A docking device and method based on a multi-engine single-unit parallel structure of a hoisted small envelope rocket

Abstract

A docking device and method for a multi-engine single-unit parallel structure based on a hoisting-type small-envelope rocket is characterized in that the docking device is composed of a crane (1), an inclined steel cable (2), a crossbeam (3), a length adjustment device (4), a contoured clamp (6) and a combined clamping ring (7); the rocket engine (5) is composed of a nozzle (8), an engine body (9) and a frame (10); the present invention utilizes only two load-bearing points on the engine to design a combined clamping ring and a contoured clamp structure, thereby simplifying the structure and making the envelope of the multi-engine single-unit parallel structure docking device smaller than the envelope of the engine body, thereby realizing the docking of single engines of the multi-engine single-unit parallel structure in a narrow space under complex working conditions, solving the interference problem of each engine in the multi-engine single-unit parallel structure during the docking process, eliminating safety risks, and improving the reliability and working efficiency of the multi-engine single-unit parallel structure docking in a narrow space under complex working conditions.

Description

Technical Field

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

[0002] There are two main methods of parallel docking of multiple engines on 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, the docking method for most types of rocket engines is horizontal docking. When the engine is parked, it is in a vertical state (nozzle downward); for engines with smaller mass, the engine is lifted to a horizontal state through the double hooks of the engine frame and the engine throat to dock with the rocket body; for engines with larger mass, a squirrel cage tooling is generally used to connect with the process hole of the engine frame, and the squirrel cage and engine assembly are flipped to a horizontal state for docking with the rocket body.

[0004] The only example of vertical engine docking is a certain model of core stage. The engine has a dual-engine shared frame structure. Due to the large mass of the engine, the frame deforms greatly during the horizontal docking process, the docking holes are difficult to align, and the installation of the docking bolts is more difficult. Therefore, a vertical docking method is adopted to dock the engine with the rear transition section and tail section in a vertical state, and then the entire assembly is 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 significant differences from existing models in terms of the number of engines, structural form and installation method. The multi-engine parallel structure results in a small engine compartment space, 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 assembly of the multi-engine parallel structure.

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

[0007] Currently, 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. If it is used for docking of multiple engines in parallel, 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 current rockets, the rocket engine's main body 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 lifting 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 multi-engine single-unit parallel structure. Summary of the Invention

[0010] The purpose of the present invention is to address the problem of interference that is prone to occur during the docking process of each engine in a multi-engine single-unit parallel structure, and to invent a docking device and method for a multi-engine single-unit parallel structure based on a hoisting-type small-envelope rocket. The combined holding ring and contoured holding hoop structure are designed by fully utilizing the only two load-bearing points on the engine, 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 interference problem of each engine in the multi-engine single-unit parallel structure during the docking process, and at the same time eliminating safety risks, 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] One of the technical solutions of the present invention is:

[0012] A docking device based on a multi-engine single-unit parallel structure of a hoisting small envelope rocket: characterized in that it consists of a crane 1, an inclined steel cable 2, a crossbeam 3, a length adjustment device 4, a contoured clamp 6 and a combined clamping ring 7; the rocket engine 5 consists 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 clamping ring 7 is fixed on the frame 10, and the contoured 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 contoured clamp 6 and the combined clamping 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 parallel structure is docked, it does not interfere with the adjacent engine that has been docked, and the docking of the rocket engine and the rocket is realized in conjunction 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 half ring A15, a half ring butt bolt 16, a half ring B17, and a hanging ring 18; the half ring A15 and the half ring B17 are connected and fixed by the half ring butt bolt 16 to form an integral combined holding ring 7; the clamp assembly 12 is fixed to the half ring A15 and the half ring B17 according to the distribution of the frame 10 using the clamp assembly bolt 11 to fix the frame 10; the hanging shaft 14 fixes the half ring A15 by welding and half ring B17, distributed at 180°, for connecting 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 6 mounting holes of the lifting ring 18 are evenly distributed on the half ring A15 and the half ring B17, so as to realize 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 using the clamp assembly bolt 11, which 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. 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 rotating shaft 32 and a half clamp B33; the half clamp A31 and the half clamp B33 are connected by the clamp rotating shaft 32, and the half clamp A31 and the half clamp B can rotate around the clamp rotating 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 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 outer shape of the nozzle 8 to achieve the clamping of 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 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 second technical solution of the present invention is:

[0017] A method for docking a multi-engine single-unit parallel structure based on a hoisted small envelope rocket is characterized by comprising the following steps:

[0018] First, assemble the docking device, assemble the crane 1, the inclined steel cable 2, the crossbeam 3 and the length adjustment device 4;

[0019] Then, fix the combined holding ring 7 and the contour holding hoop 6 on the rocket engine 5; the initial state of the rocket engine 5 is vertical, the nozzle 8 and the contour holding hoop 6 are at the bottom, the frame 10 and the combined holding ring 7 are at the top, and one set of the length adjustment devices 4 is connected to the hanging 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 lifts the rocket engine 5 vertically. When the nozzle 8 is about 1m from the ground, connect another set of the length adjustment devices 4 and 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 flipped 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. 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 rocket engine 5 and the rocket are docked.

[0020] The beneficial effects of the present invention are:

[0021] The present invention makes full use of the only two load-bearing points on the engine to design a combined holding ring and contoured holding hoop structure, which simplifies the structure of the device and makes the envelope of the multi-engine single-unit parallel structure docking device smaller than the body envelope of the single engine. It realizes the docking of a single engine in a multi-engine single-unit parallel structure in a narrow space under complex working conditions, solves the interference problem during the docking process of each engine in the multi-engine single-unit parallel structure, eliminates safety risks, and improves the reliability and work 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

[0022] Figure 1 It is the overall structural diagram of the docking device of the present invention.

[0023] Figure 2 It is a schematic structural diagram of a rocket engine of the present invention.

[0024] Figure 3 This is a schematic diagram of the combined ring structure of the present invention

[0025] Figure 4 It is a schematic structural diagram of the clamp assembly of the present invention.

[0026] Figure 5 It is a structural schematic diagram of the profiled clamp of the present invention.

[0027] Figure 6 It is a flow chart of the docking method of the present invention.

[0028] Figure 7 It is a schematic diagram of the docking turnover solution of the present invention.

[0029] Figure 8 It is a schematic diagram of the parallel structure of multiple engines of a small envelope rocket of the present invention. DETAILED DESCRIPTION

[0030] The present invention will be further described below with reference to the accompanying drawings and examples. Example

[0031] like Figures 1-6 shown.

[0032] A docking device based on a multi-engine parallel structure of a hoisted small envelope rocket. The overall structure is shown in the figure Figure 1 As shown: It consists 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 FIG. Figure 2 As shown: It consists 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 in 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 present invention is shown in FIG. 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 to the semi-ring A15 and the semi-ring B17 according to the distribution of the frame 10 using the clamp assembly bolts 11, and is used to fix the frame 10; the hanging shaft 14 is fixed to 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 hanging shaft 14 in the form of a thread, and its function is to limit the length adjustment device 4 after it is connected to the hanging 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 for 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 FIG. Figure 4 As shown, it consists 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 using 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 relative to the clamp bracket 24 around the clamp shaft 19; 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 tightened around 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 present invention is shown in FIG. Figure 5As shown: It consists 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 to 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 outer shape of the nozzle 8 to clamp the nozzle 8; when the half clamp A31 and the half clamp B rotate around the clamp rotation axis 32 to clamp the nozzle 8, the clamp locking device 28 rotates around the clamp locking rotation axis 26, and after matching the structure on the half clamp A31, adjust the pressure block clamp limit nut 30 to achieve half clamp A31 and half clamp B locking the nozzle 8. Example

[0033] like Figure 6-Figure 7 shown.

[0034] A method for docking a multi-engine parallel structure of a small-envelope rocket based on a hoisting type is described as follows: Figure 6 As shown, it includes the following steps:

[0035] First, a docking device based on a hoisting-type small envelope rocket multi-engine single-unit parallel structure is assembled, and the crane 1, inclined steel cable 2, crossbeam 3 and length adjustment device 4 are assembled;

[0036] Then, fix the combined holding ring 7 and the contour holding hoop 6 on the rocket engine 5; the initial state of the rocket engine 5 is vertical, the nozzle 8 and the contour holding hoop 6 are at the bottom, the frame 10 and the combined holding ring 7 are at the top, and one set of the length adjustment devices 4 is connected to the hanging 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 lifts the rocket engine 5 vertically. When the nozzle 8 is about 1m from the ground, connect another set of the length adjustment devices 4 and 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, with the two locations being symmetrical; after the connection is made, 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 rocket engine 5 and the rocket are docked, as shown in FIG. Figure 7 shown.

[0037] The parts not involved in the present invention are the same as the existing technology or can be implemented by using the existing technology.

Claims

1. A docking device based on a multi-engine parallel structure of a hoisted small envelope rocket: characterized in that: The invention comprises a crane (1), an inclined steel cable (2), a crossbeam (3), a length adjusting device (4), a contoured clamp (6) and a combined clamping 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 clamping ring (7) is fixed on the frame (10), and the contoured 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 contoured clamp (6) and the structure on the combined clamping ring (7) via two length adjusting devices (4). The invention relates to a method for connecting a rocket engine (5) to a vehicle. The two cranes (1) are used to realize the movement of the rocket engine (5) in three degrees of freedom and the pitch and left-right swing. The length of the length adjustment device (4) is adjusted to realize the rotation of the rocket engine (5) along the axis. 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. 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, it does not interfere with the adjacent engine that has been docked. The six-degree-of-freedom attitude adjustment is used to realize the docking of the rocket engine and the rocket.

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 hanging shaft (14), a half ring A (15), a half ring butt bolt (16), a half ring B (17), and a hanging 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 integral 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) using the clamp assembly bolt (11) to fix the frame (10); the hanging shaft (14) fixes 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 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 hanging 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 hanging ring (18) are evenly distributed on the half ring A (15) and the half ring B (17), so that the rocket engine (5) can be horizontally hoisted and docked at an angle of 60 degrees along the axis.

3. The docking device according to claim 2, characterized in that: 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 A (15) or the half ring B (17) using a clamp assembly bolt (11) for fixing 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 shaft (19) relative to the clamp bracket (24). The fastening device rotation 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 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 pressure block (20) rotates along the clamp 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 pressure block (20) from the side opening of the arc pressure block (20), and after matching, adjusts the pressure block fastening nut (22) to lock the arc pressure block (20) and the clamp bracket (24).

4. The docking device according to claim 1, characterized in that: 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 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 by the clamp shaft (32), and the half clamp A (31) and the half clamp B can rotate around the clamp shaft (32). ) is rotated; the hoop locking device (28) is connected to the half hoop B (33) through 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 perform the flipping and horizontal lifting docking of 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) 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).

5. A method for docking a multi-engine single-unit parallel structure of a small-envelope rocket based on the docking device of claim 1, characterized in that The following steps are involved: 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; 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 device (4) is connected to the hanging 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). 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 device (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) is connected to the contour holding hoop (6) of the nozzle (8). 1) rises, and the crane (1) at the combined holding ring (7) connected to the frame (10) descends 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 locations are symmetrical; after the connection is completed, 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 rocket engine (5) and the rocket are docked.

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