An assembly device for modular rockets

Abstract

The present application relates to an assembly device for modular rockets, and to the field of rocket assembly technology. The assembly device includes a first longitudinal bracket and a second longitudinal bracket whose length is at least greater than the sum of the lengths of the combustion chamber of the rear basic module rocket engine and at least two standard module rocket engine combustion chambers. The movable frame includes a movable frame and a base frame arranged between the first longitudinal bracket and the second longitudinal bracket. Both sides of the base frame extend outward by at least a preset length to form an assembly area and a disassembly area. The movable frame is arranged on the base frame and is used to drive the standard module rocket engine combustion chamber to slide between the assembly area and the disassembly area to adjust the coaxiality of the standard module rocket engine combustion chamber with the front basic module rocket engine combustion chamber and the rear basic module rocket engine combustion chamber. The assembly device provided by the present application better solves the problem that solid rocket engines are difficult to disassemble and reassemble into solid rocket engines of other modes after assembly.

Description

Technical Field

[0001] The present application relates to the technical field of rocket assembly, and in particular to an assembly device for modular rockets. Background Art

[0002] Solid rocket engines have the advantages of large charge, simple structure, maneuverability, high reliability and strong survivability. They are currently the main power unit for large solid launch vehicles. Since the total propellant weight of large solid rocket engines often weighs 100 tons or more, the entire propellant cannot be poured at one time during manufacturing due to propellant production safety requirements and casting equipment capacity limitations. In addition, after the overall pouring of the propellant is completed, if there are quality problems and it is scrapped, it will result in excessive costs.

[0003] In response to the above problems, a segmented solid rocket engine is designed in the related art. In the field of rockets, the segmented solid rocket engine divides the combustion chamber into several sections, each of which has an independent shell, insulation structure and propellant column. The sections are connected by a sealing structure, and finally a complete combustion chamber is formed by assembling multiple sections, so as to achieve the design purpose of a combustion chamber with a large aspect ratio and a large charge within a limited diameter. There are many modes of solid rocket engines, and different modes of solid rocket engines are formed by assembling different segments. However, the current segmented solid rocket engine cannot be disassembled and reassembled into other modes of solid rocket engines after the multi-segment assembly is completed. Due to its huge size and heavy weight, it is also very time-consuming and labor-intensive to assemble. Summary of the invention

[0004] An embodiment of the present application provides an assembly device for modular rockets to solve the problem in the related art that segmented solid rocket engines are difficult to disassemble and reassemble into solid rocket engines of other modes after assembly.

[0005] In a first aspect, there is provided an assembly device for a modular rocket, comprising:

[0006] The main frame body includes a first longitudinal bracket and a second longitudinal bracket which are detachably connected in sequence, wherein the length of the second longitudinal bracket is at least greater than the sum of the lengths of the combustion chamber of the rear basic module rocket engine and the combustion chambers of at least two standard module rocket engines;

[0007] At least one movable frame, the movable frame comprising:

[0008] - a bottom frame, which is arranged between the first longitudinal support and the second longitudinal support, and both sides of which extend outwards by at least a preset length to form an assembly area and a disassembly area respectively located on both sides;

[0009] - A movable frame, which is arranged on the base frame, and is used to drive the standard modular rocket engine combustion chamber to slide between the assembly area and the disassembly area to adjust the coaxiality of the standard modular rocket engine combustion chamber with the front basic module rocket engine combustion chamber and the rear basic module rocket engine combustion chamber respectively located on the first longitudinal bracket and the second longitudinal bracket.

[0010] In some embodiments, the base frame includes two cross beams spaced apart along the width direction of the main frame body and a plurality of connecting beams spaced apart between the two cross beams, each of the cross beams extends at least the preset length toward both ends to form the assembly area and the disassembly area with the connecting beams, a slide rail is provided on the top surface of each cross beam, and support members that can be adjusted in the vertical direction are spaced apart on the bottom surface, and each of the two ends of the slide rail is provided with a limit member that can move along the slide rail.

[0011] In some embodiments, the movable frame includes two assembly channels arranged side by side along the width direction of the main frame body, and the width dimension and the preset length dimension of each assembly channel are consistent with the width dimension of the first longitudinal bracket and the second longitudinal bracket.

[0012] In some embodiments, a plurality of support frames are further included, wherein the plurality of support frames are slidably mounted on the first longitudinal support frame and the second longitudinal support frame respectively, and each of the assembly channels is provided with at least two support frames arranged at intervals, and the plurality of support frames are used to jointly support the rocket, and each of the support frames includes:

[0013] A horizontal bracket and a vertical bracket are arranged from bottom to top, wherein the bottom surface of the horizontal bracket is provided with a slider, and the top surface is provided with a first connecting plate, both sides of the first connecting plate are provided with waist-shaped connecting holes, and the bottom surface of the vertical bracket is provided with a second connecting plate, and both sides of the second connecting plate are provided with connecting circular holes corresponding to the waist-shaped connecting holes, and the horizontal position of the vertical bracket is adjusted by adjusting the position of the connecting circular hole relative to the waist-shaped connecting hole.

[0014] In some embodiments, a limit bracket is also provided on the top of the vertical bracket, the bottom surface of the limit bracket is connected to the vertical bracket, and at least two adjustment plates are provided between the limit bracket and the vertical bracket. The vertical position of the limit bracket is adjusted by adjusting the number of the adjustment plates, and the top surface of the limit bracket is a concave arc shape.

[0015] In some embodiments, two groups of alignment components are symmetrically arranged at one end of the first longitudinal bracket away from the movable frame, and each of the limit brackets is symmetrically provided with alignment holes. The alignment components are used to emit alignment light to adjust the position of the corresponding limit bracket according to the situation of the alignment light passing through the corresponding alignment hole.

[0016] In some embodiments, an assembly vehicle is further included, wherein the assembly vehicle includes:

[0017] A movable seat, which is slidably mounted on the second longitudinal bracket, a fixed bracket is arranged on the movable seat, and the movable seat can adjust the position of the fixed bracket in the vertical and horizontal directions respectively, the top surface of the fixed bracket is in a concave arc shape, and fixing pieces are symmetrically arranged on both sides of the top, and the fixing pieces on both sides are used to connect the movable seat with the combustion chamber of the rear basic module rocket engine;

[0018] A multi-stage oil cylinder is arranged on the second longitudinal support and one end of the multi-stage oil cylinder is connected to the movable seat.

[0019] In some embodiments, each of the fixing parts includes a fixing ear and a fixing pin rotatably inserted into the fixing ear, and the fixing pin is connected to the corresponding fixing hole on the combustion chamber of the rear basic module rocket engine by adjusting the length of the fixing pin extending out of the fixing ear.

[0020] In some embodiments, both ends of the first longitudinal bracket, the second longitudinal bracket and the base frame are provided with docking sections, and the docking sections include a transition chassis and a transition bracket arranged from bottom to top, and both ends of each side of the transition chassis are provided with a triangular connecting piece, and the top of the transition bracket is provided with a transition track.

[0021] In some embodiments, the length of the second longitudinal support ranges from 2.5 to 4 m.

[0022] The beneficial effects of the technical solution provided by this application include:

[0023] The embodiment of the present application provides an assembly device for modular rockets, which is provided by setting a first longitudinal bracket and a second longitudinal bracket, and at least one movable frame body including a base frame and a movable frame is provided between the first longitudinal bracket and the second longitudinal bracket, so that both sides of the base frame extend outward at least a preset length to form an assembly area and a disassembly area respectively located on both sides, and the movable frame is used to drive the combustion chamber of the standard module rocket engine to slide between the assembly area and the disassembly area to adjust the coaxiality of the combustion chamber of the standard module rocket engine with the front basic module rocket engine combustion chamber and the rear basic module rocket engine combustion chamber respectively located on the first longitudinal bracket and the second longitudinal bracket. The present assembly device can well assist the assembly and disassembly of the segmented solid rocket engine to achieve the purpose of changing the solid rocket engine between different modes, making it possible to quickly change between different modes, and greatly reducing the difficulty of installation, disassembly and change. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0025] Figure 1 A schematic diagram of the structure of an assembly device for a modular rocket provided in an embodiment of the present application;

[0026] Figure 2 A schematic structural diagram of a movable frame of an assembly device for modular rockets provided in an embodiment of the present application;

[0027] Figure 3 A top view of a movable frame of an assembly device for modular rockets provided in an embodiment of the present application;

[0028] Figure 4 A schematic diagram of the structure of an assembly vehicle for an assembly device for modular rockets provided in an embodiment of the present application;

[0029] Figure 5 A schematic structural diagram of the docking section of an assembly device for a modular rocket provided in an embodiment of the present application.

[0030] In the figure: 1-main frame, 10-first longitudinal bracket, 11-second longitudinal bracket, 2-movable frame, 20-base frame, 200-assembly area, 201-disassembly area, 202-cross beam, 203-slide rail, 204-connecting beam, 21-movable frame, 210-assembly channel, 3-support frame, 30-horizontal bracket, 31-vertical bracket, 32-slider, 33-first connecting plate, 34-second connecting plate, 35-limiting bracket, 36-adjusting sheet, 37-alignment hole, 4-assembly trolley, 40-movable seat, 41-fixed bracket, 42-fixing piece, 43-multi-stage cylinder, 44-fixing ear, 45-fixing pin, 5-docking section, 50-transition chassis, 51-transition bracket, 52-connecting piece, 53-transition track. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0032] An embodiment of the present application provides an assembly device for modular rockets, which can solve the problem in the related art that segmented solid rocket engines are difficult to disassemble and reassemble into solid rocket engines of other modes after assembly.

[0033] See also Figure 1 As shown, the assembly device includes a main frame 1 and at least one movable frame 2, wherein the main frame 1 includes a first longitudinal bracket 10 and a second longitudinal bracket 11 that are detachably connected in sequence, the length of the second longitudinal bracket 11 is at least greater than the sum of the lengths of the rear basic module rocket engine combustion chamber and at least two standard module rocket engine combustion chambers, and the movable frame 2 specifically includes a base frame 20 and a movable frame 21, the base frame 20 is arranged between the first longitudinal bracket 10 and the second longitudinal bracket 11, and both sides extend outward by at least a preset length to form an assembly area 200 and a disassembly area 201 respectively located on both sides, and the movable frame 21 is arranged on the base frame 20, and the movable frame 21 is used to drive the standard module rocket engine combustion chamber to slide between the assembly area 200 and the disassembly area 201 to adjust the coaxiality of the standard module rocket engine combustion chamber with the front basic module rocket engine combustion chamber and the rear basic module rocket engine combustion chamber respectively located on the first longitudinal bracket 10 and the second longitudinal bracket 11. Specifically, the movable frame 2 is a relatively flexible unit, which is mainly used to slide between the assembly area 200 and the disassembly area 201 through the movable frame 21 to realize the addition or removal of the standard module rocket engine combustion chamber between the front basic module rocket engine combustion chamber and the rear basic module rocket engine combustion chamber, so as to realize the switching between different modes of different solid rocket engines. Generally, solid rocket engines have three commonly used modes. The first mode consists of a front basic module rocket engine combustion chamber and a rear basic module rocket engine combustion chamber, the second mode consists of a front basic module rocket engine combustion chamber, a standard module rocket engine combustion chamber and a rear basic module rocket engine combustion chamber, and the third mode consists of a front basic module rocket engine combustion chamber, two or more standard module rocket engine combustion chambers and a rear basic module rocket engine combustion chamber. In addition, the length dimension of the second longitudinal bracket 11 ranges from 2.5 to 4m, generally 3m, and specifically includes two sections of standard module stop positions and one section of rear basic module stop position.

[0034] For further information, see Figure 2 and Figure 3As shown, the base frame 20 specifically includes two cross beams 202 spaced apart along the width direction of the main frame body 1 and a plurality of connecting beams 204 spaced apart between the two cross beams 202, each cross beam 202 extends at least to a preset length at both ends to form an assembly area 200 and a disassembly area 201 with the connecting beams 204, a slide rail 203 is provided on the top surface of each cross beam 202, and support members 204 that can be adjusted in the vertical direction are spaced apart on the bottom surface, and limit members that can move along the slide rail 203 are provided at both ends of each slide rail 203. Specifically, the support member 204 is used to fix the base frame 20 on the foundation located below. The base frame 20 is mainly divided into three parts, two of which are the assembly area 200 and the disassembly area 201 located on both sides, and the remaining part is the receiving area located between the assembly area 200 and the disassembly area 201. The receiving area is mainly used to receive the solid rocket engine after the installation is completed. Therefore, the size of the base frame 20 along the width direction of the main frame body 1 is at least three times the width of the solid rocket engine. The role of the limit member is to assist the movable frame 21 in accurately positioning on the base frame 20.

[0035] Furthermore, the movable frame 21 includes two assembly channels 210 arranged side by side along the width direction of the main frame body 1, and the width dimension and the preset length dimension of each assembly channel 210 are consistent with the width dimension of the first longitudinal bracket 10 and the second longitudinal bracket 11. Specifically, the two assembly channels 210 on the movable frame 21 are mainly used for accommodating and placing the combustion chamber of the standard modular rocket engine during installation and disassembly.

[0036] Furthermore, since the overall shape of the solid rocket engine is cylindrical, in order to better ensure stability, the assembly device also includes a plurality of support frames 3, and the plurality of support frames 3 are respectively slidably disposed on the first longitudinal bracket 10 and the second longitudinal bracket 11, and each assembly channel 210 is provided with at least two spaced support frames 3, and the plurality of support frames 3 are used to jointly support the rocket, and each support frame 3 specifically includes a horizontal bracket 30 and a vertical bracket 31 arranged from bottom to top, and the bottom surface of the horizontal bracket 30 is provided with a slider 32, and the top surface is provided with a first connecting plate 33, and waist-shaped connecting holes are provided on both sides of the first connecting plate 33, and the bottom surface of the vertical bracket 31 is provided with a second connecting plate 34, and the two sides of the second connecting plate 34 are provided with connecting circular holes corresponding to the waist-shaped connecting holes, and the horizontal position of the vertical bracket 31 is adjusted by adjusting the position of the connecting circular hole relative to the waist-shaped connecting hole. Specifically, since the whole is composed of multiple segments, the coaxiality between each segment needs to be ensured before splicing. Since the first longitudinal bracket 10, the second longitudinal bracket 11 and the movable frame 2 are all spliced ​​together, there may be errors in the process of superimposed splicing and subsequent positioning of the movable frame 21, resulting in a large overall cumulative error. At this time, it is not very convenient to adjust the first longitudinal bracket 10, the second longitudinal bracket 11 and the movable frame 2. Therefore, the support frame 3 is designed to be an adjustable structure. If there is an error in the horizontal position, the position of the vertical bracket 31 is adjusted so that the connecting circular hole thereon moves relative to the position of the waist-shaped connecting hole on the horizontal bracket 30, and then it can be re-fixed.

[0037] Furthermore, in addition to the need to adjust the horizontal position, the vertical position may also need to be adjusted. Therefore, a limit bracket 35 is also provided on the top of the vertical bracket 31. The bottom surface of the limit bracket 35 is connected to the vertical bracket 31, and at least two adjustment plates 36 are provided between the limit bracket 35 and the vertical bracket 31. The vertical position of the limit bracket 35 is adjusted by adjusting the number of adjustment plates 36. The top surface of the limit bracket 35 is a concave arc shape, which matches the shape of the solid rocket engine.

[0038] Furthermore, in addition to the above-mentioned position in the horizontal direction and the vertical direction can be adjusted again after the assembly is completed, since the overall length is relatively long, if there is no reference mark or detection during the adjustment process, the difficulty of adjustment will be increased. Therefore, the assembly device also includes two sets of alignment components symmetrically arranged at the end of the first longitudinal bracket 10 away from the movable frame 2, and each limit bracket 35 is symmetrically provided with alignment holes 37. The alignment components are used to emit alignment light to adjust the position of the corresponding limit bracket 35 according to the situation that the alignment light passes through the corresponding alignment hole 37. Specifically, when adjusting, it is observed whether the alignment light emitted by the alignment component at one end passes through the alignment holes 37 on the limit bracket 35 in sequence, which is used as the judgment basis for adjustment, thereby reducing the difficulty and time required for the entire adjustment process.

[0039] For further information, see Figure 4 As shown, the assembly device also includes an assembly trolley 4, which specifically includes a movable seat 40 and a multi-stage oil cylinder 43, wherein the movable seat 40 is slidably arranged on the second longitudinal bracket 11, a fixed bracket 41 is arranged on the movable seat 40, and the movable seat 40 can adjust the position of the fixed bracket 41 in the vertical and horizontal directions respectively, the top surface of the fixed bracket 41 is in a concave arc shape, and fixing members 42 are symmetrically arranged on both sides of the top, and the fixing members 42 on both sides are used to connect the movable seat 40 with the rear basic module rocket engine combustion chamber, and the multi-stage oil cylinder 43 is arranged on the second longitudinal bracket 11, and one end is connected to the movable seat 40. Specifically, the structure of the movable seat 40 is similar to that of the support frame 3, and the fixing members 42 arranged on both sides of the fixed bracket 41 are used to pass through the rear basic module rocket engine combustion chamber, so that in the process of installation and disassembly, with the assistance of the support frame 3, the rear basic module rocket engine combustion chamber, or the standard module rocket engine combustion chamber connected to the rear basic module rocket engine combustion chamber and connected thereto, are moved together in a direction close to or away from the front basic module rocket engine combustion chamber.

[0040] Furthermore, each fixing part 42 specifically includes a fixing ear 44 and a fixing pin 45 rotatably inserted into the fixing ear 44. The fixing pin 45 is connected to the corresponding fixing hole on the combustion chamber of the rear basic module rocket engine by adjusting the length of the fixing pin 45 extending out of the fixing ear 44.

[0041] For further information, see Figure 5 As shown, both ends of the first longitudinal bracket 10, the second longitudinal bracket 11 and the base frame 20 are provided with a docking section 5, and the docking section 5 includes a transition chassis 50 and a transition bracket 51 arranged from bottom to top, and both ends of each side of the transition chassis 50 are provided with a triangular connecting piece 52, and the top of the transition bracket 51 is provided with a transition track 53.

[0042] The operating principle of this assembly device is as follows:

[0043] Take the example of a solid rocket engine that needs to change from the first mode to the third mode:

[0044] First, move both movable frames 21 laterally to their respective disassembly areas 201, lift the first standard module rocket engine combustion chamber onto the support frame 3 on the first movable frame 21 close to the first longitudinal bracket 10, and lift the second standard module rocket engine combustion chamber onto the support frame 3 on the second movable frame 21 close to the second longitudinal bracket 11; then lift the solid rocket engine in the first mode onto the support frame 3 of the assembly device, and after completion, connect the fixing parts 42 on the assembly cart 4 located on the second longitudinal bracket 11 to the corresponding fixing holes on the combustion chamber of the rear basic module rocket engine.

[0045] Operate the locking nut on the female joint of the front basic module rocket engine combustion chamber to the unlocking position. At this time, the front basic module rocket engine combustion chamber and the rear basic module rocket engine combustion chamber are successfully unlocked. Then operate the assembly cart 4 located at the tail of the rear basic module rocket engine combustion chamber to move in the direction of the front basic module rocket engine combustion chamber until the rear basic module rocket engine combustion chamber is moved to the rear basic module stop position of the second longitudinal bracket 11, and then move the second movable frame 21 horizontally to its corresponding assembly area 200, so that the second standard module rocket engine combustion chamber is in the accommodation area, that is, on the same axial direction as the solid rocket engine combustion chamber in the first mode.

[0046] Operate the locking nut on the female joint on the second standard module rocket engine combustion chamber to the unlocked position, and operate the assembly cart 4 again to move toward the second standard module rocket engine combustion chamber, so that the sub-joint of the rear basic module rocket engine combustion chamber enters the connecting groove of the locking nut of the female joint of the standard module rocket engine combustion chamber, and operate the locking nut on the female joint of the standard module rocket engine combustion chamber to the locked position. At this time, the second standard module rocket engine combustion chamber is connected as a whole with the rear basic module rocket engine combustion chamber.

[0047] Then move the first movable frame 21 close to the first longitudinal bracket 10 laterally to the assembly area 200, so that the first standard module rocket engine combustion chamber is in the receiving area, on the same axial direction as the solid rocket engine combustion chamber in the first mode, operate the locking nut on the female joint in the first standard module rocket engine combustion chamber to the unlocked position, and operate the assembly cart 4 again to drive the second standard module rocket engine combustion chamber and the rear basic module rocket engine combustion chamber to move toward the direction of the first standard module rocket engine combustion chamber, so that the sub-joint of the second standard module rocket engine combustion chamber enters the female joint locking nut connecting groove of the first standard module rocket engine combustion chamber, and operates the locking nut on the female joint of the first standard module rocket engine combustion chamber to the locking position. At this time, the first standard module rocket engine combustion chamber is connected as a whole with the second standard module rocket engine combustion chamber.

[0048] Operate the assembly trolley 4 to move toward the direction approaching the front basic module rocket engine combustion chamber. Similarly, make the sub-joint of the first standard module rocket engine combustion chamber enter the connecting groove of the locking nut of the female joint of the front basic module rocket engine combustion chamber, operate the locking nut on the female joint of the front basic module rocket engine combustion chamber to the locking position, then the front basic module rocket engine combustion chamber is connected as one with the two standard module rocket engine combustion chambers and the rear basic module rocket engine combustion chamber, that is, assembled into the third mode of solid rocket engine combustion chamber.

[0049] In the description of the present application, it should be noted that the terms "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0050] It should be noted that, in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0051] The above description is only a specific implementation of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features applied for herein.

Claims

1. An assembly device for modular rockets, characterized in that: It includes: A main frame (1) comprising, in sequence, a first longitudinal bracket (10) and a second longitudinal bracket (11) which are detachably connected, wherein the length of the second longitudinal bracket (11) is at least greater than the sum of the lengths of the combustion chamber of the rear basic module rocket engine and the combustion chambers of at least two standard module rocket engines; At least one movable frame (2), the movable frame (2) comprising: - a bottom frame (20), which is arranged between the first longitudinal frame (10) and the second longitudinal frame (11), and has two sides extending outward at least by a preset length to form an assembly area (200) and a disassembly area (201) located on the two sides respectively; - a movable frame (21) disposed on the base frame (20), the movable frame (21) being used to drive the standard modular rocket engine combustion chamber to slide between the assembly area (200) and the disassembly area (201) so as to adjust the coaxiality of the standard modular rocket engine combustion chamber with the front basic module rocket engine combustion chamber and the rear basic module rocket engine combustion chamber respectively located on the first longitudinal bracket (10) and the second longitudinal bracket (11).

2. An assembly device for modular rockets according to claim 1, characterized in that: The base frame (20) comprises two cross beams (202) arranged at intervals along the width direction of the main frame body (1) and a plurality of connecting beams (204) arranged at intervals between the two cross beams (202); each of the cross beams (202) extends at least to the preset length at both ends to form the assembly area (200) and the disassembly area (201) with the connecting beams (204); the top surface of each cross beam (202) is provided with a slide rail (203); the bottom surface is provided with support members that can be adjusted in the vertical direction at intervals; and both ends of each slide rail (203) are provided with limit members that can move along the slide rail (203).

3. An assembly device for modular rockets as claimed in claim 2, characterized in that: The movable frame (21) comprises two assembly channels (210) arranged side by side along the width direction of the main frame body (1), and the width dimension and the preset length dimension of each assembly channel (210) are consistent with the width dimension of the first longitudinal support (10) and the second longitudinal support (11).

4. An assembly device for modular rockets as claimed in claim 3, characterized in that: It also comprises a plurality of support frames (3), wherein the plurality of support frames (3) are respectively slidably mounted on the first longitudinal frame (10) and the second longitudinal frame (11), and each of the assembly channels (210) is provided with at least two support frames (3) arranged at intervals, wherein the plurality of support frames (3) are used to jointly support the rocket, and each of the support frames (3) comprises: A horizontal bracket (30) and a vertical bracket (31) are arranged from bottom to top, wherein the bottom surface of the horizontal bracket (30) is provided with a slider (32), and the top surface is provided with a first connecting plate (33), both sides of the first connecting plate (33) are provided with waist-shaped connecting holes, and the bottom surface of the vertical bracket (31) is provided with a second connecting plate (34), and both sides of the second connecting plate (34) are provided with connecting circular holes corresponding to the waist-shaped connecting holes, and the horizontal position of the vertical bracket (31) is adjusted by adjusting the position of the connecting circular hole relative to the waist-shaped connecting hole.

5. An assembly device for modular rockets as claimed in claim 4, characterized in that: A limiting bracket (35) is also provided on the top of the vertical bracket (31); the bottom surface of the limiting bracket (35) is connected to the vertical bracket (31); and at least two adjusting pieces (36) are provided between the limiting bracket (35) and the vertical bracket (31); the vertical position of the limiting bracket (35) is adjusted by adjusting the number of the adjusting pieces (36); and the top surface of the limiting bracket (35) is in a concave arc shape.

6. An assembly device for modular rockets as claimed in claim 5, characterized in that: It also comprises two groups of alignment components symmetrically arranged at one end of the first longitudinal bracket (10) away from the movable frame (2), and each of the limit brackets (35) is symmetrically provided with an alignment hole (37), and the alignment component is used to emit an alignment light to adjust the position of the corresponding limit bracket (35) according to the situation of the alignment light passing through the corresponding alignment hole (37).

7. An assembly device for modular rockets as claimed in claim 1, characterized in that: It also includes an assembly trolley (4), wherein the assembly trolley (4) includes: A movable seat (40) is slidably mounted on the second longitudinal bracket (11), a fixed bracket (41) is provided on the movable seat (40), and the movable seat (40) can adjust the position of the fixed bracket (41) in the vertical and horizontal directions respectively, the top surface of the fixed bracket (41) is in a concave arc shape, and fixing members (42) are symmetrically arranged on both sides of the top, and the fixing members (42) on both sides are used to connect the movable seat (40) with the combustion chamber of the rear basic module rocket engine; A multi-stage oil cylinder (43) is arranged on the second longitudinal support (11) and one end of which is connected to the movable seat (40).

8. An assembly device for modular rockets as claimed in claim 7, characterized in that: Each of the fixing members (42) comprises a fixing ear (44) and a fixing pin (45) rotatably inserted through the fixing ear (44); the fixing pin (45) is connected to a corresponding fixing hole on the combustion chamber of the rear basic module rocket engine by adjusting the length of the fixing pin (45) extending out of the fixing ear (44).

9. An assembly device for modular rockets as claimed in claim 1, characterized in that: Both ends of the first longitudinal bracket (10), the second longitudinal bracket (11) and the bottom bracket (20) are provided with a docking section (5), the docking section (5) comprising a transition chassis (50) and a transition bracket (51) arranged from bottom to top, both ends of each side of the transition chassis (50) are provided with a triangular connecting piece (52), and the top of the transition bracket (51) is provided with a transition track (53).

10. An assembly device for modular rockets according to claim 1, characterized in that: The length dimension of the second longitudinal support (11) ranges from 2.5 to 4 m.

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