holes 222 penetrating the U-shaped groove and a fixing member 25 penetrating the mounting holes. The connecting unit near the lifting beam 1 is used to install the second lifting component. 41, so that the second lifting component 42 can be connected to the second lifting lug 42, and the other two are used for detachable connection with the lifting beam 1, so that the second lifting lug 42 can be installed on the lifting beam 1; and the second lifting component 41 can rotate relative to the second lifting lug 42, so as to adaptively adjust according to the angle of the rigging 6 and the attitude of the lifting rocket 3 during lifting; the semi-circular convex plate 423 is provided with a rigging connection hole 424 through the convex plate 423 for connecting with the rigging; the fixing component 25 can be a pin, and it is understood that the fixing component 25 can also be set as other fixing components, which can be set and adjusted according to the actual situation, and no specific limitation is made here.

[0042] In a preferred embodiment, the mounting points 101 are symmetrically distributed, and each mounting point 101 is provided with a mounting hole 222.

[0043] like Figure 2 As shown, the mounting points 101 are symmetrically distributed relative to the center line of the lifting beam 1. Each mounting point 101 is provided with two mounting holes 222, and the mounting holes 222 penetrate the lifting beam 1 for connection with the first lifting lug assembly 2 or the second lifting lug assembly 4.

[0044] To facilitate understanding by those skilled in the art, the workflow of the rocket lifting device provided in this application is further as follows: For a fully loaded solid rocket, the entire rocket is lifted horizontally. First, the center of gravity of the rocket to be lifted is determined based on the actual rocket to be lifted. Based on the size and center of gravity of the rocket to be lifted, the number of first lifting lug assemblies 2 and the position and number of corresponding installation points 101 on the lifting beam 1 are determined. Multiple first lifting lug assemblies 2 are symmetrically installed on the lifting beam 1 relative to the vertical line where the center of gravity of the rocket to be lifted is located through the fixing component 25. The rocket lifting device is slowly lifted to the top of the rocket body to be lifted. The connection between the lug assembly 23 and the lifting strap 24 is removed. The rocket lifting device is slowly lowered until the arc-shaped limiting plate 224 is 5-10mm away from the rocket body to be lifted. The lug assembly 23 and the lifting strap 24 are reconnected. At this time, the lifting ring 5 is located above the center of gravity of the rocket to be lifted and is on the same vertical line as the center of gravity of the rocket to be lifted. One end of the rigging 6 is connected to the lifting ring 5 and the other end is connected to the first lifting lug assembly 2. Using the traction force of the same lifting point, the rocket body is slowly lifted and the lifting is completed. For liquid rockets before refueling, the entire rocket is vertically hoisted. The first lifting lug assembly 2 is removed from the lifting beam 1, and the number of second lifting lug assemblies 4 and the corresponding positions and numbers of installation points 101 on the lifting beam 1 are determined based on the actual size and center of gravity of the rocket 3 to be hoisted. The second lifting lug assemblies 4 are installed, and multiple second lifting lug assemblies 4 are fixed to the corresponding installation points 101 on the lifting beam 1 by fasteners 25. The spacing between the second lifting lug assemblies 4 is adjusted according to the actual situation of the rocket 3 to be hoisted. One end of the rigging 6 connected to the lifting ring 5 is connected to the lifting ring 5, and the other end is connected to the second hoisting component 41. One end of the rigging 6 connected to the liquid rocket before refueling is connected to the rigging connection hole 424 on the protruding plate 423, and the other end is connected to the lifting point on the rocket body to be hoisted. The vertical hoisting of the rocket is completed by using the traction force of the same lifting point. Throughout the process, the symmetrical distribution and detachable design of the installation points 101 ensure stable force transmission and center of gravity matching during the hoisting process.

[0045] The rocket lifting device of this application features multiple mounting points on the lifting beam for detachable installation of a first lifting lug assembly for horizontal lifting and a second lifting lug assembly for vertical lifting. When lifting a liquid rocket before refueling, the second lifting lug assembly is selected and directly connected to the lifting point on the rocket body to achieve vertical lifting. For horizontal lifting of a fully loaded solid rocket, the first lifting lug assembly is selected. The number and corresponding mounting points of the first lifting lug assembly can be determined based on the rocket's size and center of gravity to ensure even force distribution on the rocket, allowing for single-point lifting above the center of gravity. Simultaneously, by using multiple first lifting lug assemblies to support the rocket body, the traction force on the rocket being lifted can be distributed, preventing the traction force from directly acting on the fully loaded solid rocket. At the front lifting point of the rocket body, the design protects the rocket body from damage caused by insufficient strength, enabling single-vehicle lifting. The lifting ring and the center of gravity of the rocket to be lifted are aligned vertically. The lifting ring, connected to the drive unit, provides stable traction at a single point. With the aid of rotatable first and second lifting components, the design adaptively adjusts according to the angle of the rigging and the attitude of the rocket during lifting, ensuring uniform force transmission and rocket body stability. This solves the problem of limited launch sites preventing dual-vehicle lifting. Furthermore, the spacing between the first or second lifting lugs can be adjusted according to the rocket body's condition, demonstrating strong adaptability and broad applicability to various solid-propellant heavy-lift rockets.

[0046] This document uses specific examples to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. The above descriptions are only preferred embodiments of this application. It should be noted that due to the limitations of written expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of this invention, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the inventive concept and technical solution to other situations without modification, should all be considered within the scope of protection of this application.

Claims

1. A rocket lifting device, characterized in that, include: A lifting beam (1) is provided with multiple mounting points (101); Multiple first lifting lug assemblies (2) are detachably connected to the lifting beam (1). The first lifting lug assemblies (2) are used to support the rocket (3) to be lifted and to lift the rocket (3) horizontally when subjected to traction from the same lifting point. The number of the first lifting lug assemblies (2) and their corresponding installation points (101) are determined according to the size and center of gravity of the rocket (3) to be lifted. Multiple second lifting lug assemblies (4) are detachably connected to the lifting beam (1). The second lifting lug assembly (4) is used to connect with the lifting point of the rocket (3) to be lifted and to vertically lift the rocket (3) to be lifted when subjected to traction force.

2. The rocket lifting device according to claim 1, characterized in that, The rocket lifting device also includes a lifting ring (5) and a rigging (6), wherein the lifting ring (5) and the center of mass of the rocket (3) to be lifted in the lifting state are located on the same vertical line; One end of the rigging (6) is connected to the lifting ring (5), and the other end is connected to the first lifting lug assembly (2) or the second lifting lug assembly (4).

3. The rocket lifting device according to claim 2, characterized in that, The first lug assembly (2) includes: The first lifting component (21) is used to connect with the rigging (6); The first lifting lug (22) is detachably connected to the lifting beam (1), and the first lifting component (21) is detachably mounted on the first lifting lug (22) and can rotate relative to the first lifting lug (22); The ear-hanging assembly (23) is symmetrically arranged on both sides of the first hanging ear (22) and is detachably connected to the first hanging ear (22); The sling (24) is detachably connected to the lug assembly (23) at both ends. The first lug (22) and the sling (24) form a space for supporting the rocket (3) to be hoisted.

4. The rocket lifting device according to claim 3, characterized in that, The first lifting lug (22) is provided with a U-shaped mounting groove (221) on the side near the lifting beam (1). The opening of the U-shaped mounting groove (221) faces the lifting beam (1) and is used to accommodate the lifting beam (1). It is provided with multiple connecting units. Each connecting unit includes a pair of mounting holes (222) arranged on two sides of the U-shaped mounting groove (221) and a fixing member (25) that passes through the mounting holes (222). The connecting unit near the lifting beam (1) is used to install the first lifting component (21), and the remaining mounting units are used to install the lifting beam (1).

5. The rocket lifting device according to claim 3, characterized in that, The first lug (22) has mounting plates (223) symmetrically arranged on both sides for mounting the lug assembly (23).

6. The rocket lifting device according to claim 3, characterized in that, The first lifting lug (22) is provided with a symmetrically arranged arc-shaped limiting plate (224) on the side away from the lifting beam (1), which is used to abut against the outer surface of the rocket (3) to be lifted during hoisting.

7. The rocket lifting device according to claim 3, characterized in that, The first lifting component (21) has mounting holes (222) at both ends. One mounting hole (222) is used to connect the rigging (6), and the other mounting hole (222) is connected to the connecting unit of the first lifting lug (22) near the lifting beam (1).

8. The rocket lifting device according to claim 5, characterized in that, The ear loop assembly (23) includes: A connecting rod (231) passes through the mounting plate (223). One end of the connecting rod (231) near the lifting beam (1) is connected to the mounting plate (223), and the other end away from the lifting beam (1) is detachably connected to a connecting ring (232) for connecting to the lifting strap (24).

9. The rocket lifting device according to claim 2, characterized in that, The second lug assembly (4) includes: The second lifting component (41) is used to connect with the rigging (6); The second lifting lug (42) is a U-shaped part, including two side plates (421) and a connecting plate (422) connecting the side plates (421). A convex plate (423) is integrally formed on the connecting plate. The opening of the U-shaped part faces the lifting beam (1). Its interior is used to accommodate the lifting beam (1). It is provided with multiple connecting units. Each connecting unit includes a pair of mounting holes (222) and a fixing member (25) that passes through the mounting holes (222) and is provided on the side plate (421) and is coaxially arranged. The connecting unit near the lifting beam (1) is used to install the second lifting component (41). The remaining mounting units are used to install the lifting beam (1). The second lifting component (41) is detachably mounted on the second lifting lug (42) and can rotate relative to the second lifting lug (42). At least one rigging connection hole (424) is provided on the convex plate (423).

10. The rocket lifting device according to claim 1, characterized in that, The mounting points (101) are symmetrically distributed, and each mounting point (101) is provided with a mounting hole (222).

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