Vertical hoisting device and method suitable for commercial rocket split type star cover assembly

Abstract

The invention relates to spaceflight launching supporting equipment, in particular to a vertical hoisting device and hoisting method suitable for a commercial rocket split type star cover assembly, the hoisting device comprises a vertical hoisting tool, a hoisting basket, a plurality of supporting arms and a supporting assembly, the vertical hoisting tool comprises a hoisting ring located at the top, and the hoisting basket is arranged on the vertical hoisting tool; the bottom of the vertical lifting tool is used for being detachably connected with the hanging basket, the hanging basket comprises an annular frame and a plurality of fairing outer ring connecting assemblies, the fairing outer ring connecting assemblies are used for being connected with fairings, the length of the supporting arm is adjustable, and one end of the supporting arm is provided with a lifting connector used for being connected with a satellite support. The middle of the supporting arm is hinged to the annular frame, the supporting arm is suitable for being in a vertical state or a horizontal state, and the supporting assembly is connected to the bottom of the annular frame. The integral vertical hoisting of the split type star cover assembly can be completed under the condition that a rocket does not need structures such as an adapter frame and a transition bracket, the structure is simple, the operation is convenient, and the cost is low.

Description

Technical Field

[0001] The present invention relates to a space launch support device, in particular to a vertical lifting device and a lifting method suitable for a split fairing assembly of a commercial rocket. Background Art

[0002] In the rocket general assembly stage, it is necessary to complete the general assembly process of the satellite (including the satellite bracket) and the fairing assembly with the rocket core stage module. Currently, a general solution is to install the satellite (including the satellite bracket) and the fairing into an integrated unit by adding connection structures such as adapter frames and transition brackets, and then perform lifting. The main process is as follows: Install the adapter frame and the transition bracket into an integrated unit at the general assembly station; install the satellite bracket and the satellite on the transition bracket, install the fairing on the adapter frame, and the satellite (including the satellite bracket) and the fairing are connected to form an integrated unit through the adapter frame and the transition bracket structure; connect a lifting device outside the adapter frame and then perform overall vertical lifting to complete the general assembly with the rocket core stage module. The vertical lifting of this integrated fairing assembly requires the rocket to add connection structures such as adapter frames and transition brackets, which increases the takeoff weight of the rocket, reduces the carrying capacity, has a high launch cost, and the lifting process is complex. In view of the requirements of commercial spaceflight for low launch cost, high efficiency, and commercialization of rockets, there is an urgent need for a vertical lifting device for a split fairing assembly of a commercial rocket that does not require connection structures such as adapter frames and transition brackets to improve the commercial competitiveness of the rocket. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a vertical lifting device and method suitable for a split fairing assembly of a commercial rocket, which can complete overall vertical lifting without adding connection structures such as adapter frames and transition brackets to the rocket, and has a simple structure and low cost.

[0004] To solve the above technical problem, the present application provides the following technical solutions:

[0005] A vertical lifting device suitable for a split fairing assembly of a commercial rocket according to the present invention includes a vertical lifting tool, a hanging basket, a plurality of support arms, and a support assembly.

[0006] The vertical lifting tool includes a lifting ring at the top, and the bottom of the vertical lifting tool is detachably connected to the hanging basket.

[0007] The hanging basket includes an annular frame and a plurality of fairing outer ring connection components, and the fairing outer ring connection components are used to connect the fairing, and the plurality of fairing outer ring connection components are arranged in sequence along the circumference of the annular frame.

[0008] The length of the support arm is adjustable. One end of the support arm is provided with a lifting joint for connecting to the satellite bracket. The middle part of the support arm is hinged to the annular frame, and the support arm expands and contracts along the radial direction of the annular frame. A plurality of the support arms are arranged in sequence along the circumferential direction of the annular frame. The support arm is adapted to be in a vertical state or a horizontal state.

[0009] The support assembly is connected to the bottom of the annular frame.

[0010] Compared with the prior art, the split vertical lifting device applicable to the commercial rocket fairing assembly of the present invention has at least the following beneficial effects:

[0011] A vertical lifting device applicable to the split fairing assembly of a commercial rocket of the present invention includes a vertical lifting tool, a hanging basket, and a support arm. The hanging basket includes a plurality of outer fairing connection components. One end of the support arm is provided with a lifting joint, and the support arm is adapted to be in a vertical state or a horizontal state. Without adding structures such as an adapter frame and a transition bracket to connect the satellite (including the satellite bracket) and the fairing into a whole on the rocket, the overall lifting of the split fairing assembly can be completed for general assembly with the rocket. The structure is simple, the operation is convenient, safe, and reliable, effectively reducing the take-off weight of the rocket, improving the carrying capacity, reducing the rocket launch cost, and enhancing the commercial competitiveness of the rocket.

[0012] The following further describes the split vertical lifting device applicable to the commercial rocket fairing assembly of the present invention with reference to the accompanying drawings. Description of the Drawings

[0013] Figure 1 It is a schematic structural diagram of the split vertical lifting device applicable to the commercial rocket fairing assembly of the present invention;

[0014] Figure 2 It is a schematic structural diagram of the support arm in the retracted state in the split vertical lifting device applicable to the commercial rocket fairing assembly of the present invention;

[0015] Figure 3 It is a schematic structural diagram of the support arm in the extended state in the split vertical lifting device applicable to the commercial rocket fairing assembly of the present invention;

[0016] Figure 4 It is a schematic structural diagram of the support arm in the split vertical lifting device applicable to the commercial rocket fairing assembly of the present invention;

[0017] Figure 5 It is one of the partial structural schematic diagrams of the split vertical lifting device applicable to the commercial rocket fairing assembly of the present invention;

[0018] Figure 6This is the second partial structural schematic diagram of the split-type vertical lifting device applicable to the commercial rocket fairing assembly of the present invention. Detailed implementation manners

[0019] As Figure 1 、 Figure 2 、 Figure 3 shown, a split-type vertical lifting device applicable to the commercial rocket fairing assembly of the present invention includes a vertical lifting tool 01, a hanging basket 02, a plurality of support arms 03, and a support assembly 04.

[0020] The vertical lifting tool 01 includes a lifting ring 11 at the top, and the bottom of the vertical lifting tool 01 is used for detachably connecting with the hanging basket 02.

[0021] The hanging basket 02 includes an annular frame 21 and a plurality of fairing outer ring connection components 25. The annular frame 21 is a frame structure with a certain width. The fairing outer ring connection components 25 are used for connecting the fairing, and the plurality of fairing outer ring connection components 25 are arranged in sequence along the circumference of the annular frame 21.

[0022] The length of the support arm 03 is adjustable. One end of the support arm 03 is provided with a lifting joint 30, and the lifting joint 30 is used for connecting with the satellite bracket. The middle part of the support arm 03 is hinged to the annular frame 21, and the support arm 03 expands and contracts along the radial direction of the annular frame 21. The plurality of support arms 03 are arranged in sequence along the circumference of the annular frame 21, and the support arm 03 is adapted to be in a vertical state or a horizontal state.

[0023] The support assembly 04 is connected to the bottom of the annular frame 21, and the support assembly 04 is used for placing on the ground.

[0024] As Figure 2 、 Figure 3As shown in the figure, when the split-type vertical hoisting device of the present invention applicable to the combined body of the nose cone and satellite of a commercial rocket is in use, it is placed on the ground through the support assembly 04. The support arm 03 is retracted to the shortest and kept in a vertical state. It is connected to the lifting ring 11 through the hook in the site, and the vertical lifting tool 01 is lifted above the hanging basket 02. The bottom of the vertical lifting tool 01 is connected to the annular frame 21 of the hanging basket 02. Then, the hoisting device of the present invention is lifted and moved above the combined body of the nose cone and satellite, and then moved downward and sleeved outside the combined body of the nose cone and satellite until the position of the connection part between the annular frame 21 and the combined body of the nose cone and satellite is matched; adjust the position of the outer-ring connection assembly 25 of the fairing, align the connection holes, and connect and fix the outer ring of the fairing to the outer-ring connection assembly 25 of the fairing; drive the hoisting device of the present invention and the fairing to move upward through the hook in the site, and make the support arm 03 turn to a horizontal state and remain in the horizontal state. Adjust the length of the support arm 03 so that the lifting joint 30 extends to the position connected to the satellite support. Connect and fix the lifting joint 30 to the satellite support; lift the hoisting device of the present invention and the combined body of the nose cone and satellite as a whole above the rocket through the hook in the site and then slowly lower it. After the satellite support in the combined body of the nose cone and satellite is centered and in contact with the rocket support surface, disconnect the connection between the lifting joint 30 of the support arm 03 and the satellite support, shorten the length of the support arm 03 and turn the support arm 03 to a vertical state and remain in the vertical state; continue to lower the hoisting device of the present invention and the combined body of the nose cone and satellite. After the fairing is centered and in contact with the rocket support surface, disconnect the connection between the outer-ring connection assembly 25 of the fairing and the fairing; lift the hoisting device of the present invention upward away from the combined body of the nose cone and satellite through the hook in the site, and the hoisting process ends.

[0025] A split-type vertical hoisting device of the present invention applicable to the combined body of the nose cone and satellite of a commercial rocket includes a vertical lifting tool 01, a hanging basket 02, and a support arm 03. The hanging basket 02 includes a plurality of outer-ring connection assemblies 25 of the fairing. One end of the support arm 03 is provided with a lifting joint 30. The support arm 03 is adapted to be in a vertical state or a horizontal state. Without adding structures such as an adapter frame and a transition bracket to connect the satellite (including the satellite support) and the fairing as a whole to the rocket, the overall hoisting of the split-type combined body of the nose cone and satellite can be completed for general assembly with the rocket. The structure is simple, the operation is convenient, safe, and reliable, effectively reducing the take-off weight of the rocket, improving the carrying capacity, reducing the rocket launch cost, and enhancing the commercial competitiveness of the rocket.

[0026] Optionally, as Figure 2 、 Figure 3As shown in the figure, the hanging basket 02 further includes a plurality of swivel seats 22, a plurality of first tie rods 23, and a plurality of second tie rods 24. The swivel seats 22, the first tie rods 23, and the second tie rods 24 are in one-to-one correspondence. The swivel seats 22 and the first tie rods 23 are both located on the outer side wall of the annular frame 21, and the second tie rods 24 are located on the inner side wall of the annular frame 21. The swivel seats 22 are connected to the bottom surface of the annular frame 21. One end of each first tie rod 23 and one end of each second tie rod 24 are both connected to the annular frame 21. The connection points of the first tie rods 23 and the second tie rods 24 with the annular frame 21 are both above the swivel seats 22. The plurality of swivel seats 22 are arranged in sequence along the circumferential direction of the annular frame 21. The middle parts of the respective support arms 03 are hinged to one swivel seat 22. The other ends of the first tie rods 23 are all used to connect to the first ends of the support arms 03 when the support arms 03 are in the vertical state, so as to keep the support arms 03 in the vertical state. The other ends of the second tie rods 24 are all used to connect to the second ends of the support arms 03 when the support arms 03 are in the horizontal state, so as to keep the support arms 03 in the horizontal state. Specifically, the swivel seats 22 are welded to the annular frame 21. By means of the first tie rods 23 and the second tie rods 24, the support arms 03 can be kept in the vertical state or the horizontal state, making the split vertical lifting device of the present invention suitable for the commercial rocket fairing assembly more stable during the lifting process.

[0027] Optionally, as Figure 4 shown, the support arm 03 includes a primary arm 31, a secondary arm 32, a tertiary arm 33, a primary screw drive pair 34, and a secondary screw drive pair 35. The tertiary arm 33 is arranged inside the secondary arm 32, and the secondary arm 32 is arranged inside the primary arm 31. The tertiary arm 33 is adapted to move relative to the secondary arm 32 along the length direction through the secondary screw drive pair 35, and the secondary arm 32 is adapted to move relative to the primary arm 31 along the length direction through the primary screw drive pair 34. The primary arm 31 is connected to the swivel seat 22 through a rotary shaft 36, and the lifting joint 30 is connected to the tertiary arm 33. Specifically, the primary arm 31, the secondary arm 32, and the tertiary arm 33 are all square tubes. The primary arm 31 is further provided with a connection seat for connecting to the first tie rod 23, a connection seat for connecting to the second tie rod 24, and an operating handle. When it is necessary to adjust the length of the support arm 03, the primary screw drive pair 34 and the secondary screw drive pair 35 are rotated through the operating handle, so that the primary arm 31 moves relative to the secondary arm 32, and the secondary arm 32 moves relative to the tertiary arm 33 until the appropriate length is adjusted.

[0028] Optionally, as Figure 6As shown in the figure, the first pull rod 23 includes a first upper ear 231, a pull rod body 232, and a first lower ear 233. The first upper ear 231 and the first lower ear 233 are respectively connected to both ends of the pull rod body 232. The first pull rod 23 is hinged to the annular frame 21 through the first upper ear 231, and is used to be connected to the support arm 03 in the vertical state through the first lower ear 233. Specifically, an ear seat 211 is provided on the annular frame 21, and the first upper ear 231 is connected to the ear seat 211.

[0029] Optionally, the second pull rod 24 includes a second upper ear 241, a first upper stop pin 242, a first screw sleeve 243, a second lower ear 244, and a first lower stop pin 245. The second upper ear 241 is connected to the ear seat 211 on the annular frame 21 through the first upper stop pin 242, and the second lower ear 244 is used to be connected to the support arm 03 in the horizontal state through the first lower stop pin 245.

[0030] Optionally, as Figure 5 shown, the vertical sling 01 further includes a hanger 12, a plurality of first slings 13, and a plurality of second slings 14. The first slings 13 and the second slings 14 are in one-to-one correspondence. The hanger 12 is placed horizontally. One end of each second sling 14 is respectively used to be hinged to different positions on the circumference of the annular frame 21. One end of each first sling 13 is hinged to the lifting ring 11. The other ends of each first sling 13 and the other ends of each second sling 14 are hinged to different positions of the hanger 12. The second slings 14 are parallel to each other. The connection point of one first sling 13 and the hanger 12 and the connection point of one second sling 14 and the hanger 12 are located at the same position. Specifically, it further includes a plurality of shackles 15, an upper ear 16, a lower ear 17, an upper pin 161, a middle pin 181, and a lower pin 171. Each first sling 13 is respectively connected to the lifting ring 11 through a shackle 15. The first sling 13 is connected to the upper ear 16 through the upper pin 161. The second sling 14 is connected to the lower ear 17 through the lower pin 171. The upper ear 16 and the lower ear 17 are connected to the hanger 12 through the middle pin 181. A plurality of upper connection seats are evenly distributed along the axial direction on the upper edge of the annular frame 21. Each second sling 14 is respectively connected to the connection seat through a pin 141. Since each second sling 14 is hinged to different positions of the hanger 12, it is convenient to connect the second sling 14 to the annular frame 21 during use.

[0031] Optionally, there are four first slings 13 and four second slings 14. The hanger 12 is a quadrilateral frame. The connection points of the first slings 13 and the second slings 14 with the hanger 12 are located at the four vertices of the hanger 12.

[0032] Optionally, the outer fairing connection assembly 25 includes a mounting base 251 and a mounting frame 252. The mounting frame 252 includes a bottom plate and side plates, and the bottom plate and the side plates form an L shape. A long circular hole extending in the radial direction of the annular frame 21 is provided on the bottom plate, and a connection hole for connecting with the outer fairing is provided on the side plate. The mounting base 251 is connected to the annular frame 21, and the mounting frame 252 is connected to the mounting base 251 through a connecting member passing through the long circular hole. Moving the mounting frame 252 relative to the mounting base 251 along the long circular hole can adjust the position of the connection hole, facilitating the connection with the outer fairing.

[0033] Optionally, the support assembly 04 includes a plurality of legs, and the legs are evenly distributed along the circumferential direction of the annular frame 21. Each leg includes a leg arm 41, a lifting member 42, and a support disk 43. The cross-sectional area of the support disk 43 is larger than that of the leg arm 41. The support disk 43 is used for supporting on the ground. The lifting member 42 is connected to the support disk 43, one end of the leg arm 41 is connected to the lifting member 42, and the other end is connected to the bottom of the annular frame 21. Since the leg includes the leg arm 41, the lifting member 42, and the support disk 43, and the support disk 43 is used for supporting on the ground, the height of the support assembly 04 can be adjusted through the lifting member 42, making the support of the present invention more stable and more convenient to use.

[0034] The method for hoisting using the above-mentioned split vertical hoisting device applicable to the commercial rocket fairing assembly includes the following steps:

[0035] (1) Place the hanging basket 02 on the ground through the support assembly 04, retract the support arm 03 to the shortest and flip it to the vertical state, and connect and fix the first pull rod 23 to the support arm 03;

[0036] (2) Connect the vertical hoisting tool 01 to the hanging basket 02 above by connecting the in-site hook to the lifting ring 11, and connect the bottom of the second sling 14 to the annular frame 21 of the hanging basket 02;

[0037] (3) Lift and move the vertical hoisting tool 01 and the hanging basket 02 above the fairing assembly by the in-site hook, and then move vertically downward at a speed of 0.5 m / min to 5 m / min so that the annular frame 21 is sleeved on the fairing assembly until it matches the connection part;

[0038] (4) Adjust the position of the mounting frame 252 to align the connection hole on the side plate of the mounting frame 252 for connecting with the outer fairing with the connection hole of the outer fairing, and connect and fix the outer fairing to the mounting frame 252;

[0039] (5) Lift the vertical sling 01, the hanging basket 02 and the fairing upward at a speed of 0.1 m / min to 0.5 m / min by 5 mm to 10 mm with the hook in the site, release the connection between the first pull rod 23 and the support arm 03, turn the support arm 03 to the horizontal state, and connect and fix the second pull rod 24 to the support arm 03;

[0040] (6) Extend the secondary arm 32 and the tertiary arm 33 synchronously to the position connected to the satellite support at a speed of 50 mm / min to 500 mm / min, adjust the position of the lifting joint 30, and connect and fix the lifting joint 30 to the satellite support;

[0041] (7) Lift the vertical sling 01, the hanging basket 02 and the satellite fairing assembly as a whole above the rocket by the hook in the site and then slowly lower it. After the satellite support in the satellite fairing assembly contacts the rocket support surface in alignment, release the connection between the lifting joint 30 and the satellite support, retract the secondary arm 32 and the tertiary arm 33, release the connection between the support arm 03 and the second pull rod 24, turn the support arm 03 to the vertical state, and connect and fix the first pull rod 23 to the support arm 03;

[0042] (8) The vertical sling 01 and the hanging basket 02 continue to lower. When the fairing contacts the rocket support surface in alignment, release the connection between the mounting bracket 252 and the fairing;

[0043] (9) Lift the vertical sling 01 and the hanging basket 02 away from the satellite fairing assembly at a speed of 0.5 m / min to 5 m / min, and the split vertical lifting process of the satellite fairing assembly ends.

[0044] The embodiments described above are only used to describe the preferred embodiments of the present invention, and do not limit the scope of the present invention. Without departing from the design spirit of the present invention, various deformations and improvements made by those of ordinary skill in the art to the technical solutions of the present invention shall fall within the protection scope determined by the claims of the present invention.

Claims

1. A vertical lifting device applicable to a split satellite fairing assembly of a commercial rocket, characterized in that, It includes a vertical sling (01), a hanging basket (02), multiple support arms (03), and a support assembly (04). The vertical sling (01) includes a lifting ring (11) at the top, and the bottom of the vertical sling (01) is used for detachably connecting to the hanging basket (02). The hanging basket (02) includes an annular frame (21) and multiple fairing outer ring connection assemblies (25). The fairing outer ring connection assemblies (25) are used for connecting fairings, and the multiple fairing outer ring connection assemblies (25) are arranged in sequence along the circumference of the annular frame (21). The length of the support arm (03) is adjustable. One end of the support arm (03) is provided with a lifting joint (30), and the lifting joint (30) is used for connecting to a satellite bracket. The middle part of the support arm (03) is hinged to the annular frame (21), and the support arm (03) expands and contracts along the radial direction of the annular frame (21). The multiple support arms (03) are arranged in sequence along the circumference of the annular frame (21). The support arm (03) is adapted to be in a vertical state or a horizontal state. The support assembly (04) is connected to the bottom of the annular frame (21).

2. The vertical lifting device for the split satellite fairing assembly applicable to commercial rockets according to claim 1, wherein The hanging basket (02) further includes multiple slewing seats (22), multiple first tie rods (23), and multiple second tie rods (24). The slewing seats (22), the first tie rods (23), and the second tie rods (24) are in one-to-one correspondence. The slewing seats (22) and the first tie rods (23) are both located on the outer side wall of the annular frame (21), and the second tie rods (24) are located on the inner side wall of the annular frame (21). The slewing seats (22) are connected to the bottom surface of the annular frame (21). One end of the first tie rod (23) and one end of the second tie rod (24) are both connected to the annular frame (21). The connection points of the first tie rod (23) and the second tie rod (24) with the annular frame (21) are both above the slewing seats (22). The multiple slewing seats (22) are arranged in sequence along the circumference of the annular frame (21). The middle parts of the respective support arms (03) are hinged to one of the slewing seats (22). The other end of the first tie rod (23) is used for connecting to the first end of the support arm (03) when the support arm (03) is in a vertical state, and the other ends of the second tie rods (24) are all used for connecting to the second end of the support arm (03) when the support arm (03) is in a horizontal state.

3. The vertical lifting device for the split satellite fairing assembly applicable to commercial rockets according to claim 2, characterized in that, The support arm (03) includes a first-stage arm (31), a second-stage arm (32), a third-stage arm (33), a first-stage screw drive pair (34), and a second-stage screw drive pair (35). The third-stage arm (33) is disposed within the second-stage arm (32), and the second-stage arm (32) is disposed within the first-stage arm (31). The third-stage arm (33) is adapted to move relative to the second-stage arm (32) along the length direction through the second-stage screw drive pair (35), and the second-stage arm (32) is adapted to move relative to the first-stage arm (31) along the length direction through the first-stage screw drive pair (34). The first-stage arm (31) is connected to the slewing base (22) through a rotary shaft (36), and the lifting joint (30) is connected to the third-stage arm (33).

4. The vertical lifting device for the split satellite fairing assembly applicable to commercial rockets according to claim 3, characterized in that, The first pull rod (23) includes a first upper lug (231), a pull rod body (232), and a first lower lug (233). The first upper lug (231) and the first lower lug (233) are respectively connected to both ends of the pull rod body (232). The first pull rod (23) is hinged to the annular frame (21) through the first upper lug (231) and connected to the support arm (03) in the vertical state through the first lower lug (233).

5. The vertical lifting device for the split satellite fairing assembly applicable to commercial rockets according to claim 4, characterized in that, The second pull rod (24) includes a second upper lug (241), a first upper stop pin (242), a first screw sleeve (243), a second lower lug (244), and a first lower stop pin (245). The second upper lug (241) is connected to the annular frame (21) through the first upper stop pin (242), and the second lower lug (244) is used to connect to the support arm (03) in the horizontal state through the first lower stop pin (245).

6. The vertical hoisting device for the split satellite fairing assembly applicable to commercial rockets according to claim 5, characterized in that The vertical lifting device (01) further includes a lifting frame (12), a plurality of first suspension straps (13), and a plurality of second suspension straps (14). The first suspension straps (13) and the second suspension straps (14) are in one-to-one correspondence. The lifting frame (12) is placed horizontally. One end of each of the second suspension straps (14) is respectively used to connect to different positions along the circumference of the annular frame (21). One end of each of the first suspension straps (13) is hinged to the lifting ring (11). The other end of each of the first suspension straps (13) and the other end of each of the second suspension straps (14) are hinged to different positions of the lifting frame (12). The second suspension straps (14) are parallel to each other. The connection point of one first suspension strap (13) and the lifting frame (12) and the connection point of one second suspension strap (14) and the lifting frame (12) are located at the same position.

7. The vertical lifting device for the split satellite fairing assembly applicable to commercial rockets according to claim 6, characterized in that, There are four first suspension straps (13) and four second suspension straps (14). The connection points of the first suspension straps (13) and the second suspension straps (14) with the lifting frame (12) are located at the four vertices of the lifting frame (12).

8. The vertical lifting device applicable to the split satellite fairing assembly of commercial rockets according to claim 7, characterized in that, The outer fairing connecting assembly (25) includes a mounting base (251) and a mounting frame (252). The mounting frame (252) includes a bottom plate and side plates. The bottom plate and the side plates form an L shape. The bottom plate is provided with an oblong hole extending along the radial direction of the annular frame (21). The side plate is provided with a connection hole for connecting with the outer fairing. The mounting base (251) is connected to the annular frame (21), and the mounting frame (252) is connected to the mounting base (251) through a connecting piece passing through the oblong hole.

9. The vertical lifting device for the split satellite fairing assembly applicable to commercial rockets according to claim 8, wherein, The support assembly (04) includes a plurality of legs. Each leg is evenly distributed along the circumferential direction of the annular frame (21). The leg includes a leg arm (41), a lifting member (42), and a support disk (43). The support disk (43) is used for supporting on the ground. The lifting member (42) is connected to the support disk (43). One end of the leg arm (41) is connected to the lifting member (42), and the other end is connected to the bottom of the annular frame (21).

10. A method of hoisting using the vertical hoisting device for the split star fairing assembly of a commercial rocket according to any one of the above claims 1-9, comprising the following steps: (I) Place the hanging basket (02) on the ground through the support assembly (04), retract the support arm (03) to the shortest and flip it to the vertical state, and connect the first pull rod (23) to the support arm (03); (II) Lift the vertical hoisting tool (01) above the hanging basket (02) through the lifting ring (11), and connect the second sling (14) to the annular frame (21) of the hanging basket (02); (III) Move the vertical hoisting tool (01) and the hanging basket (02) above the star fairing assembly, and then move vertically downward so that the annular frame (21) is sleeved on the star fairing assembly; (IV) Adjust the position of the mounting frame (252) on the hanging basket (02), and connect the outer fairing to the mounting frame (252); (V) Lift the vertical hoisting tool (01), the hanging basket (02), and the fairing upward by 5 mm to 10 mm, disconnect the connection between the first pull rod (23) and the support arm (03), flip the support arm (03) to the horizontal state, and connect the second pull rod (24) to the support arm (03); (VI) Extend the secondary arm (32) and the tertiary arm (33) synchronously to the position where they are connected to the satellite support, and connect the lifting joint (30) to the satellite support; (VII) Lift the vertical hoisting tool (01), the hanging basket (02), and the star fairing assembly as a whole above the rocket and then lower them. After the satellite support in the star fairing assembly is in centering contact with the rocket support surface, disconnect the connection between the lifting joint (30) and the satellite support, retract the support arm (03) to the shortest, disconnect the connection between the support arm (03) and the second pull rod (24), flip the support arm (03) to the vertical state, and connect and fix the first pull rod (23) to the support arm (03); (8) Continue to lower the vertical sling (01) and the hanging basket (02). After the fairing makes centered contact with the rocket support surface, disconnect the mounting bracket (252) from the fairing. (9) Move the vertical sling (01) and the hanging basket (02) upward to lift them off the star-fairing assembly.

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