A hoisting structure based on secondary expansion of a C-shaped connecting piece rotating arm mechanism

Abstract

A kind of hoisting structure based on C-type connecting piece swing arm mechanism secondary deployment.The spacecraft needs to use lifting appliance to realize hoisting, during the connection of lifting appliance and spacecraft, due to the limitation of space, the swing arm of C-type connecting piece of lifting appliance needs to be rotated from 0° to 90° first, so that the lifting appliance avoids the protruding parts of spacecraft during the process from outside the star to the first installation position.After reaching the first installation position, the height can realize the 90° rotation operation of the swing arm, and the swing arm and the protruding parts of spacecraft do not interfere with each other during the whole process, to complete the first swing arm rotation.After the swing arm completes the 90° rotation operation, the connecting adjusting assembly and the spacecraft lifting block are connected, to complete the second swing arm rotation, and realize the connection of lifting appliance and spacecraft.The present application can effectively solve the problem that the protruding parts of spacecraft block the vertical hoisting space, resulting in the inability to hoist, and become an effective support equipment for spacecraft hoisting operation.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft hoisting tooling technology, specifically relating to a device for hoisting large spacecraft. Background Technology

[0002] The ultra-large spacecraft is lifted vertically, with four lifting points located on the top of the spacecraft.

[0003] Due to the spacecraft's enormous size, complex configuration, and numerous ground loads, the vertical direction of the lifting points is obstructed by a large antenna, making it impossible to directly lift the spacecraft using vertical slings. The antenna is large, with an outer contour much larger than the spacecraft itself, exceeding 6.1 meters in height. This results in a spacecraft larger than any existing spacecraft in China, necessitating the design of a large lifting device to address the challenge of vertical obstruction at the lifting points, given that the spacecraft can only withstand vertical lifting. Summary of the Invention

[0004] The purpose of this invention is to provide a hoisting structure based on a C-type connector swing arm mechanism that unfolds in two stages. By rotating the swing arm to a 90° position through the swing arm mechanism, the hoisting device does not collide with the antenna during its approach to the spacecraft. After reaching the installation position, the swing arm can be rotated to a 0° position through the swing arm mechanism to complete the connection between the hoisting device and the spacecraft. This solves the problem of vertical obstruction at the hoisting point and enables the stable hoisting of ultra-large spacecraft.

[0005] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0006] This invention provides a lifting structure based on a C-shaped connector swing arm mechanism with secondary deployment. It includes a main lifting ring for connection to an overhead crane, a main lifting beam horizontally positioned below the main lifting ring, and the main lifting ring and main lifting beam connected by four diagonal tie straps. It also includes a C-shaped connector with its opening facing the workpiece to be lifted. The top end of the C-shaped connector is connected to the main lifting beam, and its bottom end is connected to the workpiece via a rotatable adapter assembly. The rotation axis of the adapter assembly is vertical, allowing the adapter assembly to avoid interference with the workpiece during movement.

[0007] In some embodiments, the present invention further includes the following technical features:

[0008] There are four C-shaped connectors, with two at each end of the main lifting beam. The open side of the C-shaped connector is the inner side, and the closed side is the outer side. The top end of the outer side of the C-shaped connector is connected to the end of the main lifting beam through an auxiliary hanger, and the top end of the inner side of the C-shaped connector is connected to the main lifting beam through a C-shaped connector pin.

[0009] The auxiliary cross rod is connected with one C-shaped connector at one end and connected with another C-shaped connector arranged at the same end of the main hanging beam at the other end, so that the two C-shaped connectors at the same side are fixed as a whole and cannot rotate in the vertical direction.

[0010] The reinforcing beam is arranged on the C-shaped connector to increase the bending section area and the bending strength.

[0011] The adapter assembly comprises a rotating arm connected with a rotating arm base arranged at the bottom of the C-shaped connector through a rotating shaft, and a spacecraft adjusting structure is arranged at the end of the rotating arm away from the rotating shaft to be connected with the workpiece to be hoisted.

[0012] The 0° support and 90° support are arranged on the rotating arm base, and the rotating arm support is arranged at the bottom of the C-shaped connector to cooperate with the 0° support and 90° support to realize the positioning of the 0° and 90° positions of the rotating arm; the quick release pin is arranged at the end of the rotating arm support, the rotating arm is positioned at the 0° position when the rotating arm support is connected with the 0° support through the quick release pin, and the rotating arm is positioned at the 90° position when the rotating arm support is connected with the 90° support.

[0013] The adapter assembly further comprises a stop plate connected with the lower part of the C-shaped connector to prevent the rotating arm from rotating more than 90°.

[0014] The spacecraft adjusting structure comprises an adjusting assembly, an adjusting rod, a spacecraft lifting block, a two-stage lifting chain, a lifting block pin shaft, a star pin shaft, an adjusting nut and an operating rod, one end of the adjusting assembly is connected with the rotating arm through a connecting pin, the other end is provided with the adjusting rod, the adjusting rod is connected with the adjusting assembly through threads, the adjusting nut is arranged at the upper part of the adjusting rod, the star pin shaft is arranged at the lower part of the adjusting rod to be connected with the two-stage lifting chain, the height between the lifting device and the spacecraft can be adjusted by rotating the adjusting nut; the upper part of the two-stage lifting chain is connected with the adjusting rod through the star pin shaft, and the lower part of the two-stage lifting chain is connected with the spacecraft lifting block through the lifting block pin shaft; the spacecraft lifting block is arranged on the workpiece to be hoisted; the operating rod is connected with the adjusting nut through threads to rotate the adjusting nut more conveniently.

[0015] The adjusting range of the adjusting rod is ±30 mm.

[0016] The spacecraft adjusting structure has the advantages that:

[0017] The application realizes the avoidance of the large-size antenna on the top of the spacecraft, not only realizes the avoidance in the process that the lifting appliance approaches the spacecraft, but also realizes the avoidance of the spacecraft in the process that the rotating arm rotates when the lifting appliance reaches the installation position, so that the four lifting points are always subjected to the vertical upward pulling force, effectively solves the hoisting technical problem that the traditional method cannot be hoisted due to the large-size antenna of the super-large spacecraft shielding the vertical direction of the lifting point, and through various limiting designs, the large-size and large-weight run stably in the use process, do not shake, greatly reduce the operation risk, and good use effect is obtained. BRIEF DESCRIPTION OF DRAWINGS

[0018] Fig. 1 It is a whole structure schematic view of a hoisting structure based on a C-shaped connecting piece rotating arm mechanism secondary unfolding of the application;

[0019] Fig. 2 It is a local structure schematic view when the rotating arm of the C-shaped connecting piece is located at 0°;

[0020] Fig. 3 It is a local structure schematic view when the rotating arm of the C-shaped connecting piece is located at 90°;

[0021] In the figure, 1 is a main lifting ring, 2 is a cable-stayed lifting belt, 3 is a main lifting beam, 4 is an auxiliary lifting hanging, 5 is a C-shaped connecting piece, 6 is a reinforcing beam, 7 is a rotating arm seat, 8 is a rotating shaft, 9 is a rotating arm support rod, 10 is a quick release pin, 11 is a 0° support, 12 is a rotating arm, 13 is a 90° support, 14 is a spacecraft lifting block, 15 is a stop plate, 16 is an auxiliary cross rod, 17 is a C-shaped connecting piece pin shaft, 18 is a connecting pin, 19 is an adjusting assembly, 20 is a two-stage lifting chain, 21 is a lifting block pin shaft, 22 is a star pin shaft, 23 is an adjusting nut, 24 is an adjusting rod, and 25 is an operating rod. DETAILED DESCRIPTION

[0022] The following is a specific embodiment of the content described in the application, and the following specific embodiment further clarifies the content described in the application. Of course, the following specific embodiment is only for illustrating the content of different aspects of the application, and should not be understood as limiting the scope of the application.

[0023] As Figs. 1-3As shown, in some embodiments, the present application provides a hoisting structure device based on the secondary expansion of the C-shaped connector 5 and the rotating arm 12 mechanism. The spacecraft whole device lifting point is distributed on the top end face of the spacecraft, and the lifting point is designed to only bear vertical tension. Because the large antenna interferes with the lifting path in the vertical direction of the lifting point, the C-shaped connector 5 is used to avoid the large antenna, so that the lifting appliance can complete the lifting work. This determines that the lifting appliance can only move from one side of the spacecraft to the spacecraft in the horizontal direction, and through this way, it reaches the position connected to the spacecraft from a position away from the spacecraft. During the horizontal movement, the antenna and the C-shaped connector 5 interfere with each other, so the rotating arm 12 mechanism is designed to change the C-shaped connector 5 into an inverted L-shaped connector during the horizontal movement, thereby solving the interference problem. When the lifting appliance reaches the position connected to the spacecraft, the rotating arm 12 mechanism is rotated by 90° to reach the installation position, thereby completing the connection with the spacecraft.

[0024] The main hanging ring 1 is connected with four inclined pull hanging belts 2 through four shackles, forming a connection mode of "one ring and four legs". The four inclined pull hanging belts 2 are connected with the main hanging beam 3 through four shackles. The lower part of the main hanging beam 3 is provided with four vertical columns. The bottom of the vertical column is designed with a small hole. Four C-shaped connecting pieces 5 are connected with the main hanging beam 3 through the pin shaft of the C-shaped connecting piece 5. The pin shaft of the C-shaped connecting piece 5 limits the five degrees of freedom of the C-shaped connecting piece 5, leaving only the freedom of rotation along the pin shaft of the C-shaped connecting piece 5. In order to further limit the freedom of rotation of the C-shaped connecting piece 5 along the pin shaft of the C-shaped connecting piece 5, four auxiliary hanging devices 4 are designed at the four distal ends of the main hanging beam 3. The upper part of the auxiliary hanging device 4 is connected with the main hanging beam 3 through a shackle, and the lower part is connected with the C-shaped connecting piece 5 through a shackle. The length of the auxiliary hanging device 4 can be adjusted through a basket screw, so as to ensure that the C-shaped connecting piece 5 remains in a horizontal state. One reinforcing beam 6 is installed on each side of each C-shaped connecting piece 5, a total of eight, for increasing the bending section area of the C-shaped connecting piece 5 and improving the bending resistance. Four rotary arm 12 seats 7 are installed at the lower ends of the four C-shaped connecting pieces 5 through screws. The rotary arm 12 seat 7 is connected with the rotary arm 12 through a rotating shaft 8, so that the rotary arm 12 can rotate on the rotary arm 12 seat 7 along the rotating shaft 8, and the rotary arm 12 seat 7 limits the ability of the rotary arm 12 to move vertically. A stop plate 15 is installed on each rotary arm 12 seat 7 through a screw, ensuring that the angle rotation range of the rotary arm 12 is between 0° and 90°. Since the rotary arm 12 has two working positions, one at 0° and the other at 90°, a 0° support 11 and a 90° support 13 are installed on each rotary arm 12 through a screw. A rotary arm 12 support rod is installed near the rotary arm 12 seat 7 at the lower part of each C-shaped connecting piece 5 through a screw. The rotary arm 12 support rod is connected with the 0° support 11 and the 90° support 13 through a quick-release pin 10, ensuring that the rotary arm 12 does not rotate relatively at the two working positions of 0° and 90°, and further ensuring that the rotary arm 12 is stable and does not interfere with large-size antennas during use of the lifting device. On the back of the two C-shaped connecting pieces 5 on the same side, one auxiliary cross bar 16 is installed. The auxiliary cross bar 16 is connected with the backs of the two C-shaped connecting pieces 5 through its non-detachable pin structure, ensuring that the two C-shaped connecting pieces 5 on the same side do not twist, causing the lifting device as a whole to twist and sway.

[0025] At the end of the rotating arm 12 away from the C-shaped connector 5, an adjusting assembly 19 is installed through two connecting pins. The adjusting assembly 19 has a threaded hole inside, which is in a screwing relationship with an adjusting rod 24. The adjusting rod 24 can move up and down relative to the adjusting assembly 19. An adjusting nut 23 is installed at the upper part of the adjusting rod 24. When the adjusting rod 24 reaches the set position, the adjusting nut 23 is tightened so that the adjusting nut 23 cannot move up and down relative to the adjusting assembly 19. The pin hole at the lower end of the adjusting rod 24 is installed with a two-stage lifting chain 20 through a star pin shaft 22. The lower end of the two-stage lifting chain 20 is connected with a lifting block through a lifting block pin shaft 21. The lifting block is installed at the top of the satellite, and there are four in total. An operating rod 25 is installed on the adjusting nut 23 through a threaded connection, which is used to tighten or loosen the adjusting nut 23.

[0026] During the approach of the lifting appliance to the spacecraft, the C-shaped connector 5 is rotated to a 90° position. At this time, during the movement of the lifting appliance, the lifting appliance does not interfere with the protrusions of the spacecraft.

[0027] When the C-shaped connector 5 reaches the alignment position at the upper end of the spacecraft lifting block 14, the C-shaped connector 5 is rotated from the 90° position to the 0° position to realize the next connection work.

[0028] After the C-shaped connector 5 is rotated to the 0° position, the lifting appliance and the spacecraft lifting block 14 can be connected, and the installation of the lifting appliance is completed.

[0029] The adjusting range of the adjusting rod 24 is ±30mm. The reason is that during the swinging of the rotating arm 12 from 90° to 0°, in order to avoid the protrusions of the spacecraft, the height at which the lifting appliance is located is inconsistent with the height at which the lifting appliance is finally connected with the spacecraft. The purpose is to connect the spacecraft and the lifting appliance together.

[0030] A specific embodiment is described below:

[0031] As shown in Figs. 1-3 , the main lifting ring 1 is connected with the factory overhead crane. Four inclined lifting belts 2 are installed on the main lifting ring 1 and connected with the main lifting beam 3. The main lifting beam 3 is lifted to the upper part of the four C-shaped connectors 5, and the connection between the main lifting beam 3 and the C-shaped connectors 5 is completed through the pin shafts of the four C-shaped connectors 5.

[0032] Among them, four spacecraft lifting blocks 14 are installed at the top of the spacecraft, and two-stage lifting chains 20 are installed through lifting block pin shafts 21.

[0033] Wherein, 4 auxiliary hanging 4 are connected with 4 C-shaped connectors 5, auxiliary cross bars 16 are installed on the back of the C-shaped connectors 5 on the same side to ensure that the 4 C-shaped connectors 5 do not twist. A reinforcing beam 6 is installed on each C-shaped connector assembly to improve the strength; the quick release pin 10 is removed from the 0° support 11, the rotating arm 12 is rotated clockwise by 90°, while rotating the rotating arm 12, the rotating arm 12 support is also rotated, so that the rotating arm 12 support is rotated from the 0° support 11 to the 90° support 13 position, the quick release pin 10 is installed to connect the 90° support 13 and the rotating arm 12 support together, and the rotating arm 12 is fixed at the 90° position.

[0034] Wherein, the lifting appliance is lifted to a specific height (the lower surface of the C-shaped connector 5 is 217mm away from the lower surface of the spacecraft lifting block 14), the lifting appliance is moved horizontally towards the spacecraft, when the rotating shaft 8 reaches the alignment position of the upper lifting block pin shaft 21 of the spacecraft lifting block 14, the C-shaped connector 5 is rotated to the 0° position.

[0035] Wherein, when the rotating shaft 8 reaches the alignment position of the upper lifting block pin shaft 21 of the spacecraft lifting block 14, the quick release pin 10 is removed from the 90° support 13, the rotating arm 12 is rotated counterclockwise by 90°, the quick release pin 10 is used to connect the 0° support 11 and the rotating arm 12 support together, and the rotating arm 12 is fixed at the 0° position.

[0036] Wherein, the adjusting rod 24 is initially located in the middle of the adjusting assembly 19, while supporting the adjusting rod 24, the adjusting nut 23 is rotated to move the adjusting rod 24 downward to a position where the star pin shaft 22 can be installed, the adjusting rod 24 and the two-stage lifting chain 20 are connected through the star pin shaft 22, and the installation of the entire lifting appliance is completed.

[0037] Although the specific embodiments of the present application are described and illustrated in detail above, it should be noted that various equivalent changes and modifications can be made to the above embodiments according to the concept of the present application, and the resulting functional effects still fall within the scope of the present application as long as they do not exceed the spirit of the specification and drawings.

Claims

1. A hoisting structure based on a C-type connector swing arm mechanism with secondary deployment, characterized in that, The system includes a main lifting ring for connection with an overhead crane, a main lifting beam horizontally positioned below the main lifting ring, the main lifting ring and the main lifting beam connected by four diagonal tie straps, and a C-shaped connector. The opening of the C-shaped connector faces the workpiece to be lifted, its top end connects to the main lifting beam, and its bottom end connects to the workpiece to be lifted via a rotatable adapter assembly. The adapter assembly includes a rotating arm rotatably connected to a rotating arm seat located at the bottom of the C-shaped connector via a rotating shaft. A spacecraft adjustment structure for connection to the workpiece to be lifted is mounted on the end of the rotating arm away from the rotating shaft. The rotating arm seat is equipped with... Equipped with 0° and 90° supports, the bottom of the C-shaped connector is fitted with a swing arm support rod that mates with the 0° and 90° supports, enabling the swing arm to be positioned at 0° and 90°. The end of the swing arm support rod is equipped with a quick-release pin. When the swing arm support rod is connected to the 0° support rod via the quick-release pin, the swing arm is positioned at 0°. When the swing arm support rod is connected to the 90° support rod, the swing arm is positioned at 90°. The rotation axis of the adapter assembly is vertical, allowing the adapter assembly to avoid interference with the workpiece to be lifted during movement.

2. The hoisting structure based on the secondary unfolding of the C-type connector swing arm mechanism according to claim 1, characterized in that, There are four C-shaped connectors, with two at each end of the main lifting beam. The open side of the C-shaped connector is the inner side, and the closed side is the outer side. The top end of the outer side of the C-shaped connector is connected to the end of the main lifting beam through an auxiliary hanger, and the top end of the inner side of the C-shaped connector is connected to the main lifting beam through a C-shaped connector pin.

3. The hoisting structure based on the secondary unfolding of the C-type connector swing arm mechanism according to claim 2, characterized in that, It also includes an auxiliary crossbar, one end of which is connected to a C-shaped connector, and the other end is connected to another C-shaped connector located at the same end of the main lifting beam, so that the two C-shaped connectors on the same side are fixed together as one unit and will not rotate in the vertical direction.

4. The hoisting structure based on the secondary unfolding of the C-type connector swing arm mechanism according to claim 2, characterized in that, It also includes a reinforcing beam, which is installed on the C-shaped connector to increase the bending cross-sectional area and increase the bending strength.

5. The hoisting structure based on the secondary unfolding of the C-type connector swing arm mechanism according to claim 1, characterized in that, The adapter assembly also includes a stop plate, which is connected to the lower part of the C-shaped connector to prevent the swing arm from rotating more than 90°.

6. The hoisting structure based on the secondary unfolding of the C-type connector swing arm mechanism according to claim 1, characterized in that, The spacecraft adjustment structure includes an adjustment component, an adjustment rod, a spacecraft lifting block, a two-stage lifting chain, a lifting block pin, a star pin, an adjustment nut, and an operating rod. One end of the adjustment component is connected to the rotating arm via a connecting pin, and the other end is equipped with an adjustment rod. The adjustment rod is threaded to the adjustment component. An adjustment nut is installed on the upper part of the adjustment rod, and the lower part is connected to the two-stage lifting chain via a star pin. Rotating the adjustment nut is used to adjust the height between the lifting device and the spacecraft. The upper part of the two-stage lifting chain is connected to the adjustment rod via a star pin, and the lower part is connected to the spacecraft lifting block via a lifting block pin. The spacecraft lifting block is installed on the workpiece to be lifted. The operating rod is threaded to the adjustment nut for easier rotation of the adjustment nut.

7. The hoisting structure based on the secondary unfolding of the C-type connector swing arm mechanism according to claim 6, characterized in that, The adjustment range of the adjusting rod is ±30mm.

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