Satellite lifting, turning-over and parking device

Abstract

The utility model provides a satellite lifting, turning-over and parking device. The satellite lifting, turning-over and parking device comprises an isosceles trapezoid supporting rod, a turning-over extension sleeve, a Z-shaped lifting appliance adapter block, a whole satellite lifting point connecting plate, a turning-over extension rod and a lifting appliance supporting rod, the Z-shaped lifting appliance switching blocks are mounted at the two ends of the whole star body; one end of the whole star body is provided with a turnover extension sleeve through a Z-shaped lifting appliance adapter block, and the turnover extension sleeve is connected with an isosceles trapezoid supporting rod; the other end of the whole star body is provided with a whole star lifting point connecting plate and a turnover extension rod through a Z-shaped lifting appliance adapter block, and the turnover extension rod is connected with the lifting appliance supporting rod through a lifting belt. According to the method, the mass center of the satellite can be balanced by selecting different lifting point combinations, it is guaranteed that the satellite body is kept stable in the whole satellite horizontal lifting process, the whole satellite vertical lifting process and the whole satellite 90-degree turning process, side turning is prevented, and the whole satellite lifting and turning risks of the satellite are reduced.

Description

Technical Field

[0001] This utility model relates to the field of satellite assembly, specifically to a satellite lifting, turning, and parking device. Background Technology

[0002] Currently, the most common methods for lifting and turning satellites in China involve using L-shaped beams with double hooks, or first lifting and transferring the satellite as a whole to a two-axis turntable, and then turning the satellite over by operating the pitch mechanism of the two-axis turntable.

[0003] When traditional large satellites are flipped using L-beams, (1) one side of the L-beam is placed on the parking fixture, and fasteners are installed between the L-beam and the parking fixture and tightened; (2) the satellite is lifted to the top of the L-beam, the satellite attitude is adjusted, the mounting holes of the satellite docking surface are aligned with the mounting holes of the L-beam docking surface, and then docked, fasteners are installed, and tightening torque is applied; (3) the main and auxiliary hooks of the crane are connected to both ends of the L-beam respectively; (4) the main and auxiliary hooks of the crane are simultaneously lifted horizontally to a safe height, the main hook of the crane descends, the auxiliary hook rises, and the L-beam and satellite are flipped 90° to a horizontal state; (5) the crane is operated to move the L-beam and satellite horizontally to the top of the parking fixture; (6) after aligning the mounting holes, docking is performed, the L-beam and satellite are parked on the parking fixture, fasteners are installed, and tightening torque is applied. Therefore, it can be seen that the traditional L-beam turning tool is complicated when performing a 90° turning operation on a large satellite. The tool cannot be removed after the satellite is turned over, and the L-beam occupies the interface of the satellite docking surface, which prevents the satellite from docking with other tooling.

[0004] When using a two-axis turntable to perform a satellite flipping operation, (1) the docking surface of the two-axis turntable is adjusted to a horizontal state; (2) the satellite is lifted to the docking surface of the two-axis turntable; (3) the satellite attitude is adjusted, the mounting holes are aligned, the satellite is placed on the mounting surface of the two-axis turntable, fasteners are installed, and tightening torque is applied; (4) the pitch mechanism of the two-axis turntable is operated to flip the satellite 90°. It can be seen that the process of using a two-axis turntable to perform a 90° flipping operation of the entire satellite is complicated. The two-axis turntable occupies the satellite docking surface, and the two-axis turntable vehicle body is too large, which seriously affects the subsequent operation of the satellite and cannot meet the requirements for satellite-rocket docking after the satellite flips.

[0005] For non-traditional satellite configurations that are large, lightweight, and lack a load-bearing cylinder structure, designing a separate L-shaped beam is costly and has limited functionality and versatility. Furthermore, the L-shaped beam occupies a significant amount of space and, after the satellite is flipped over, will occupy onboard interfaces, affecting docking operations after the satellite has flipped over.

[0006] In summary, using L-beams for satellite turning and parking involves high initial equipment costs, a long production cycle, and poor versatility of L-beam tooling. Using L-beams or two-axis turntables for satellite turning occupies both the satellite and launch vehicle docking surfaces, hindering the satellite's parking after turning or docking with other tooling. Turning and subsequent docking require multiple satellite lifting operations, increasing operational risks and leading to greater safety hazards.

[0007] To meet the needs of satellite rotation, there is an urgent need for a 90° satellite rotation tool that is safe and reliable, easy to operate, quick to assemble and disassemble, has fewer lifting and rotation procedures, high efficiency, and integrates lifting and rotation into one unit. This tool can simplify satellite rotation operations, reduce the number of times the entire satellite is lifted, shorten satellite rotation time, and improve operational efficiency. The functions of this tooling should include: (1) using the double hook of the crane to lift and transport the entire satellite; (2) using the double hook of the crane to operate synchronously to complete the 90° turning of the entire satellite; (3) after the satellite is turned to a vertical position, a single hook can be used to meet the lifting, docking and parking work of the entire satellite; (4) the installation and dismantling of the whole satellite lifting tooling is convenient and does not occupy the docking interface after the satellite is lifted, transported and turned over; (5) the whole satellite lifting tooling can select the double hook horizontal lifting and single hook vertical lifting tooling lifting point interface according to the satellite's center of mass position in different states, to ensure that the crane hook is close to the satellite's center of mass in the vertical direction during the lifting and turning of the satellite, to prevent the satellite from overturning during the lifting process and reduce the operational risk. Utility Model Content

[0008] In view of the deficiencies in the existing technology, the purpose of this utility model is to provide a satellite lifting, turning and parking device.

[0009] A satellite lifting, turning, and parking device according to the present invention includes: an isosceles trapezoidal support rod, a turning extension sleeve, a Z-shaped lifting adapter block, a whole satellite lifting point connecting plate, a turning extension rod, and a lifting adapter support rod;

[0010] The Z-shaped lifting adapter blocks are installed at both ends of the entire star body;

[0011] One end of the entire star body is fitted with a turning extension sleeve via a Z-shaped lifting adapter block, and the turning extension sleeve is connected to an isosceles trapezoidal support rod;

[0012] The other end of the entire star body is equipped with a star lifting point connecting plate and a turning extension rod via a Z-shaped lifting adapter block. The turning extension rod is connected to the lifting support rod via a sling.

[0013] Preferably, the isosceles trapezoidal strut is a trapezoidal frame structure formed by welding square tubes.

[0014] Preferably, the isosceles trapezoidal support is provided with a first vertical lifting center of gravity balancing point embedded part group, a second vertical lifting center of gravity balancing point embedded part group, a third vertical lifting center of gravity balancing point embedded part group, a first horizontal lifting center of gravity balancing point embedded part group, a second horizontal lifting center of gravity balancing point embedded part group, a first threaded lifting point embedded part, a second threaded lifting point embedded part, a through hole embedded part, and a third threaded lifting point embedded part;

[0015] The first vertical lifting center of gravity balancing point embedded part group, the second vertical lifting center of gravity balancing point embedded part group, the third vertical lifting center of gravity balancing point embedded part group, the first horizontal lifting center of gravity balancing point embedded part group, the second horizontal lifting center of gravity balancing point embedded part group, the first threaded lifting point embedded part, the second threaded lifting point embedded part, and the third threaded lifting point embedded part are provided with threaded holes and are connected to eye bolts through the threaded holes. The eye bolts are connected to the crane main hook through slings.

[0016] The through-hole embedded part is provided with a through hole, and the through hole of the through-hole embedded part is collinear with the axis of the threaded hole of the connected Z-type lifting adapter block.

[0017] Preferably, the first vertical lifting center of gravity balancing point embedded part group includes multiple embedded parts on the same circle, the second vertical lifting center of gravity balancing point embedded part group includes multiple embedded parts on the same circle, so the third vertical lifting center of gravity balancing point embedded part group includes multiple embedded parts on the same circle;

[0018] The first vertical lifting center of gravity balancing point embedded part group, the second vertical lifting center of gravity balancing point embedded part group, and the third vertical lifting center of gravity balancing point embedded part group are located in circles with different diameters and different centers, but they share a common embedded part lifting point.

[0019] Preferably, one side of the lifting rod is provided with a first lifting rod center of gravity balance point, a second lifting rod center of gravity balance point and a third lifting rod center of gravity balance point, and the other side of the lifting rod is provided with a first lifting rod point and a second lifting rod point.

[0020] Preferably, the first, second, and third lifting points of the lifting rod are provided in two sets and are symmetrical about the centerline of the lifting rod.

[0021] The first, second, and / or third lifting points of the spreader strut are connected to the turning extension rod via shackles and slings. The first and second lifting points of the spreader strut are connected to the crane auxiliary hook via shackles and slings.

[0022] Preferably, the lifting support rod is provided with a first weight-reducing through hole, a second weight-reducing through hole, and a third weight-reducing through hole.

[0023] Preferably, the entire star lifting point connecting plate has multiple through holes machined at both ends. The through holes of the entire star lifting point connecting plate are collinear with the through holes on the Z-shaped lifting adapter block. The through holes of the entire star lifting point connecting plate and the through holes of the Z-shaped lifting adapter block cooperate with the threaded holes on the entire star truss.

[0024] Preferably, one end of the Z-shaped lifting adapter block is machined with multiple threaded holes, and the threaded holes of the Z-shaped lifting adapter block are used to be collinear with the through holes on the isosceles trapezoidal support rod and the turning extension sleeve;

[0025] The other end of the Z-shaped lifting adapter block is machined with multiple through holes, and the through holes of the Z-shaped lifting adapter block are collinear with the threaded holes on the entire star truss.

[0026] Preferably, the Z-shaped lifting adapter block and the whole star lifting point connecting plate are made of aluminum alloy.

[0027] The isosceles trapezoidal support rod, the turning extension sleeve, the turning extension rod, and the lifting support rod are made of Q235B or Q345B steel.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] 1. This application integrates multiple functions such as horizontal hoisting of the entire satellite, vertical hoisting of the entire satellite, 90° rotation of the entire satellite, and vertical parking of the entire satellite into an integrated design, which has good versatility for satellites with non-traditional load-bearing tube structures;

[0030] 2. This application can balance the satellite's center of mass by selecting different combinations of lifting points, ensuring the stability of the satellite during horizontal lifting, vertical lifting, and 90° tilting, preventing tipping, and reducing the risk of satellite lifting and tilting.

[0031] 3. This application significantly reduces the cost of tooling production, simplifies the preparation work before lifting and turning, optimizes the 90° turning process of the whole satellite, and does not occupy the satellite docking surface. After turning, it does not affect the docking operation of the satellite with other tooling or with the rocket. It has good operability, improves the efficiency of satellite turning, and reduces the risk of satellite AIT (satellite assembly, integration and testing) process. Attached Figure Description

[0032] Other features, objects, and advantages of this invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0033] Figure 1 A schematic diagram of the overall structure of the satellite lifting, turning, and parking device;

[0034] Figure 2 This is a schematic diagram of the connection plate structure for the entire satellite's lifting points;

[0035] Figure 3 This is a schematic diagram of the lifting device strut structure;

[0036] Figure 4 A schematic diagram showing how a crane can lift the entire satellite using a satellite lifting, turning, and parking device.

[0037] As shown in the figure:

[0038]

[0039] Detailed Implementation

[0040] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0041] Example 1

[0042] like Figure 1 and 4 As shown, this embodiment includes: an isosceles trapezoidal support rod 1, a turning extension sleeve 2, a Z-shaped lifting adapter block 3, a whole-star lifting point connecting plate 4, a turning extension rod 5, and a lifting support rod 6; the isosceles trapezoidal support rod 1 is installed on the Z-shaped lifting adapter block 3 through the turning extension sleeve 2 and is installed on one end of the whole-star body 7 through the Z-shaped lifting adapter block 3; the whole-star lifting point connecting plate 4 is installed on the other end of the whole-star body 7 through the Z-shaped lifting adapter block 3, the turning extension rod 5 is installed on the Z-shaped lifting adapter block 3, and the turning extension rod 5 is connected to the lifting support rod 6 through a sling. One side of the isosceles trapezoidal strut 1 is connected to the Z-type lifting adapter block 3 at four points, indirectly connecting to the entire satellite 7 truss. The other side is connected to the main crane hook 25 via a lifting eye bolt. One end of the turning extension rod 5 is connected to the Z-type lifting adapter block 3 via fasteners, indirectly connecting to the entire satellite 7 truss. The other end is connected to the auxiliary crane hook 26 via a lifting strap. When the main crane hook 25 rises and the auxiliary crane hook 26 falls, the satellite can be turned 90° with both hooks. After the entire satellite 7 is turned from a horizontal state to a vertical state, the turning extension block 5 is removed. The satellite can then be docked with the parking fixture via the four Z-type lifting adapter blocks 3 to achieve vertical parking of the entire satellite 7. It can also be used to dock the satellite-rocket docking surface with the side-mounted adapter when the satellite is in a vertical state.

[0043] like Figure 2As shown, the isosceles trapezoidal strut 1 is designed with five sets of center-of-gravity balancing lifting points, corresponding to three different vertical lifting conditions of the entire satellite (4-point lifting): the first vertical lifting center-of-gravity balancing lifting point embedded part group 8 is used for vertical lifting of the entire satellite in its folded state when the propulsion system is not charged with propellant and the solar array is not installed; the second vertical lifting center-of-gravity balancing lifting point embedded part group 9 is used for vertical lifting of the entire satellite in its folded state when the propulsion system is not charged with propellant and the solar array is installed; the third vertical lifting center-of-gravity balancing lifting point embedded part group 10 is used for vertical lifting of the entire satellite in its folded state when the propulsion system is charged with propellant and the solar array is installed; and two horizontal lifting conditions of the entire satellite 7: the first horizontal lifting center-of-gravity balancing lifting point embedded part group 11 is used for horizontal lifting of the entire satellite in its folded state when the propulsion system is not charged with propellant and the solar array is not installed; the second horizontal lifting center-of-gravity balancing lifting point embedded part group 12 is used for horizontal lifting of the entire satellite in its folded state when the propulsion system is charged with propellant and the solar array is installed. Specifically, the isosceles trapezoidal strut 1 is equipped with a first vertical lifting center of gravity balancing point embedded part group 8, a second vertical lifting center of gravity balancing point embedded part group 9, a third vertical lifting center of gravity balancing point embedded part group 10, a first horizontal lifting center of gravity balancing point embedded part group 11, a second horizontal lifting center of gravity balancing point embedded part group 12, a first threaded lifting point embedded part 13, a second threaded lifting point embedded part 14, a through hole embedded part 15, and a third threaded lifting point embedded part 16; the first vertical lifting center of gravity balancing point embedded part group 8, the second vertical lifting center of gravity balancing point embedded part group 9, the third vertical lifting center of gravity balancing point embedded part group 10, a first horizontal lifting center of gravity balancing point embedded part group 11, a second horizontal lifting center of gravity balancing point embedded part group 12, a first threaded lifting point embedded part 13, a second threaded lifting point embedded part 14, a through hole embedded part 15, and a third threaded lifting point embedded part 16; Embedded parts group 9, third vertical lifting center of gravity balance point embedded parts group 10, first horizontal lifting center of gravity balance point embedded parts group 11, second horizontal lifting center of gravity balance point embedded parts group 12, first threaded lifting point embedded parts 13, second threaded lifting point embedded parts 14 and third threaded lifting point embedded parts 16 are provided with threaded holes and connected to eye bolts through the threaded holes. The eye bolts are connected to the crane main hook 25 through the lifting strap. Through hole embedded parts 15 are provided with through holes, and the through hole of through hole embedded parts 15 is collinear with the axis of the threaded hole of the connected Z-type lifting adapter block 3. The first vertical lifting center of gravity balancing point embedded part group 8 includes multiple embedded parts on the same circle, the second vertical lifting center of gravity balancing point embedded part group 9 includes multiple embedded parts on the same circle, therefore the third vertical lifting center of gravity balancing point embedded part group 10 includes multiple embedded parts on the same circle; the first vertical lifting center of gravity balancing point embedded part group 8, the second vertical lifting center of gravity balancing point embedded part group 9, and the third vertical lifting center of gravity balancing point embedded part group 10 are located in circles with different diameters and different centers, but share a common embedded part lifting point.

[0044] The first vertical lifting center of gravity balancing point embedded part group 8, the second vertical lifting center of gravity balancing point embedded part group 9, and the third vertical lifting center of gravity balancing point embedded part group 10 are determined according to the position of the satellite's center of gravity in the vertical state at different assembly stages. The center of the circle containing the four points of the first vertical lifting center of gravity balancing point embedded part group 8, the second vertical lifting center of gravity balancing point embedded part group 9, and the third vertical lifting center of gravity balancing point embedded part group 10 is the position of the satellite's center of gravity in the vertical state.

[0045] Because the number and location of payloads installed on the satellite vary at different assembly stages, when the initial stage has a small number of payloads and the center of mass is off-center from the geometric center, the first horizontal lifting center of mass balancing point embedded part group 11 can be used to install eye bolts for horizontal lifting. When the number of satellite payloads is large, the overall satellite mass is large, and the center of mass is off-center from the geometric center, the first horizontal lifting center of mass balancing point embedded part group 11 and the second horizontal lifting center of mass balancing point embedded part group 12 can be used in combination at the two farthest lifting points for horizontal lifting. When the satellite payloads are installed (after the solar array on one side is installed), and the center of mass of the entire satellite is close to the geometric center, the second horizontal lifting center of mass balancing point embedded part group 12 can be used to install eye bolts and then lift the satellite.

[0046] The first threaded lifting point embedded part 13 and the second threaded lifting point embedded part 14 are used as lifting points in the initial assembly stage of the satellite. They are suitable for horizontal lifting when the center of mass of the satellite is not eccentric. As backup lifting points, in the later stage of the satellite final assembly, due to the installation of loads such as on-board antennas, the lifting sling path of the first threaded lifting point embedded part 13 and the second threaded lifting point embedded part 14 is interfered with. Therefore, these lifting point embedded parts are no longer used in the later stage of the final assembly and in the horizontal lifting, 90° turning and vertical lifting processes during the satellite-rocket docking stage. Horizontal lifting mainly uses the first horizontal lifting center of mass balancing lifting point embedded part group 11 and the second horizontal lifting center of mass balancing lifting point embedded part group 12.

[0047] The third threaded lifting point embedded parts 16 are distributed at the four corners of the isosceles trapezoidal strut 1. In the later stage of satellite assembly, when all loads have been installed on the satellite and the vertical center of mass of the entire satellite is close to the geometric center of the satellite, lifting eye bolts can be installed on the third threaded lifting point embedded parts 16. The satellite can be vertically lifted using a four-point lifting method for vertical placement of the entire satellite and satellite-rocket docking operations. The through-hole embedded parts 15 are distributed at the four corners of the isosceles trapezoidal strut 1. They are designed according to the threaded hole positions of the satellite truss structure. The through-hole embedded parts 15 are only used to connect with the threaded holes on the Z-type lifting adapter block 3, indirectly connecting the isosceles trapezoidal strut 1 to the satellite truss through the Z-type lifting adapter block 3.

[0048] like Figure 3As shown, the first lifting point 17, the second lifting point 18, and the third lifting point 19 are provided on one side of the lifting rod 6, and the first lifting point 20 and the second lifting point 21 are provided on the other side of the lifting rod 6. Two sets of symmetrically arranged lifting points 17, 18, and 19 are provided on the first lifting support rod center of gravity balancing point 6. The first lifting support rod center of gravity balancing point 17, the second lifting support rod center of gravity balancing point 18, and / or the third lifting support rod center of gravity balancing point 19 are connected to the turning extension rod 5 through shackles and slings. The first lifting support rod center of gravity balancing point 17, the second lifting support rod center of gravity balancing point 18, and / or the third lifting support rod center of gravity balancing point 19 are used to ensure that under different satellite lifting conditions, the position of the lifting point below the lifting support rod 6 is adjusted so that the trolley auxiliary hook 26 is located above the center of gravity of the entire satellite body 7, preventing the entire satellite body 7 from tipping over during horizontal lifting. The first lifting support rod lifting point 20 and the second lifting support rod lifting point 21 are connected to the trolley auxiliary hook 26 through shackles and slings. The lifting support rod 6 is provided with a first weight reduction through hole 22, a second weight reduction through hole 23 and a third weight reduction through hole 24, which are designed for weight reduction of the lifting device.

[0049] The first spreader support point 20 and the second spreader support point 21 are connected to the gantry crane auxiliary hook 26 via shackles and slings. During horizontal lifting, the gantry crane auxiliary hook 26 is located between the first spreader support point 20 and the second spreader support point 21. The first spreader support point 20 and the second spreader support point 21 are set according to the deviation of the satellite's center of mass from its geometric center, and their principle is similar to that of a weighing lever. In actual use, it is more common to use the first spreader support directly below the first spreader support point 20. The center of gravity balancing point 17 of the pole is connected to the turning extension pole 5 via shackles and slings. The center of gravity balancing point 17 of the first spreader support pole, or the center of gravity balancing point 18 of the second spreader support pole, or the center of gravity balancing point 19 of the third spreader support pole, which is close to the third weight reduction through hole 24, is connected to the turning extension pole 5 via shackles and slings. By switching the positions of the three center of gravity balancing points of the spreader support poles close to the third weight reduction through hole 24, the position of the gantry auxiliary hook 26 in the vertical direction is indirectly adjusted, so that the gantry auxiliary hook 26 is close to the satellite center of gravity in the vertical direction.

[0050] In this embodiment, one end of the Z-type lifting adapter block 3 is machined with multiple threaded holes, which are collinear with the through holes on the isosceles trapezoidal strut 1 and the turning extension sleeve 2; the other end of the Z-type lifting adapter block 3 is machined with multiple through holes, which are collinear with the threaded holes on the entire star body 7 truss. Both ends of the entire star lifting point connecting plate 4 are machined with multiple through holes, which are collinear with the through holes on the Z-type lifting adapter block 3. The through holes of the entire star lifting point connecting plate 4 and the through holes of the Z-type lifting adapter block 3 together cooperate with the threaded holes on the entire star body 7 truss.

[0051] In one embodiment, the Z-type lifting adapter block 3 and the whole star lifting point connecting plate 4 are made of aluminum alloy; the isosceles trapezoidal support rod 1, the turning extension sleeve 2, the turning extension rod 5 and the lifting support rod 6 are made of Q235B or Q345B steel.

[0052] In one embodiment, the isosceles trapezoidal strut 1 is a trapezoidal frame structure formed by welding square tubes.

[0053] In use, a Z-type spreader adapter block 3 and a whole-star lifting point connecting plate 4 are installed on one side of the entire star body 7. The Z-type spreader adapter block 3 and the whole-star lifting point connecting plate 4 share the interface of the lifting point of the entire star body 7 and are connected to the entire star body 7 with M16×90 screws. The isosceles trapezoidal strut 1 is connected to the other side of the entire star body 7 by passing through the turning extension sleeve 2 with M16×185 screws. During the horizontal lifting of the entire star body 7, two M16 eye bolts are installed on the isosceles trapezoidal strut 1, and it is connected to the main hook 25 of the crane using shackles and a 2m long sling. The turning extension rod 5 on the other side of the entire star body 7 is connected to the lower part of the spreader strut 6 with shackles and a 5m long sling, and connected to the upper part of the crane auxiliary hook 26 using a 2m long sling. After the entire star body 7 is lifted horizontally, the main hook 25 of the crane is raised and the auxiliary hook 26 of the crane is lowered to complete the flipping of the entire star body. After flipping, the shackles, slings and flipping extension rods 5 on the lower end face of the star body are removed, and the entire star body 7 can be vertically placed on the parking fixture through the Z-type lifting adapter block 3.

[0054] Example 2

[0055] Example 2 is a preferred example of Example 1.

[0056] like Figure 1As shown, this embodiment includes: an isosceles trapezoidal support rod 1, a turning extension sleeve 2, a Z-shaped lifting adapter block 3, a whole-star lifting point connecting plate 4, a turning extension rod 5, and a lifting support rod 6; the isosceles trapezoidal support rod 1 is connected to the Z-shaped lifting adapter block 3 through the turning extension sleeve 2; the whole-star lifting point connecting plate 4 is a long strip-shaped sheet structure, and the whole-star lifting point connecting plate 4 is connected to the Z-star lifting adapter block 3; the turning extension rod 5 is connected to the Z-shaped lifting adapter block 3; the lifting support rod 6 is connected to the turning extension rod 5 through a sling; there are 4 turning extension sleeves 2, 8 Z-shaped lifting adapter blocks 3, 4 whole-star lifting point connecting plates 4, and 2 turning extension rods 5.

[0057] like Figure 2 As shown, the main material of the isosceles trapezoidal strut 1 is square tubing, which is a standard profile with a wall thickness of 5mm. All connections of the square tubing are fully welded. The isosceles trapezoidal strut 1 has five sets of embedded parts: the first vertical lifting center of gravity balance point embedded part group 8, the second vertical lifting center of gravity balance point embedded part group 9, the third vertical lifting center of gravity balance point embedded part group 10, the first horizontal lifting center of gravity balance point embedded part group 11, the second horizontal lifting center of gravity balance point embedded part group 12, the first threaded lifting point embedded part 13, the second threaded lifting point embedded part 14, and the third threaded lifting point embedded part 16 are provided with threaded holes, and the through hole embedded part 15 is a through hole. The first vertical lifting center of gravity balance point embedded part group 8 includes 4 embedded parts on the same circle; the second vertical lifting center of gravity balance point embedded part group 9 includes 4 embedded parts on the same circle; the third vertical lifting center of gravity balance point... The embedded part group 10 contains four embedded parts on the same circle; the first vertical lifting center of gravity balance point embedded part group 8, the second vertical lifting center of gravity balance point embedded part group 9, and the third vertical lifting center of gravity balance point embedded part group 10 are located on circles with different diameters and different centers, but share a common embedded part lifting point; the through hole of the through hole embedded part 15 is collinear with the axis of the threaded hole on the Z-type lifting adapter block 3; the threaded holes of the first vertical lifting center of gravity balance point embedded part group 8, the second vertical lifting center of gravity balance point embedded part group 9, the third vertical lifting center of gravity balance point embedded part group 10, the first horizontal lifting center of gravity balance point embedded part group 11, the second horizontal lifting center of gravity balance point embedded part group 12, the first threaded lifting point embedded part 13, the second threaded lifting point embedded part 14, and the third threaded lifting point embedded part 16 can all be connected to eye bolts for connecting points for horizontal or vertical lifting of satellites.

[0058] like Figure 3As shown, the main body material of the lifting support rod 6 is preferably Q235B or Q345B steel. The lifting support rod 6 is machined with a first lifting support rod center of gravity balance point 17, a second lifting support rod center of gravity balance point 18, and a third lifting support rod center of gravity balance point 19. The first lifting support rod center of gravity balance point 17, the second lifting support rod center of gravity balance point 18, and the third lifting support rod center of gravity balance point 19 can be connected to the star-mounted turning extension rod 5 by installing shackles and slings; the lifting support rod The first lifting point 17, the second lifting point 18, and the third lifting point 19 on the left and right sides of the rod 6 are used in combination to make the center of gravity of the entire star body 7 and the lifting point of the hook lie on the same vertical line. The first lifting point 20 and the second lifting point 21 can be connected to the crane auxiliary hook 26 through shackles and slings. The first weight reduction through hole 22, the second weight reduction through hole 23, and the third weight reduction through hole 24 are used for weight reduction of the overall structure.

[0059] like Figure 4 As shown, the second horizontal lifting center of gravity balancing point embedded part group 12 on the isosceles trapezoidal strut 1 is connected to the main crane hook 25 via a sling after the eye bolts are installed; the through hole embedded part 15 is installed to the Z-type spreader adapter block 3 via fasteners, and the Z-type spreader adapter block 3 is connected to the entire star body 7 truss via fasteners; the first spreader strut lifting point 20 and the second spreader strut lifting point 21 of the upper part of the spreader strut 6 are connected to the crane auxiliary hook 26 via a sling, and the first spreader strut center of gravity balancing point 17, the second spreader strut center of gravity balancing point 18 or the third spreader strut center of gravity balancing point 19 of the lower part of the spreader strut 6 are connected to the turning extension rod 5 via a sling; the turning extension rod 5 is indirectly installed to the entire star body 7 truss via the Z-type spreader adapter block 3; the crane main hook 25 rises and the crane auxiliary hook 26 descends, thus completing the turning of the entire star body 7 from a horizontal state to a vertical state. Status: The main hook 25 of the crane descends, and the auxiliary hook 26 of the crane rises, thus completing the flipping of the entire satellite 7 from a vertical to a horizontal state. After the entire satellite flipping fixture flips the entire satellite 7 to a vertical state, the fasteners between the flipping extension rod 5 and the Z-type lifting adapter block 3 are removed, and the flipping extension rod 5 is taken out. The satellite can then be vertically placed on the parking fixture through the four Z-type lifting adapter blocks 3 on one side of the entire satellite 7. When the entire satellite 7 is flipped 90° from a vertical parking state to a horizontal state, the fasteners between the Z-type lifting adapter block 3 on one side of the entire satellite 7 and the parking fixture are removed. The main hook 25 of the crane lifts the satellite, and the flipping extension rod 5 is installed on the upper half of the Z-type lifting adapter block 3 on one side of the satellite. The flipping extension rod 5 is connected to the lifting support rod 6 through a sling. The auxiliary hook 26 of the crane rises, and the main hook 25 of the crane descends, thus completing the flipping of the entire satellite from a vertical to a horizontal state.

[0060] The satellite tilting fixture integrates multiple functions such as horizontal lifting, vertical lifting, 90° tilting, and vertical parking into a single design, offering excellent versatility for satellites with non-traditional load-bearing cylinder structures. By selecting different combinations of lifting points, the fixture balances the satellite's center of gravity, ensuring stability during horizontal lifting, vertical lifting, and 90° tilting, preventing tipping and reducing the risks associated with lifting and tilting the entire satellite. The fixture significantly reduces production costs, simplifies preparations before lifting and tilting, optimizes the 90° tilting process, and does not obstruct the satellite's docking surface. After tilting, it does not affect docking operations with other fixtures or the rocket, demonstrating excellent operability, improving tilting efficiency, and reducing risks during the satellite's AIT (Autonomous In-Process) process.

[0061] Example 3

[0062] In this embodiment, the isosceles trapezoidal support rod 1 is formed by full welding of 80×60×5 Q345 standard rectangular tubing; multiple embedded parts are welded on the isosceles trapezoidal support rod 1 and M16 threaded holes are machined to form 5 sets of satellite center of gravity balance lifting points; M16 eye bolts can be installed in the threaded holes of the isosceles trapezoidal support rod 1 for lifting the entire satellite body 7, of which 3 sets of center of gravity balance lifting points are used for vertical lifting of the entire satellite body 7, and 2 sets of center of gravity balance lifting points are used for horizontal lifting of the entire satellite body 7 for turning over.

[0063] The lifting strut 6 is made of Q235B or Q345B steel. The upper part of the lifting strut 6 is connected to the lifting point position of the trolley auxiliary hook 26 and fixed. The lower part of the lifting strut 6 is machined with lifting points at different distances. During use, different combinations of lifting points can be selected according to the center of gravity position of the entire star body 7 being lifted, so that the position of the trolley auxiliary hook 26 in the vertical direction is close to the center of gravity of the satellite, ensuring the stability of the entire star body 7 during horizontal lifting.

[0064] Each Z-type lifting adapter block 3 is formed from aluminum alloy. One end of the Z-type lifting adapter block 3 has two threaded holes, which are collinear with the through holes on the isosceles trapezoidal strut 1 and the turning extension sleeve 2. The other end of the Z-type lifting adapter block 3 has two circular through holes, which are collinear with the threaded holes on the truss of the entire star body 7. After the entire star body 7 is turned to a vertical position, the turning extension rod 5 on the bottom surface of the turned star body 7 can be removed, and the four Z-type lifting adapter blocks 3 on the bottom surface of the turned star body can be connected to the parking fixture. The threaded holes on the Z-type lifting adapter block 3 are collinear with the through holes on the parking fixture.

[0065] The forming lifting point connecting plate 4 is made of aluminum alloy. The upper and lower ends of the forming star lifting point connecting plate 4 have 4 through holes, which are collinear with the through holes on the Z-type lifting adapter block 3. The through holes on the forming star lifting point connecting plate 4 and the through holes on the Z-type lifting adapter block 3 share the threaded holes on the truss of the forming star body 7. When the mass of the forming star is large, the forming star lifting point connecting plate 4 and the Z-type lifting adapter block 3 are used together. The forming star lifting point connecting plate 4 connects the two Z-type lifting adapter blocks 3 on the same side into a whole, which improves the structural strength. When the mass of the forming star is small, the Z-type lifting adapter block 3 can be used alone.

[0066] 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.

[0067] The specific embodiments of this utility model have been described above. It should be understood that this utility model 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 substantive content of this utility model. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A satellite lifting, turning, and parking device, characterized in that, include: Isosceles trapezoidal strut (1), turning extension sleeve (2), Z-type lifting adapter block (3), whole star lifting point connecting plate (4), turning extension rod (5) and lifting adapter strut (6); The Z-shaped lifting adapter block (3) is installed at both ends of the entire star body (7); One end of the entire star body (7) is fitted with a turning extension sleeve (2) via a Z-shaped lifting adapter block (3), and the turning extension sleeve (2) is connected to an isosceles trapezoidal support rod (1); The other end of the entire star body (7) is equipped with a star lifting point connecting plate (4) and a turning extension rod (5) through a Z-shaped lifting adapter block (3). The turning extension rod (5) is connected to the lifting support rod (6) through a sling.

2. The satellite lifting, turning, and parking device according to claim 1, characterized in that: The isosceles trapezoidal strut (1) is a trapezoidal frame structure made of square tubes welded together.

3. The satellite lifting, turning, and parking device according to claim 1, characterized in that: The isosceles trapezoidal strut (1) is provided with a first vertical lifting center of gravity balance point embedded part group (8), a second vertical lifting center of gravity balance point embedded part group (9), a third vertical lifting center of gravity balance point embedded part group (10), a first horizontal lifting center of gravity balance point embedded part group (11), a second horizontal lifting center of gravity balance point embedded part group (12), a first threaded lifting point embedded part (13), a second threaded lifting point embedded part (14), a through hole embedded part (15), and a third threaded lifting point embedded part (16). The first vertical lifting center of gravity balancing point embedded part group (8), the second vertical lifting center of gravity balancing point embedded part group (9), the third vertical lifting center of gravity balancing point embedded part group (10), the first horizontal lifting center of gravity balancing point embedded part group (11), the second horizontal lifting center of gravity balancing point embedded part group (12), the first threaded lifting point embedded part (13), the second threaded lifting point embedded part (14), and the third threaded lifting point embedded part (16) are provided with threaded holes and are connected to eye bolts through the threaded holes. The eye bolts are connected to the crane main hook (25) through slings. The through hole embedded part (15) is provided with a through hole, and the through hole of the through hole embedded part (15) is collinear with the threaded hole axis of the connected Z-type lifting adapter block (3).

4. The satellite lifting, turning, and parking device according to claim 3, characterized in that: The first vertical lifting center of gravity balance point embedded part group (8) includes multiple embedded parts on the same circle, the second vertical lifting center of gravity balance point embedded part group (9) includes multiple embedded parts on the same circle, so the third vertical lifting center of gravity balance point embedded part group (10) includes multiple embedded parts on the same circle; The first vertical lifting center of gravity balance point embedded part group (8), the second vertical lifting center of gravity balance point embedded part group (9), and the third vertical lifting center of gravity balance point embedded part group (10) have different circle diameters and different circle centers, but share a common embedded part lifting point.

5. The satellite lifting, turning, and parking device according to claim 1, characterized in that: The first lifting rod center of gravity balance point (17), the second lifting rod center of gravity balance point (18) and the third lifting rod center of gravity balance point (19) are provided on one side of the lifting rod (6), and the first lifting rod center of gravity balance point (20) and the second lifting rod center of gravity balance point (21) are provided on the other side of the lifting rod (6).

6. The satellite lifting, turning, and parking device according to claim 5, characterized in that: The first lifting rod center of gravity balance point (17), the second lifting rod center of gravity balance point (18) and the third lifting rod center of gravity balance point (19) are provided in two sets and are symmetrical about the center line of the lifting rod (6); The first lifting point (17), the second lifting point (18), and / or the third lifting point (19) of the lifting rod are connected to the turning extension rod (5) via shackles and slings. The first lifting point (20) and the second lifting point (21) of the lifting rod are connected to the crane auxiliary hook (26) via shackles and slings.

7. The satellite lifting, turning, and parking device according to claim 1, characterized in that: The lifting rod (6) is provided with a first weight reduction through hole (22), a second weight reduction through hole (23) and a third weight reduction through hole (24).

8. The satellite lifting, turning, and parking device according to claim 1, characterized in that: The entire star lifting point connecting plate (4) has multiple through holes processed at both ends. The through holes of the entire star lifting point connecting plate (4) are collinear with the through holes on the Z-type lifting adapter block (3). The through holes of the entire star lifting point connecting plate (4) and the through holes of the Z-type lifting adapter block (3) cooperate with the threaded holes on the truss of the entire star body (7).

9. The satellite lifting, turning, and parking device according to claim 1, characterized in that: The Z-type lifting adapter block (3) has multiple threaded holes at one end. The threaded holes of the Z-type lifting adapter block (3) are used to be collinear with the through holes on the isosceles trapezoidal support rod (1) and the turning extension sleeve (2). The other end of the Z-type lifting adapter block (3) is machined with multiple through holes, and the through holes of the Z-type lifting adapter block (3) are collinear with the threaded holes on the truss of the entire star body (7).

10. The satellite lifting, turning, and parking device according to claim 1, characterized in that: The Z-type lifting adapter block (3) and the whole star lifting point connecting plate (4) are made of aluminum alloy. The isosceles trapezoidal support rod (1), the turning extension sleeve (2), the turning extension rod (5), and the lifting support rod (6) are made of Q235B or Q345B steel.

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