Butt joint device based on hoisting type small envelope rocket multi-engine single-machine parallel connection structure

Abstract

The utility model discloses a docking device based on a hoisting type small envelope rocket multi-engine single-machine parallel structure. The docking device is characterized by comprising a crane (1), an inclined steel cable (2), a cross beam (3), a length adjusting device (4), a profiling hoop (6) and a combined hoop (7), the rocket engine (5) is composed of a spray pipe (8), an engine body (9) and a rack (10). According to the butt joint device, a combined type holding ring and profiling hoop structure is designed by means of only two force bearing points on the engine, the structure is simplified, the envelope of the butt joint device of the multi-engine single-machine parallel connection structure is smaller than that of a single engine body, single engine butt joint of the multi-engine single-machine parallel connection structure in a narrow space under complex working conditions is achieved, and the butt joint efficiency is improved. The problem of interference in the butt joint process of all the engines in the multi-engine single-machine parallel structure is solved, meanwhile, safety risks are eliminated, and the butt joint reliability and working efficiency of the multi-engine single-machine parallel structure in a narrow space under complex working conditions are improved.

Description

Technical Field

[0001] The utility model relates to a rocket engine technology, in particular to a rocket body and a machine splicing technology, specifically a single-machine parallel structure docking device based on a hoisting small envelope rocket multi-engine. Background Art

[0002] There are two main ways of parallel docking of multiple engines of a launch vehicle. One is that a single engine is docked with the rocket body through a rack, and the other is that multiple engines (two or four engines) are docked and assembled with the rocket body through a common rack.

[0003] At present, most types of rocket engines are docked horizontally, with the engine in a vertical position (nozzle facing downward) when parked. For engines with smaller mass, the engine is lifted by double hooks on the engine frame and the engine throat to flip the engine to a horizontal position for docking with the rocket body. For engines with larger mass, a squirrel cage-type tooling is generally used to connect the engine frame process hole, flip the squirrel cage and engine assembly to a horizontal position for docking with the rocket body.

[0004] The only example of vertical engine docking was a certain model of core stage. The engine was a dual-engine shared frame structure. Due to the large mass of the engine, the frame deformed greatly during the horizontal docking process, the docking holes were difficult to align, and the installation of the docking bolts was relatively difficult. Therefore, a vertical docking method was adopted to dock the engine with the rear transition section and tail section in a vertical state, and then the entire assembly was flipped horizontally and docked horizontally with the rocket body.

[0005] There is no parallel docking and assembly of multiple engines in the current domestic launch vehicles. A new model of rocket adopts a parallel structure of multiple engines (not a shared frame) for the first time. Figure 8 As shown, there are great differences in the number of engines, structural form and installation method compared with existing models. The multi-engine parallel structure leads to a small space in the engine compartment, small gaps between each engine, and unavoidable interference between each engine and between the engine and tooling, which greatly increases the difficulty of docking and assembling the multi-engine parallel structure.

[0006] (1) The docking device is large in structure and exceeds the envelope of the existing rocket engine body.

[0007] At present, the docking technology for engines of active models is all single-machine docking, and the docking devices all adopt a squirrel-cage structure. After the engine is dropped into the squirrel cage for connection, the squirrel cage and product assembly are lifted vertically, flipped to a horizontal state, and dropped onto a docking trolley for docking. The squirrel-cage hoist itself has a large structure, far exceeding the envelope of the rocket engine itself. When used for docking of multiple-engine single-machine parallel structures, it will inevitably interfere with nearby engines and other structures on the rocket, making docking impossible.

[0008] (2) The rocket engine and environment structures are complex, and the docking device has a single attitude adjustment method.

[0009] At present, the new generation of manned rockets adopts a docking solution with a multi-engine single-unit parallel structure (non-shared frame). Compared with the existing rockets, the rocket engine's main structure and rocket engine environment are more complex, there are fewer parts supported by the lifting fixture, and the operating space is more limited. The existing hoisting docking solution that only uses a crane to adjust the attitude cannot meet the docking requirements of the new generation of manned carrier rockets with multiple engines in parallel. Utility Model Content

[0010] The purpose of the utility model is to design a docking device for a multi-engine single-unit parallel structure based on a hoisting-type small-envelope rocket in order to solve the problem of interference that is prone to occur during the docking process of each engine in a multi-engine single-unit parallel structure. The utility model makes full use of the only two load-bearing points on the engine to design a combined holding ring and a contoured holding hoop structure, thereby simplifying the structure of the rocket engine docking device, making the overall envelope of the docking device smaller than the envelope of the single engine, and realizing the docking of a single engine of a multi-engine single-unit parallel structure in a narrow space under complex working conditions, solving the problem of interference in the docking process of each engine in the multi-engine single-unit parallel structure, and eliminating safety risks at the same time, thereby improving the reliability and work efficiency of the docking of the multi-engine single-unit parallel structure in a narrow space under complex working conditions.

[0011] The technical solution of the utility model is:

[0012] A docking device based on a single-unit parallel structure of a multi-engine of a hoisting small envelope rocket: characterized in that it is composed of a crane 1, an inclined steel cable 2, a crossbeam 3, a length adjustment device 4, a contour clamp 6 and a combined clamp ring 7; the rocket engine 5 is composed of a nozzle 8, an engine body 9 and a frame 10; the nozzle 8 and the frame 10 are connected and fixed through the engine body 9; the combined clamp ring 7 is fixed on the frame 10, and the contour clamp 6 is fixed on the nozzle 8; the crane 1 is connected to the crossbeam 3 through the inclined steel cable 2, and each crossbeam 3 is respectively connected to the contour clamp 6 and the combined clamp ring 7 through two length adjustment devices 4. structural connection; the three-degree-of-freedom movement, pitch and left-right swing of the rocket engine 5 are realized by two cranes 1, and the rotation of the rocket engine 5 along the axis is realized by adjusting the length of the length adjustment device 4. With the cooperation of the two cranes 1 and the length adjustment device 4, the six-degree-of-freedom attitude adjustment of the rocket engine 5 is realized; wherein the outer envelope of the combined holding ring 7 and the contoured holding hoop 6 are both smaller than the outer envelope of the frame 10, ensuring that when a single engine in a multi-engine single-unit parallel structure is docked, it does not interfere with the adjacent single engine that has been docked, and the docking of the rocket engine and the rocket is realized in cooperation with the six-degree-of-freedom attitude adjustment.

[0013] The combined holding ring 7 is composed of a clamp assembly bolt 11, a clamp assembly 12, a holding ring limit nut 13, a hanging shaft 14, a semi-ring A15, a semi-ring butt bolt 16, a semi-ring B17, and a hanging ring 18; the semi-ring A15 and the semi-ring B17 are connected and fixed by the semi-ring butt bolt 16 to form an integral combined holding ring 7; the clamp assembly 12 is fixed to the semi-ring A15 and the semi-ring B17 according to the distribution of the frame 10 by the clamp assembly bolt 11, so as to fix the frame 10; the hanging shaft 14 fixes the semi-ring A15 by welding and half ring B17, distributed at 180°, and used to connect the length adjustment device 4 to flip the rocket engine 5; the holding ring limit nut 13 is installed on the hanging shaft 14 in the form of a thread, and its function is to limit the length adjustment device 4 after the hanging shaft 14 is connected to prevent the length adjustment device 4 from falling out; the lifting ring 18 is installed on the half ring A15 and the half ring B17 in the form of a thread, wherein six mounting holes of the lifting ring 18 are evenly distributed on the half ring A15 and the half ring B17, so as to realize the horizontal lifting and docking of the rocket engine 5 at an angle of 60° along the axis.

[0014] The clamp assembly 12 is composed of a clamp shaft 19, an arc-shaped pressure block 20, a pressure block fastening device 21, a pressure block fastening nut 22, a fastening device shaft 23, a clamp bracket 24, and a clamp base 25; the clamp base 25 is fixed to the half ring A15 or the half ring B17 by the clamp assembly bolt 11, and is used to fix the entire clamp assembly 12; the clamp bracket 24 is fixedly connected to the clamp base 25; the arc-shaped pressure block 20 is connected to the clamp bracket 24 through the clamp shaft 19, and the arc-shaped pressure block 20 can rotate around the clamp shaft 19 relative to the clamp bracket 24; the pressure block fastening device 21 is fixed to the clamp bracket 24 through the fastening device The rotating shaft 23 is connected to the clamp bracket 24, and at the same time, the pressure block fastening device 21 can rotate around the fastening device rotating shaft 23 relative to the clamp bracket 24; the pressure block fastening nut 22 is installed on the pressure block fastening device 21 in the form of a thread, and can be adjusted and moved along the axial direction of the pressure block fastening device 21; when the arc pressure block 20 rotates along the clamp rotating shaft 19 to hug the frame 10, the pressure block fastening device 21 rotates around the fastening device rotating shaft 23, enters the arc pressure block 20 from the side opening of the arc pressure block 20 to match the arc pressure block 20, and then adjusts the pressure block fastening nut 22 to lock the arc pressure block 20 and the clamp bracket 24.

[0015] The contoured clamp 6 is composed of a clamp locking shaft 26, a clamp locking nut 27, a clamp locking device 28, an end journal 29, a clamp limiting nut 30, a half clamp A31, a clamp shaft 32 and a half clamp B33; the half clamp A31 and the half clamp B33 are connected by the clamp shaft 32, and the half clamp A31 and the half clamp B can rotate around the clamp shaft 32; the clamp locking device 28 is connected to the half clamp B33 by the clamp locking shaft 26, and the clamp locking device 28 can rotate around the clamp locking shaft 26; the clamp locking nut 27 is installed on the clamp locking device 28 in the form of a thread, and can be adjusted and moved along the axial direction of the clamp locking device 28; the end journal 29 is fixed to the half clamp A31 and On the half hoop B, it is distributed at 180° and is used to connect the length adjustment device 4 to flip and horizontally lift and dock the rocket engine 5; the hoop limiting nut 30 is installed on the end shaft neck 29 in the form of a thread, and its function is to limit the length adjustment device 4 and the end shaft neck 29 after being connected to prevent the length adjustment device 4 from falling out; the inner side of the half hoop A31 and the half hoop B matches the shape of the nozzle 8 to clamp the nozzle 8; when the half hoop A31 and the half hoop B rotate around the hoop rotating shaft 32 to clamp the nozzle 8, the hoop locking device 28 rotates around the hoop locking rotating shaft 26, and after matching with the structure on the half hoop A31, the pressure block hoop limiting nut 30 is adjusted to achieve the half hoop A31 and the half hoop B locking the nozzle 8.

[0016] The docking method of the utility model comprises the following steps:

[0017] First, the docking device is assembled, and the crane 1, the inclined steel cable 2, the crossbeam 3 and the length adjustment device 4 are assembled;

[0018] Then, the combined holding ring 7 and the contour holding hoop 6 are fixed on the rocket engine 5; the rocket engine 5 is initially in a vertical state, with the nozzle 8 and the contour holding hoop 6 at the bottom, and the frame 10 and the combined holding ring 7 at the top. One set of the length adjustment devices 4 is connected to the suspension shaft 14 on the combined holding ring 7. After the connection is completed, the length adjustment device 4 is limited by the holding ring limiting nut 13, and then the crane 1 vertically lifts the rocket engine 5. When the nozzle 8 is about 1m from the ground, another set of the length adjustment devices 4 is connected to the end shaft neck 29 on the contour holding hoop 6. After the connection is completed, the hoop limiting nut 30 is used to limit the position; after the state is confirmed, the crane 1 rises at the contour holding hoop 6 connected to the nozzle 8. , the crane 1 at the combined holding ring 7 connected to the frame 10 is lowered until the rocket engine 5 is turned over to a horizontal state, and then parked on the front turnover bracket 34 and the rear turnover bracket 35; in order to reduce the overall envelope of the rocket engine 5 when docking and realize the docking of the rocket engine 5 in a narrow space, the length adjustment device 4 connected to the hanging shaft 14 on the combined holding ring 7 is decomposed and connected to the hanging ring 18 on the combined holding ring 7, and the two places are symmetrical; after the connection, the two cranes 1 synchronously lift the rocket engine 5, and through the cooperation of the two cranes 1 and the adjustment of the four length adjustment devices 4, the six degrees of freedom of the rocket engine 5 can be adjusted, and then the docking of the rocket engine 5 with the rocket is realized.

[0019] The beneficial effects of the utility model are:

[0020] The utility model makes full use of the only two load-bearing points on the engine to design a combined holding ring and a contoured holding hoop structure, thereby simplifying the structure of the device and making the envelope of the multi-engine single-unit parallel structure docking device smaller than the body envelope of the single engine, thereby realizing the docking of a single engine of the multi-engine single-unit parallel structure in a narrow space under complex working conditions, solving the interference problem during the docking process of each engine in the multi-engine single-unit parallel structure, and eliminating safety risks at the same time, thereby improving the reliability and working efficiency of the docking of the multi-engine single-unit parallel structure in a narrow space under complex working conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is the overall structural diagram of the docking device of the utility model.

[0022] Figure 2 It is a schematic diagram of the structure of a rocket engine of the utility model.

[0023] Figure 3 This is a schematic diagram of the combined ring structure of the utility model.

[0024] Figure 4It is a schematic diagram of the structure of the clamp assembly of the utility model.

[0025] Figure 5 It is a schematic diagram of the contoured clamp structure of the utility model.

[0026] Figure 6 It is a flow chart of the docking method of the utility model.

[0027] Figure 7 It is a schematic diagram of the docking turnover solution of the utility model.

[0028] Figure 8 It is a schematic diagram of the parallel structure of multiple engines of a small envelope rocket of the utility model. DETAILED DESCRIPTION

[0029] The utility model is further described below in conjunction with the accompanying drawings and embodiments.

[0030] like Figure 1-Figure 6 shown.

[0031] A docking device based on a multi-engine single-unit parallel structure of a hoisting small envelope rocket, the overall structure diagram is as follows Figure 1 As shown: it is composed of a crane 1, an inclined steel cable 2, a crossbeam 3, a length adjustment device 4, a rocket engine 5, a contoured clamp 6 and a combined clamp ring 7. The structure of the rocket engine 5 is shown in Figure 2 As shown: It is composed of a nozzle 8, an engine body 9 and a frame 10. The nozzle 8 and the frame 10 are connected and fixed through the engine body 9. The combined holding ring 7 is fixed on the frame 10, and the contour holding hoop 6 is fixed on the nozzle 8; the crane 1 is connected to the crossbeam 3 through the inclined steel cable 2, and each crossbeam 3 is respectively connected to the contour holding hoop 6 and the upper structure of the combined holding ring 7 through two length adjustment devices 4. The two cranes 1 can realize the movement of the rocket engine 5 in three degrees of freedom, as well as the pitch and left and right swing. By adjusting the length of the length adjustment device 4, the rocket engine 5 can be rotated along the axis. With the cooperation of the two cranes 1 and the length adjustment device 4, the rocket engine 5 can be adjusted in six degrees of freedom. The outer envelope of the combined holding ring 7 and the contour holding hoop 6 are both smaller than the outer envelope of the frame 10, ensuring that when a single engine of a multi-engine parallel structure is docked, it does not interfere with the adjacent engine that has been docked, and the six-degree-of-freedom attitude adjustment is coordinated to achieve the docking of the rocket engine and the rocket. Specifically, the combined holding ring structure of the utility model is shown in the figure below Figure 3As shown, it consists of a clamp assembly bolt 11, a clamp assembly 12, a ring limit nut 13, a hanging shaft 14, a half ring A15, a half ring docking bolt 16, a half ring B17, and a hanging ring 18. The semi-ring A15 and the semi-ring B17 are connected and fixed by the semi-ring docking bolts 16 to form an integral combined holding ring 7; the clamp assembly 12 is fixed on the semi-ring A15 and the semi-ring B17 according to the distribution of the frame 10 using the clamp assembly bolts 11, which is used to fix the frame 10; the suspension shaft 14 is fixed on the semi-ring A15 and the semi-ring B17 by welding, and is distributed at 180°, and is used to connect the length adjustment device 4 to flip the rocket engine 5; the holding ring limit nut 13 is installed on the suspension shaft 14 in the form of a thread, and its function is to limit the length adjustment device 4 after the connection with the suspension shaft 14, to prevent the length adjustment device 4 from falling out; the lifting ring 18 is installed on the semi-ring A15 and the semi-ring B17 in the form of a thread, wherein the semi-ring A15 and the semi-ring B17 have 6 mounting holes of the lifting ring 18 evenly distributed on the semi-ring A15 and the semi-ring B17, which can realize the horizontal lifting and docking of the rocket engine 5 at an angle of 60° along the axis. The structural diagram of the clamp assembly is shown in the figure below. Figure 4 As shown, it is composed of a clamp shaft 19, an arc-shaped pressure block 20, a pressure block fastening device 21, a pressure block fastening nut 22, a fastening device shaft 23, a clamp bracket 24, and a clamp base 25. The clamp base 25 is fixed to the half ring A15 or half ring B17 by the clamp assembly bolt 11, and is used to fix the entire clamp assembly 12; the clamp bracket 24 is fixedly connected to the clamp base 25; the arc-shaped pressure block 20 is connected to the clamp bracket 24 through the clamp shaft 19, and the arc-shaped pressure block 20 can rotate around the clamp shaft 19 relative to the clamp bracket 24; the pressure block fastening device 21 is connected to the clamp bracket 24 through the fastening device shaft 23, and at the same time, the pressure block fastening device 21 can be fastened around the clamp shaft 19. The fixing device shaft 23 rotates relative to the clamp bracket 24; the pressure block fastening nut 22 is installed on the pressure block fastening device 21 in the form of a thread, and can be adjusted and moved along the axis direction of the pressure block fastening device 21; when the arc-shaped pressure block 20 rotates along the clamp shaft 19 to hold the frame 10, the pressure block fastening device 21 rotates around the fastening device shaft 23, and after matching the structure on the arc-shaped pressure block 20, the pressure block fastening nut 22 is adjusted to lock the arc-shaped pressure block 20 and the clamp bracket 24. The schematic diagram of the contoured clamp structure of the utility model is shown in FIG. Figure 5As shown: it is composed of a clamp locking shaft 26, a clamp locking nut 27, a clamp locking device 28, an end journal 29, a clamp limiting nut 30, a half clamp A31, a clamp shaft 32, and a half clamp B33. The half clamp A31 and the half clamp B are connected by the clamp shaft 32, and the half clamp A31 and the half clamp B can rotate around the clamp shaft 32; the clamp locking device 28 is connected to the half clamp B33 through the clamp locking shaft 26, and the clamp locking device 28 can rotate around the clamp locking shaft 26; the clamp locking nut 27 is installed on the clamp locking device 28 in the form of a thread, and can be adjusted and moved along the axis direction of the clamp locking device 28; the end journal 29 is fixed on the half clamp A31 and the half clamp B by welding, and is distributed at 180 degrees, and is used to connect the length adjustment device 4 to flip and water the rocket engine 5. Horizontal lifting and docking; the clamp limit nut 30 is installed on the end shaft neck 29 in the form of a thread, and its function is to limit the length adjustment device 4 after it is connected to the end shaft neck 29 to prevent the length adjustment device 4 from falling out; the inner side of the half clamp A31 and the half clamp B matches the shape of the nozzle 8 to clamp the nozzle 8; when the half clamp A31 and the half clamp B rotate around the clamp rotating shaft 32 to clamp the nozzle 8, the clamp locking device 28 rotates around the clamp locking rotating shaft 26, and after matching with the structure on the half clamp A31, adjust the pressure block clamp limit nut 30 to achieve the half clamp A31 and the half clamp B locking the nozzle 8.

[0032] A method for docking a multi-engine single-unit parallel structure based on a hoisting small envelope rocket, the working process is as follows Figure 6 As shown, it includes the following steps:

[0033] Firstly, a docking device based on a hoisting-type small envelope rocket multi-engine single-unit parallel structure is assembled, and a crane 1, an inclined steel cable 2, a crossbeam 3 and a length adjustment device 4 are assembled;

[0034] Then, the combined holding ring 7 and the contour holding hoop 6 are fixed on the rocket engine 5; the rocket engine 5 is initially in a vertical state, with the nozzle 8 and the contour holding hoop 6 at the bottom, and the frame 10 and the combined holding ring 7 at the top. One set of the length adjustment devices 4 is connected to the suspension shaft 14 on the combined holding ring 7. After the connection is completed, the length adjustment device 4 is limited by the holding ring limiting nut 13, and then the crane 1 vertically lifts the rocket engine 5. When the nozzle 8 is about 1m from the ground, another set of the length adjustment devices 4 is connected to the end shaft neck 29 on the contour holding hoop 6. After the connection is completed, the hoop limiting nut 30 is used to limit the position. After the state is confirmed, the crane 1 rises at the contour holding hoop 6 connected to the nozzle 8. The crane 1 at the combined holding ring 7 connected to the frame 10 is lowered until the rocket engine 5 is turned over to a horizontal state, and then parked on the front turnover bracket 34 and the rear turnover bracket 35; in order to reduce the overall envelope of the rocket engine 5 when docking and realize the docking of the rocket engine 5 in a narrow space, the length adjustment device 4 connected to the hanging shaft 14 on the combined holding ring 7 is decomposed and connected to the hanging ring 18 on the combined holding ring 7, and the two places are symmetrical; after the connection, the two cranes 1 synchronously lift the rocket engine 5, and through the cooperation of the two cranes 1 and the adjustment of the four length adjustment devices 4, the six degrees of freedom of the rocket engine 5 can be adjusted, and then the docking of the rocket engine 5 with the rocket is realized, such as Figure 7 shown.

[0035] The parts not involved in the present invention are the same as the prior art or can be implemented by using the prior art.

Claims

1. A docking device based on a multi-engine single-unit parallel structure of a hoisting small envelope rocket, characterized in that: The invention comprises a crane (1), an inclined steel cable (2), a crossbeam (3), a length adjustment device (4), a contour clamp (6) and a combined clamp ring (7); the rocket engine (5) comprises a nozzle (8), an engine body (9) and a frame (10); the nozzle (8) and the frame (10) are connected and fixed via the engine body (9); the combined clamp ring (7) is fixed on the frame (10), and the contour clamp (6) is fixed on the nozzle (8); the crane (1) is connected to the crossbeam (3) via the inclined steel cable (2), and each crossbeam (3) is connected to the contour clamp (6) and the structure on the combined clamp ring (7) via two length adjustment devices (4). connection; the three-degree-of-freedom movement, pitch and left-right swing of the rocket engine (5) are achieved by two cranes (1); the rotation of the rocket engine (5) along the axis is achieved by adjusting the length of the length adjustment device (4); and the six-degree-of-freedom attitude adjustment of the rocket engine (5) is achieved with the cooperation of the two cranes (1) and the length adjustment device (4); wherein the outer envelopes of the combined holding ring (7) and the contoured holding hoop (6) are both smaller than the outer envelope of the frame (10), ensuring that when a single engine in a multi-engine parallel structure is docked, no interference occurs with an adjacent engine that has been docked, and the docking of the rocket engine and the rocket is achieved with the six-degree-of-freedom attitude adjustment.

2. The docking device according to claim 1, characterized in that: The combined holding ring (7) is composed of a clamp assembly bolt (11), a clamp assembly (12), a holding ring limit nut (13), a suspension shaft (14), a half ring A (15), a half ring butt bolt (16), a half ring B (17), and a suspension ring (18); the half ring A (15) and the half ring B (17) are connected and fixed by the half ring butt bolt (16) to form an overall combined holding ring (7); the clamp assembly (12) is fixed to the half ring A (15) and the half ring B (17) according to the distribution of the frame (10) by using the clamp assembly bolt (11) to fix the frame (10); the suspension shaft (14) is fixed to the half ring A (15) and the half ring B (17) by welding. The ring A (15) and the half ring B (17) are distributed at 180 degrees and are used to connect the length adjustment device (4) to flip the rocket engine (5); the ring limit nut (13) is installed on the suspension shaft (14) in the form of a thread, and its function is to limit the length adjustment device (4) after the suspension shaft (14) is connected to prevent the length adjustment device (4) from falling out; the lifting ring (18) is installed on the half ring A (15) and the half ring B (17) in the form of a thread, wherein six mounting holes of the lifting ring (18) are evenly distributed on the half ring A (15) and the half ring B (17), so as to realize the horizontal lifting and docking of the rocket engine (5) at an angle of 60 degrees along the axis.

3. The docking device according to claim 2, characterized in that: The clamp assembly (12) comprises a clamp rotating shaft (19), an arc-shaped pressure block (20), a pressure block fastening device (21), a pressure block fastening nut (22), a fastening device rotating shaft (23), a clamp bracket (24), and a clamp base (25); the clamp base (25) is fixed to the half ring A (15) or the half ring B (17) using a clamp assembly bolt (11) and is used to fix the entire clamp assembly (12); the clamp bracket (24) is fixedly connected to the clamp base (25); the arc-shaped pressure block (20) is connected to the clamp bracket (24) via the clamp rotating shaft (19), and the arc-shaped pressure block (20) can rotate around the clamp rotating shaft (19) relative to the clamp bracket (24); the pressure block fastening device (21) is connected to the clamp rotating shaft (19) via the clamp rotating shaft (19). The clamp bracket (24) is connected to the clamp bracket (24) through the fastening device rotation shaft (23), and the pressure block fastening device (21) can rotate around the fastening device rotation shaft (23) relative to the clamp bracket (24); the pressure block fastening nut (22) is installed on the pressure block fastening device (21) in the form of a thread, and can be adjusted and moved along the axis direction of the pressure block fastening device (21); when the arc-shaped pressure block (20) rotates along the clamp bracket rotation shaft (19) to hold the frame (10), the pressure block fastening device (21) rotates around the fastening device rotation shaft (23), enters the arc-shaped pressure block (20) from the side opening of the arc-shaped pressure block (20), and after matching, the pressure block fastening nut (22) is adjusted to lock the arc-shaped pressure block (20) and the clamp bracket (24).

4. The docking device according to claim 1, characterized in that: The contoured clamp (6) comprises a clamp locking shaft (26), a clamp locking nut (27), a clamp locking device (28), an end journal (29), a clamp limiting nut (30), a half clamp A (31), a clamp shaft (32) and a half clamp B (33); the half clamp A (31) and the half clamp B (33) are connected via the clamp shaft (32), and the half clamp A (31) and the half clamp B can rotate around the clamp shaft (32). ) for rotation; the hoop locking device (28) is connected to the half hoop B (33) via the hoop locking shaft (26), and the hoop locking device (28) can rotate around the hoop locking shaft (26); the hoop locking nut (27) is installed on the hoop locking device (28) in the form of a thread, and can be adjusted and moved along the axis direction of the hoop locking device (28); the end journal (29) is fixed to the half hoop A by welding. (31) and the half hoop B are distributed at 180 degrees and are used to connect the length adjustment device (4) to flip and horizontally lift the rocket engine (5) for docking; the hoop limiting nut (30) is installed on the end shaft neck (29) in the form of a thread, and its function is to limit the length adjustment device (4) after being connected to the end shaft neck (29) to prevent the length adjustment device (4) from falling out; the inner sides of the half hoop A (31) and the half hoop B match the outer shape of the nozzle (8) to achieve the clamping of the nozzle (8); when the half hoop A (31) and the half hoop B rotate around the hoop rotating shaft (32) to clamp the nozzle (8), the hoop locking device (28) rotates around the hoop locking rotating shaft (26) to match the structure on the half hoop A (31), and then the pressure block hoop limiting nut (30) is adjusted to achieve the half hoop A (31) and the half hoop B to lock the nozzle (8).

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