A positioning device for rocket engine thrust chamber and turbine pump assembly

Abstract

The utility model relates to a positioning device for rocket engine thrust chamber and turbine pump assembly, and the device comprises a main beam, a first support beam and a second support beam, the first support beam and the second support beam are both installed on the main beam, and the first support beam and the second support beam are both located on the same side of the main beam, a first flange plate is installed on the end of the first support beam away from the main beam, a second flange plate is installed on the end of the second support beam away from the main beam, the first flange plate and the second flange plate are respectively used for connecting with the rocket engine thrust chamber and the turbine pump to realize the assembly positioning of the rocket engine thrust chamber and the turbine pump, a first connecting block and a second connecting block are installed on the end of the main beam away from the first support beam, the first connecting block is located on one side of the second connecting block, a first lifting ring is installed on the first connecting block, and a second lifting ring is installed on the second connecting block. The utility model can guarantee the installation precision between the rocket engine thrust chamber and the turbine pump, and can also improve the assembly efficiency.

Description

Technical Field

[0001] This utility model relates to the field of rocket engine technology, and in particular to a positioning device for assembling the thrust chamber and turbopump of a rocket engine. Background Technology

[0002] During the assembly of rocket engines, especially in the assembly of post-pump turbofan rocket engines, the installation accuracy requirements between the rocket engine thrust chamber and the turbopump are extremely strict. If the installation accuracy is not high, defects such as the overall performance of the rocket engine deviating from the design requirements may occur.

[0003] In the existing technology, the rocket engine thrust chamber and turbopump are usually assembled by visual inspection by the operator. This method not only fails to guarantee the installation accuracy between the rocket engine thrust chamber and turbopump, but also has very low assembly efficiency.

[0004] Therefore, there is an urgent need for a positioning device for assembling the rocket engine thrust chamber and turbopump, so as to realize the assembly positioning of the rocket engine thrust chamber and turbopump, thereby improving the assembly efficiency between the rocket engine thrust chamber and turbopump, and also improving the installation accuracy between the rocket engine thrust chamber and turbopump, thus avoiding the defect of the overall performance of the rocket engine deviating from the design requirements. Utility Model Content

[0005] The purpose of this invention is to provide a positioning device for assembling the thrust chamber and turbopump of a rocket engine, so as to solve the problems existing in the prior art.

[0006] To achieve the above objectives, this utility model provides the following solution: This utility model provides a positioning device for assembling a rocket engine thrust chamber and a turbopump, comprising a main beam, a first support beam, and a second support beam, wherein: Both the first support beam and the second support beam are installed on the main beam, and both the first support beam and the second support beam are located on the same side of the main beam; A first flange is installed at the end of the first support beam away from the main beam, and a second flange is installed at the end of the second support beam away from the main beam; The first flange and the second flange are used to connect to the rocket engine thrust chamber and the turbopump, respectively, so as to realize the assembly and positioning of the rocket engine thrust chamber and the turbopump. The main beam is equipped with a first connecting block and a second connecting block at the end away from the first support beam, and the first connecting block is located on one side of the second connecting block. A first lifting ring is installed on the first connecting block, and a second lifting ring is installed on the second connecting block.

[0007] According to one embodiment of the present invention, the first support beam and the second support beam are arranged in parallel. The first connecting block is provided with a plurality of first mounting bolts, and the first connecting block is connected to the main beam through the first mounting bolts.

[0008] According to one embodiment of the present invention, the second connecting block is provided with a plurality of second mounting bolts, and the second connecting block is connected to the main beam through the second mounting bolts.

[0009] According to one embodiment of the present invention, pads are provided between the first connecting block and the main beam, and between the second connecting block and the main beam.

[0010] According to one embodiment of the present invention, the first lifting ring is installed at the end of the first connecting block away from the main beam, and the second lifting ring is installed at the end of the second connecting block away from the main beam.

[0011] According to one embodiment of the present invention, a first threaded rod is installed on the first lifting ring, and a first threaded hole is opened at the end of the first connecting block away from the main beam. The first threaded rod is threaded into the first threaded hole, and the first lifting ring is connected to the first connecting block through the first threaded rod and the first threaded hole.

[0012] According to one embodiment of the present invention, a second threaded rod is installed on the second lifting ring, and a second threaded hole is opened at the end of the second connecting block away from the main beam. The second threaded rod is threadedly engaged in the second threaded hole, and the second lifting ring is connected to the second connecting block through the second threaded rod and the second threaded hole.

[0013] According to one embodiment of the present invention, the number of the second lifting rings is at least two, and the two second lifting rings are symmetrically arranged on the second connecting block with the main beam as the axis of symmetry.

[0014] According to one embodiment of the present invention, both the first lifting ring and the second lifting ring are universal swivel lifting rings.

[0015] According to one embodiment of the present invention, both the first flange and the second flange are provided with positioning pin mounting holes, and positioning pins are detachably installed in the positioning pin mounting holes.

[0016] Beneficial effects This utility model has at least the following technical effects: This invention, through the arrangement of a main beam, a first support beam, a second support beam, a first flange, and a second flange, enables the assembly and positioning of the rocket engine thrust chamber and the turbopump. This allows for precise fixing of the relative positions of the rocket engine thrust chamber and the turbopump, enabling subsequent rocket engine assembly work to proceed with the fixed relative positions. This ensures the installation accuracy between the rocket engine thrust chamber and the turbopump, preventing defects such as deviations in the overall performance of the rocket engine from design requirements, and improving the assembly efficiency between the rocket engine thrust chamber and the turbopump. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 for Figure 1 A magnified view of a portion of point A in the middle; Figure 3 for Figure 1 A schematic diagram of the overall structure from another angle; Figure 4 for Figure 3 A schematic diagram of the overall structure from another angle; Figure 5 This is a schematic diagram of the overall structure of the main beam, the first support beam, and the second support beam in this utility model. Figure 6 This is a schematic diagram of the overall structure of the first connecting block in this utility model; Figure 7 This is a schematic diagram of the overall structure of the second connecting block in this utility model; Figure 8 This is a schematic diagram of the overall structure of the pad block in this utility model; Figure 9 This is a schematic diagram of the overall structure of the first and second lifting rings in this utility model; Figure 10 This is a schematic diagram of the overall structure of the first flange and the second flange in this utility model.

[0019] Explanation of reference numerals in the attached figures: 1. Main beam; 2. First support beam; 3. Second support beam; 4. First flange; 5. Second flange; 6. Gasket; 7. First connecting block; 8. Second connecting block; 9. First lifting ring; 10. Second lifting ring; 11. First mounting bolt; 12. Second mounting bolt; 13. Locating pin. Detailed Implementation

[0020] The features and exemplary embodiments of various aspects of this utility model will be described in detail below. To make the objectives, technical solutions, and advantages of this utility model clearer, the following detailed description is provided in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain this utility model and to exemplarily illustrate the principles of this utility model, and are not configured to limit this utility model. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of this utility model.

[0021] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of this utility model. In the description of this utility model, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0022] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0023] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., without specifically indicating order or sequence, and should not be considered restrictive. Similar terms are used throughout the description to represent similar elements.

[0024] For those skilled in the art, this invention can be implemented without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples.

[0025] In the following embodiments, there may be descriptions such as "this device". It should be understood that "this device" refers to a positioning device for assembling a rocket engine thrust chamber and a turbopump provided by this utility model.

[0026] like Figures 1-10 As shown, this utility model provides a positioning device for assembling a rocket engine thrust chamber and a turbopump. Figure 1 , Figure 3 , Figure 4 and Figure 5 As shown, this device includes at least a main beam 1, a first support beam 2, and a second support beam 3, wherein: like Figure 1 , Figure 3 , Figure 4 and Figure 5 As shown, the first support beam 2 and the second support beam 3 are both installed on the main beam 1, and the first support beam 2 and the second support beam 3 are both located on the same side of the main beam 1.

[0027] In this embodiment, as Figure 1 As shown, the main beam 1, the first support beam 2, and the second support beam 3 can all be rectangular structures, without any special restrictions.

[0028] In this embodiment, the main beam 1, the first support beam 2, and the second support beam 3 can all be made of metal materials known in the art, such as Q235 carbon structural steel, which is not particularly limited here.

[0029] In this embodiment, the main beam 1 and the first support beam 2, and the main beam 1 and the second support beam 3 can be connected by welding, a method known in the art, and are not particularly limited herein.

[0030] In this embodiment, as Figure 1 As shown, the first support beam 2 can be set parallel to the second support beam 3.

[0031] In this embodiment, as Figure 1 As shown, both the first support beam 2 and the second support beam 3 can be installed on... Figure 1 The bottom end of the main beam 1 (i.e., both the first support beam 2 and the second support beam 3 mentioned above are located on the same side of the main beam 1). The first support beam 2 is located on one side of the second support beam 3, and the first support beam 2 and the second support beam 3 can also be located on... Figure 1 The bottom two sides of the main beam 1, that is, the main beam 1, the first support beam 2 and the second support beam 3 will form a U-shaped structure or roughly form a U-shaped structure.

[0032] like Figure 1 As shown, the end of the first support beam 2 furthest from the main beam 1 (i.e. Figure 1 The bottom end of the first beam 2 is equipped with (see reference) Figure 10 First flange 4, second support beam 3 at the end furthest from main beam 1 (i.e. Figure 1 The second flange 5 is installed at the bottom end of the second support beam 3 (see reference). Figure 10 ).

[0033] In this embodiment, the first flange 4 and the first support beam 2, and the second flange 5 and the second support beam 3 can all be connected by welding, a method known in the art, and are not particularly limited herein.

[0034] In this embodiment, both the first flange 4 and the second flange 5 can be flat cylindrical structures.

[0035] It should be understood that, since the first flange 4 and the second flange 5 have the same structure, therefore... Figure 10 This allows us to understand the specific structure of both the first flange 4 and the second flange 5.

[0036] In this embodiment, the first flange 4 and the second flange 5 can be used to connect to the rocket engine thrust chamber and the turbopump, respectively, thereby achieving the assembly and positioning of the rocket engine thrust chamber and the turbopump. Specifically, the first flange 4 can be connected to the flange of the normally level seat on the top of the rocket engine thrust chamber (not shown in the figure), and the first flange 4 can also be connected to the flange at the oxygen pump inlet of the turbopump (not shown in the figure); similarly, the second flange 5 can be connected to the flange of the normally level seat on the top of the rocket engine thrust chamber (not shown in the figure), and the second flange 5 can also be connected to the flange at the oxygen pump inlet of the turbopump (not shown in the figure). In other words, there is no particular limitation on which of the first flange 4 and the second flange 5 is connected to the rocket engine thrust chamber or the turbopump.

[0037] Furthermore, in order to reduce the overall weight of this device, such as Figure 5 As shown, the main beam 1 can be a hollow structure with covers on both sides (not shown in the figure), and the first support beam 2 and the second support beam 3 can both be hollow structures.

[0038] like Figure 1 As shown, the end of the main beam 1 furthest from the first support beam 2 (i.e. Figure 1 A first connecting block 7 and a second connecting block 8 are installed at the top of the main beam 1, with the first connecting block 7 located on one side of the second connecting block 8. A first lifting ring 9 is installed on the first connecting block 7, and a second lifting ring 10 is installed on the second connecting block 8.

[0039] In this embodiment, as Figure 1 As shown, the first connecting block 7 (refer to...) Figure 6 The first connecting block 7 can be set to correspond with the first support beam 2 (i.e., the first connecting block 7 can be located at the first support beam 2). Figure 1 On the same vertical axis), the second connecting block 8 (see reference) Figure 7 The second connecting block 8 can be configured corresponding to the second support beam 3 (i.e., the second connecting block 8 can be located at the second support beam 3). Figure 1 On the same vertical axis (in).

[0040] In this embodiment, as Figure 6 As shown, the first connecting block 7 can be a cuboid structure with rounded corners, which is not particularly limited here.

[0041] Specifically, such as Figure 1 As shown, the first connecting block 7 is provided with a plurality of first mounting bolts 11, that is, the first connecting block 7 can be connected to the main beam 1 through the first mounting bolts 11. The second connecting block 8 is provided with a plurality of second mounting bolts 12, that is, the second connecting block 8 can be connected to the main beam 1 through the second mounting bolts 12.

[0042] In this embodiment, the first mounting bolt 11 and the second mounting bolt 12 can both be bolts with hexagonal heads, and no special limitation is made here.

[0043] In this embodiment, as Figure 1 As shown, the number of the first mounting bolt 11 and the second mounting bolt 12 can both be four, and no special limitation is made here.

[0044] More specifically, main beam 1 in Figure 1The top of the first connecting block 7 is provided with four first mounting threaded holes (not shown in the figure) corresponding to the first mounting bolt 11 and four second mounting threaded holes (not shown in the figure) corresponding to the second mounting bolt 12. The threaded rods of the four first mounting bolts 11 are configured to be threaded into the first mounting threaded holes respectively, and the threaded rods of the four second mounting bolts 12 are configured to be threaded into the second mounting threaded holes respectively, thereby realizing the bolted connection between the first connecting block 7 and the main beam 1, and between the second connecting block 8 and the main beam 1.

[0045] Furthermore, such as Figure 1 As shown, pads 6 are provided between the first connecting block 7 and the main beam 1, and between the second connecting block 8 and the main beam 1 (see reference). Figure 8 Among them, with Figure 1 For example, the top end of the pad 6 between the first connecting block 7 and the main beam 1 abuts against the bottom end of the first connecting block 7, and its bottom end abuts against the top end of the main beam 1; the top end of the pad 6 between the second connecting block 8 and the main beam 1 abuts against the bottom end of the second connecting block 8, and its bottom end abuts against the top end of the main beam 1.

[0046] In this embodiment, as Figure 8 As shown, the pad 6 can be a cuboid structure with rounded corners, and no special limitation is made here.

[0047] like Figure 8 As shown, the pad 6 can be provided with four through holes. The threaded rods of the four first mounting bolts 11 are configured to be located in the four through holes of the pad 6 between the first connecting block 7 and the main beam 1, respectively. The threaded rods of the four second mounting bolts 12 are configured to be located in the four through holes of the pad 6 between the second connecting block 8 and the main beam 1, respectively. Thus, the pad 6 is installed between the first connecting block 7 and the main beam 1 and between the second connecting block 8 and the main beam 1.

[0048] Specifically, such as Figure 1 As shown, the first lifting ring 9 is installed at the end of the first connecting block 7 away from the main beam 1 (i.e., Figure 1 The first connecting block 7 is located at its top end, and the second lifting ring 10 is installed at the end of the second connecting block 8 furthest from the main beam 1 (i.e., at the top end of the first connecting block 7). Figure 1 (The top of the second connecting block 8).

[0049] More specifically, such as Figure 9 As shown, a first threaded rod is installed on the first lifting ring 9, and the first connecting block 7 is located at the end furthest from the main beam 1 (i.e., Figure 1 The top of the first connecting block 7 has a first threaded hole (see reference). Figure 6The first threaded rod is adapted to the first threaded hole, and the first threaded rod is configured to be threaded into the first threaded hole, that is, the first lifting ring 9 can be detachably connected to the first connecting block 7 through the first threaded rod and the first threaded hole.

[0050] In this embodiment, as Figure 6 As shown, the first threaded hole can be opened at the exact center of the first connecting block 7, without any particular limitation.

[0051] Similarly, as Figure 9 As shown, a second threaded rod is installed on the second lifting ring 10, and the end of the second connecting block 8 away from the main beam 1 (i.e. Figure 1 The top of the second connecting block 8 has a second threaded hole (see reference). Figure 7 The second threaded rod is adapted to the second threaded hole, and the second threaded rod is configured to be threaded into the second threaded hole, that is, the second lifting ring 10 is detachably connected to the second connecting block 8 through the second threaded rod and the second threaded hole.

[0052] In this embodiment, the first lifting ring 9 and the first threaded rod, and the second lifting ring 10 and the second threaded rod can be connected by welding, a method known in the art, and are not particularly limited herein.

[0053] Furthermore, such as Figure 1 As shown, the number of second lifting rings 10 is at least two, preferably two, and the two second lifting rings 10 are symmetrically arranged on the second connecting blocks 8 with the main beam 1 as the axis of symmetry (that is, symmetrically arranged on the second connecting blocks 8 with the main beam 1 as the axis of symmetry). Figure 1 (at the top of the middle).

[0054] In this embodiment, since there are two second lifting rings 10, there are also two second threaded holes, which are sequentially opened at the top of the second connecting block 8 (i.e., Figure 1 The two sides of the top of the second connecting block 8.

[0055] With the above configuration, when this device is hoisted using external hoisting equipment (not shown in the figure and known in the art), the hoisting rope (not shown in the figure) on the external hoisting equipment, together with the first lifting ring 9 and the two second lifting rings 10, will form a triangular structure, thereby improving the stability of this device during hoisting and effectively preventing swaying. Simultaneously, the tilt angle of this device can be adjusted to adapt to different working conditions, thus improving work efficiency.

[0056] It should be understood that, since the first ring 9 and the second ring 10 have the same structure, therefore... Figure 9 This allows one to understand the specific structure of both the first ring 9 and the second ring 10.

[0057] Furthermore, both the first lifting ring 9 and the second lifting ring 10 are universal swivel lifting rings.

[0058] By incorporating a universal rotating lifting ring, the flexibility of the first lifting ring 9 and the second lifting ring 10 can be improved, thereby adapting to different working conditions and increasing work efficiency. The universal rotating lifting ring is existing technology known in the art and will not be described in detail here.

[0059] Furthermore, such as Figure 1 and Figure 2 As shown, both the first flange 4 and the second flange 5 are provided with locating pin mounting holes, and locating pins 13 can be detachably installed in the locating pin mounting holes.

[0060] In this embodiment, the number of locating pin mounting holes on the first flange 4 and the second flange 5 is not particularly limited. For example, they can be staggered with the flange bolt holes on the first flange 4 and the second flange 5. The locating pin 13 is prior art known in the art and will not be described in detail here.

[0061] By setting the locating pin 13, when the first flange 4 and the second flange 5 need to be connected to the rocket engine thrust chamber (not shown in the figure) and the turbopump (not shown in the figure) respectively, the locating pin 13 can provide a positioning effect, thereby avoiding the problem of low connection efficiency caused by the tolerance between different workpieces, and thus improving work efficiency.

[0062] The working process of this device will be briefly described below with reference to the above embodiments: During the assembly of rocket engines, especially in the assembly of post-pump rocket engines, when it is necessary to assemble and position the rocket engine thrust chamber (not shown in the figure) and turbopump (not shown in the figure), firstly, according to the relative height difference between the rocket engine thrust chamber and the turbopump, the first support beam 2 and the second support beam 3 of different lengths are machined, and then all the components of this device are assembled to complete the assembly of this device and prepare for the positioning work of the rocket engine thrust chamber and turbopump.

[0063] Then, the first flange 4 or the second flange 5 is bolted to the flange at the oxygen pump inlet of the turbine pump (not shown in the figure) using flange connecting bolts (not shown in the figure) known in the art. Prior to this work, the first flange 4 or the second flange 5 can be precisely positioned to the flange at the oxygen pump inlet of the turbine pump using locating pins 13. This avoids the problem of low flange connecting bolt installation efficiency caused by tolerances between the first flange 4 or the second flange 5 and the flange at the oxygen pump inlet of the turbine pump, thus improving work efficiency.

[0064] Next, after the above work is completed, the external hoisting equipment (not shown in the figure but known in the art) is connected to the first lifting ring 9 and the second lifting ring 10, and the device is hoisted together with the turbopump. For example, if the first flange 4 was connected to the flange at the oxygen pump inlet of the turbopump in the above work, then the second flange 5 can be hoisted onto the flange of the constant-level seat on the top of the rocket engine thrust chamber (not shown in the figure). After hoisting, the above steps are repeated, and the second flange 5 and the flange of the constant-level seat on the top of the rocket engine thrust chamber are precisely positioned by the locating pin 13 and then connected to each other by the flange connecting bolts, thus completing the precise fixing of the relative position of the rocket engine thrust chamber and the turbopump (that is, realizing the assembly positioning of the rocket engine thrust chamber and the turbopump).

[0065] Finally, once the relative positions of the rocket engine thrust chamber and the turbopump are precisely fixed (i.e., the rocket engine thrust chamber and the turbopump are assembled and positioned), subsequent rocket engine assembly work can be carried out. This ensures the installation accuracy between the rocket engine thrust chamber and the turbopump, avoids defects that cause the overall performance of the rocket engine to deviate from the design requirements, and improves the assembly efficiency between the rocket engine thrust chamber and the turbopump.

[0066] Furthermore, the assembly positioning accuracy of this device can be improved to 0.01mm, and the circumferential angle accuracy of the turbopump after assembly can be improved to 0.01°. Therefore, the overall assembly position accuracy is improved, ensuring the reliability of the assembly. Compared with the traditional assembly relying on visual inspection, this device can complete the assembly and positioning of the rocket engine thrust chamber and turbopump in a maximum of 0.5 hours, compared with the traditional assembly relying on visual inspection which requires at least 4 hours. This significantly reduces the assembly cycle and greatly improves the assembly efficiency.

[0067] It should be understood that the above-described embodiments or examples of this utility model can be combined with each other and have corresponding technical effects.

[0068] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A positioning device for assembling a rocket engine thrust chamber and a turbopump, characterized in that, It includes the main beam (1), the first support beam (2), and the second support beam (3), wherein: The first support beam (2) and the second support beam (3) are both installed on the main beam (1), and the first support beam (2) and the second support beam (3) are both located on the same side of the main beam (1); The first support beam (2) is equipped with a first flange (4) at the end away from the main beam (1), and the second support beam (3) is equipped with a second flange (5) at the end away from the main beam (1). The first flange (4) and the second flange (5) are respectively used to connect with the rocket engine thrust chamber and the turbopump to realize the assembly and positioning of the rocket engine thrust chamber and the turbopump; The main beam (1) is equipped with a first connecting block (7) and a second connecting block (8) at the end away from the first support beam (2), and the first connecting block (7) is located on one side of the second connecting block (8). A first lifting ring (9) is installed on the first connecting block (7), and a second lifting ring (10) is installed on the second connecting block (8).

2. The positioning device for assembling a rocket engine thrust chamber and a turbopump according to claim 1, characterized in that, The first support beam (2) and the second support beam (3) are arranged in parallel; The first connecting block (7) is provided with a plurality of first mounting bolts (11), and the first connecting block (7) is connected to the main beam (1) through the first mounting bolts (11).

3. The positioning device for assembling a rocket engine thrust chamber and a turbopump according to claim 1, characterized in that, The second connecting block (8) is provided with a plurality of second mounting bolts (12), and the second connecting block (8) is connected to the main beam (1) through the second mounting bolts (12).

4. The positioning device for assembling a rocket engine thrust chamber and a turbopump according to claim 1, characterized in that, A pad (6) is provided between the first connecting block (7) and the main beam (1), and between the second connecting block (8) and the main beam (1).

5. The positioning device for assembling a rocket engine thrust chamber and a turbopump according to claim 4, characterized in that, The first lifting ring (9) is installed at the end of the first connecting block (7) away from the main beam (1), and the second lifting ring (10) is installed at the end of the second connecting block (8) away from the main beam (1).

6. The positioning device for assembling a rocket engine thrust chamber and a turbopump according to claim 5, characterized in that, The first lifting ring (9) is equipped with a first threaded rod, and the first connecting block (7) has a first threaded hole at one end away from the main beam (1). The first threaded rod is threaded into the first threaded hole, and the first lifting ring (9) is connected to the first connecting block (7) through the first threaded rod and the first threaded hole.

7. The positioning device for assembling a rocket engine thrust chamber and a turbopump according to claim 5, characterized in that, The second lifting ring (10) is equipped with a second threaded rod, and the second connecting block (8) has a second threaded hole at one end away from the main beam (1). The second threaded rod is threaded into the second threaded hole, and the second lifting ring (10) is connected to the second connecting block (8) through the second threaded rod and the second threaded hole.

8. The positioning device for assembling a rocket engine thrust chamber and a turbopump according to claim 5, characterized in that, The number of the second lifting ring (10) is at least two, and the two second lifting rings (10) are symmetrically arranged on the second connecting block (8) with the main beam (1) as the axis of symmetry.

9. The positioning device for assembling a rocket engine thrust chamber and a turbopump according to claim 1, characterized in that, Both the first lifting ring (9) and the second lifting ring (10) are universal swivel lifting rings.

10. The positioning device for assembling a rocket engine thrust chamber and a turbopump according to claim 1, characterized in that, Both the first flange (4) and the second flange (5) are provided with positioning pin mounting holes, and positioning pins (13) can be detachably installed in the positioning pin mounting holes.

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