A first stage tail section applied to multi-engine large-thrust reusable rocket

Abstract

The application relates to a first-stage tail section applied to a multi-engine large-thrust reusable rocket, which comprises a cabin body with a cylindrical structure and a frame installed in the cabin body. The frame comprises an upper end layer frame, an engine layer frame and a lower end layer frame, and the engine layer frame is located between the upper end layer frame and the lower end layer frame; the first support rods which form a regular polygon structure are installed in the upper end layer frame; the second support rods which form a cross structure are installed in the engine layer frame, and the third support rods which form a regular polygon structure are arranged in the engine layer frame. The fifth support rods which form a regular polygon structure are arranged in the lower end layer frame, and the fifth support rods are connected with the lower end layer frame through the fourth support rods; the upper end layer frame is connected with the third support rods through the first connecting rods, the upper end layer frame is connected with the second support rods through the second connecting rods, and the third support rods are connected with the fifth support rods through the third connecting rods. The application can adapt to the needs of the first-stage tail section of the multi-engine large-thrust reusable rocket.

Description

Technical Field

[0001] This invention relates to the field of reusable rocket technology, and more specifically to a first-stage tail section for use in multi-engine, high-thrust reusable rockets. Background Technology

[0002] As reusable rockets abroad move from concept to practical engineering application, especially with the success of the Falcon 9 reusable rocket and the urgent need for the StarNet mission, the development of reusable rockets in China is also in full swing, creating a flourishing landscape.

[0003] For reusable rockets with multiple engines and high thrust, the first-stage tail section is the most complex section, with the most interfaces, the most operating conditions, the greatest load-bearing capacity, and the most complex structure. Therefore, the development of the first-stage tail section has now been given entirely new requirements.

[0004] However, the traditional first-stage tail section of a rocket has a relatively small load and does not need to be reused, so its structural design is relatively simple and its load-bearing capacity is relatively small, which cannot meet the needs of the first-stage tail section of a multi-engine, high-thrust, reusable rocket.

[0005] Therefore, there is an urgent need for a first-stage tail section that can be applied to multi-engine (especially nine-engine parallel) high-thrust reusable rockets. Summary of the Invention

[0006] The purpose of this invention is to provide a first-stage tail section applicable to multi-engine, high-thrust, reusable rockets, in order to solve at least some of the technical problems existing in the prior art.

[0007] To achieve the above objectives, the present invention provides the following solution: The present invention provides a first-stage tail section for a multi-engine, high-thrust, reusable rocket, comprising a cabin with a cylindrical structure and a frame mounted within the cabin; The frame includes an upper frame, an engine frame, and a lower frame, all mounted on the inner wall of the cabin, with the engine frame located between the upper frame and the lower frame. The upper frame contains several first support rods forming a regular polygon structure; the engine frame contains several second support rods forming a cross structure; the engine frame contains several third support rods forming a regular polygon structure, the third support rods being connected to the engine frame via the second support rods; the second support rods are used to install the central engine, and the third support rods are used to install the outer ring engine; the lower frame contains several fifth support rods forming a regular polygon structure, the fifth support rods being connected to the lower frame via fourth support rods. The upper frame is connected to the third support rod via a first connecting rod, the upper frame is connected to the second support rod via a second connecting rod, and the third support rod is connected to the fifth support rod via a third connecting rod. The outer wall of the cabin is equipped with main lugs corresponding to the upper layer frame and secondary lugs corresponding to the lower layer frame.

[0008] According to one embodiment of the present invention, the cabin is a cylindrical structure; The upper frame, the engine frame, and the lower frame are all annular structures, and the outer wall diameters of the upper frame, the engine frame, and the lower frame are the same as the inner wall diameter of the cabin.

[0009] According to one embodiment of the present invention, the cabin includes a skin and stringers; the skin is a cylindrical structure, and the number of stringers is several and they are installed sequentially and evenly on the inner wall of the skin along the circumference of the skin; The upper frame, the engine frame, and the lower frame are all mounted on the stringer. Both the main lug and the secondary lug are installed on the outer wall of the skin.

[0010] According to one embodiment of the present invention, the number of the first support rods is at least four and they form a regular quadrilateral structure, and the regular quadrilateral structure formed by the four first support rods is concentrically arranged with the upper frame. The number of the second support rods is at least two and they form a cross structure, with the intersection of the cross structure formed by the two second support rods located at the center of the engine layer frame; the number of the third support rods is at least eight and they form a regular octagon structure, with the regular octagon structure formed by the eight third support rods being concentrically arranged with the engine layer frame; The two second support rods and the eight third support rods are connected at any four included angles of the regular octagonal structure; The number of the fifth support rods is at least eight, forming a regular octagonal structure. The regular octagonal structure formed by the eight fifth support rods is concentrically arranged with the lower end frame. The number of the fourth support rods is at least eight, and the eight fourth support rods all point to the center position of the lower end frame and are respectively arranged at the eight included corners of the regular octagonal structure formed by the eight fifth support rods.

[0011] According to one embodiment of the present invention, a joint is installed at each of the four included corners of the regular quadrilateral structure formed by the four first support rods; The fourth support rod is an I-beam.

[0012] According to one embodiment of the present invention, the number of central engines is one and it is installed at the intersection of the cross structure formed by the two second support rods; The number of outer ring engines is eight, and each engine is installed at the center of one of the eight third support rods.

[0013] According to one embodiment of the present invention, a first engine mounting seat is installed at the intersection of the cross structure formed by the two second support rods, and the central engine is mounted at the intersection of the cross structure formed by the two second support rods via the first engine mounting seat; Each of the eight third support rods has a second engine mounting base installed at its center, and the eight outer ring engines are respectively mounted on the center of the eight third support rods via the eight second engine mounting bases.

[0014] According to one embodiment of the present invention, the number of the first connecting rods is at least sixteen and they are arranged in pairs, and the eight pairs of the first connecting rods are respectively arranged corresponding to the eight third support rods; the end of each pair of the first connecting rods near the corresponding third support rod is connected to the center position of the corresponding third support rod, and the end of each pair of the first connecting rods away from the corresponding third support rod is respectively connected to the four included corners of the regular quadrilateral structure formed by the four first support rods; The number of the second connecting rods is at least four. One end of each of the four second connecting rods is connected to the intersection of the cross structure formed by the two second support rods, and the other end of each of the four second connecting rods is connected to the four included corners of the square structure formed by the four first support rods. The number of the third connecting rods is at least eight. One end of each of the eight third connecting rods is connected to one of the eight included corners of the regular octagonal structure formed by the eight third supporting rods, and the other end of each of the eight third connecting rods is connected to one of the eight included corners of the regular octagonal structure formed by the eight fifth supporting rods.

[0015] According to one embodiment of the present invention, the number of main support ears is at least four, and the four main support ears are respectively connected to the four included corners of the regular quadrilateral structure formed by the four first support rods.

[0016] According to one embodiment of the present invention, a column is installed between the engine layer frame and the lower end layer frame, and the number of the column is at least four and they are arranged evenly along the circumference of the cabin. The number of auxiliary lugs is at least four, and each of the four auxiliary lugs is connected to one of the four columns respectively through a first force transmission component and a second force transmission component.

[0017] Beneficial effects This invention has at least the following technical effects: This invention, through the arrangement of an upper frame, an engine frame, a lower frame, and a first, second, third, fourth, and fifth support rod of a regular polygonal structure, along with a first, second, and third connecting rod, achieves a large load-bearing capacity, thus meeting the requirements of the first-stage tail section of a multi-engine, high-thrust reusable rocket. Simultaneously, through the above arrangement, this invention also satisfies the requirements of reusable rockets in restraint and release operations, reusable rocket landing operations, and the overall requirement for strict control of structural weight. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention 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 the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the overall structure of the cabin in this invention; Figure 3 This is a schematic diagram of the overall structure of the frame in this invention; Figure 4 This is a schematic diagram of the overall structure of the upper layer frame in this invention; Figure 5 This is a schematic diagram of the overall structure of the engine layer frame in this invention; Figure 6 This is a schematic diagram of the overall structure of the lower end frame in this invention; Figure 7 This is a schematic diagram of the overall structure of the secondary support lug, the first force transmission component, and the second force transmission component in this invention.

[0020] Explanation of reference numerals in the attached figures: 1. Hull; 11. Skin; 12. Beams; 2. Rack; 21. Upper frame; 211. First support rod; 212. Joint; 22. Engine frame; 221. Second support rod; 222. Third support rod; 223. First engine mounting bracket; 224. Second engine mounting bracket; 23. Lower frame; 231. Fourth support rod; 232. Fifth support rod; 3. Columns; 4. First connecting rod; 5. Second connecting rod; 6. Third connecting rod; 7. Main ear; 8. Secondary support lug; 81. First force transmission component; 82. Second force transmission component. Detailed Implementation

[0021] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and to exemplify the principles of the present invention, and are not configured to limit the present invention. 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 the present invention.

[0022] 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 the present invention. In the description of the present invention, 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 the present invention according to the specific circumstances.

[0023] 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.

[0024] 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.

[0025] For those skilled in the art, the present invention can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.

[0026] like Figures 1-7 As shown, this invention provides a first-stage tail section applicable to a multi-engine, high-thrust, reusable rocket. For example... Figure 1 As shown, this first-stage tail section (i.e., the first-stage tail section of a multi-engine, high-thrust reusable rocket provided by the present invention, hereinafter the same) includes at least a cylindrical cabin 1 and a frame 2 fixedly installed inside the cabin 1, wherein: like Figure 1 and Figure 3 As shown, the frame 2 includes at least an upper frame 21, an engine frame 22, and a lower frame 23, all of which are fixedly installed on the inner wall of the cabin 1, and the engine frame 22 is located between the upper frame 21 and the lower frame 23.

[0027] like Figure 4 As shown, several first support rods 211 capable of forming a regular polygon structure are fixedly installed on the inner wall of the upper frame 21.

[0028] like Figure 5 As shown, several second support rods 221 capable of forming a cross structure are fixedly installed on the inner wall of the engine layer frame 22. Several third support rods 222 capable of forming a regular polygon structure are arranged inside the engine layer frame 22, and the third support rods 222 can be fixedly connected to the engine layer frame 22 through the second support rods 221. Among them, the second support rods 221 can be used to install the central engine (not shown in the figure), and the third support rods 222 can be used to install the outer ring engine (not shown in the figure).

[0029] like Figure 6 As shown, the lower frame 23 has several fifth support rods 232 that can form a regular polygon structure inside, and the fifth support rods 232 can be fixedly connected to the inner wall of the lower frame 23 through the fourth support rods 231.

[0030] like Figure 3 As shown, the upper frame 21 can be fixedly connected to the third support rod 222 via the first connecting rod 4, and the upper frame 21 can be fixedly connected to the second support rod 221 via the second connecting rod 5. The third support rod 222 can be fixedly connected to the fifth support rod 232 via the third connecting rod 6.

[0031] like Figure 1As shown, the outer wall of the cabin 1 is fixedly equipped with a main support lug 7 corresponding to the upper layer frame 21 and a secondary support lug 8 corresponding to the lower layer frame 23. The main support lug 7 and the secondary support lug 8 can be used to install landing legs (not shown in the figure).

[0032] Preferably, in this embodiment, the cabin 1 can be or is approximately cylindrical. The upper frame 21, engine frame 22, and lower frame 23 can all be annular or approximately annular structures. When the cabin 1 is cylindrical and the upper frame 21, engine frame 22, and lower frame 23 are all annular structures, the outer diameter of the upper frame 21, engine frame 22, and lower frame 23 is the same as the inner diameter of the cabin 1.

[0033] Preferably, in this embodiment, such as Figure 2 As shown, the cabin 1 includes at least a skin 11 and stringers 12. The skin 11 can be a cylindrical structure or a roughly cylindrical structure, and the stringers 12 can be a number that are uniformly fixed to the inner wall of the skin 11 along the circumference of the skin 11.

[0034] Optionally, in this embodiment, the skin 11 and the stringer 12 can be connected by riveting, which is not particularly limited here.

[0035] In this embodiment, the outer walls of the upper layer frame 21, the engine layer frame 22, and the lower layer frame 23 can all be fixedly installed on the end of the stringer 12 away from the skin 11. The main support lug 7 and the secondary support lug 8 are both fixedly installed on the outer wall of the skin 11.

[0036] Preferably, in this embodiment, such as Figure 4 As shown, the number of first support rods 211 is at least four and they form a regular quadrilateral structure (including but not limited to a rectangular structure, a square structure, and preferably a square structure), and the regular quadrilateral structure formed by the four first support rods 211 can be concentrically set with the upper layer frame 21.

[0037] In some embodiments of the present invention, the number of first support rods 211 may also be eight or sixteen, etc., to form a regular octagonal structure or a regular hexagonal structure, etc., which is not particularly limited here.

[0038] Preferably, in this embodiment, such as Figure 5As shown, there are at least two second support rods 221 forming a cross structure, and the intersection of the cross structure formed by the two second support rods 221 is located at the center of the engine layer frame 22. There are at least eight third support rods 222 forming a regular octagon structure, and the regular octagon structure formed by the eight third support rods 222 is concentrically arranged with the engine layer frame 22. Any four included angles (i.e., any four spaced-apart included angles) of the regular octagon structure formed by the two second support rods 221 and the eight third support rods 222 are fixedly connected to each other.

[0039] More preferably, in this embodiment, the two second support rods 221 form a cross structure.

[0040] Optionally, in this embodiment, as Figure 5 As shown, the third support rod 222 can also be fixedly connected to the engine layer frame 22 via four sixth support rods. The four sixth support rods are positioned at any four included angles of the regular octagonal structure formed by the eight third support rods 222, and are staggered and sequentially adjacent to the two second support rods 221. All four sixth support rods point towards the center of the engine layer frame 22.

[0041] Preferably, in this embodiment, such as Figure 6 As shown, there are at least eight fifth support rods 232 forming a regular octagonal structure, and the regular octagonal structure formed by the eight fifth support rods 232 is concentrically arranged with the lower layer frame 23. There are at least eight fourth support rods 231, and all eight fourth support rods 231 point to the center of the lower layer frame 23 and are respectively located at the eight included angles of the regular octagonal structure formed by the eight fifth support rods 232. One end of the fourth support rod 231 is fixedly connected to the outer wall of the fifth support rod 232, and the other end of the fourth support rod 231 is fixedly connected to the inner wall of the lower layer frame 23.

[0042] Specifically, in this embodiment, such as Figure 4 As shown, each of the four included corners of the regular quadrilateral structure formed by the four first support rods 211 is fixedly installed with a connector 212. Additionally, four connectors 212 can be uniformly fixedly installed along the circumference of the inner wall of the upper frame 21, meaning that in this embodiment, the number of connectors 212 can be eight.

[0043] Preferably, the connectors 212 installed at the included corners of the above-mentioned square structure and the connectors 212 installed on the inner wall of the upper frame 21 are arranged in a staggered manner.

[0044] In this embodiment, the joint 212 installed at the included corner of the aforementioned quadrilateral structure can be used to connect and fix the fulcrum on the landing leg to better transmit the landing load; at the same time, it can also serve as a fixing structure for the upper end of the second connecting rod 5 and a portion of the first connecting rod 4 to better transmit the engine thrust. The joint 212 installed on the inner wall of the upper frame 21 can connect and fix the erection structure (not shown in the figure) outside the tail section of this first stage to better transmit the rocket body erection load; at the same time, it can also serve as a fixing structure for the upper end of another portion of the first connecting rod 4 to better transmit the engine thrust.

[0045] Furthermore, in order to improve the structural strength of the tail section of this first stage, the fourth support rod 231 can be an I-beam.

[0046] In this embodiment, the first-stage tail section can be a first-stage tail section containing a "nine-engine parallel" structure; therefore, the number of engines installed in this first-stage tail section is nine. Wherein: The central engine can be one and fixedly installed at the intersection of the cross structure formed by the two second support rods 221; The number of outer ring engines can be eight, and they are respectively fixedly installed at the center position of eight third support rods 222.

[0047] With the above settings, the engine in this embodiment has an "8+1" layout configuration (i.e., eight outer ring engines evenly distributed on the outer ring and one central engine in the center position), which is also the "Octaweb" configuration.

[0048] Optionally, in this embodiment, as Figure 5 As shown, a first engine mounting base 223 is fixedly installed at the intersection of the cross structure formed by the two second support rods 221, meaning the central engine can be fixedly installed at the intersection of the cross structure formed by the two second support rods 221 via the first engine mounting base 223. A second engine mounting base 224 is fixedly installed at the center position of each of the eight third support rods 222, meaning the eight outer ring engines can be fixedly installed at the center position of each of the eight third support rods 222 via the eight second engine mounting bases 224.

[0049] Preferably, in this embodiment, such as Figure 3As shown, there are at least sixteen first connecting rods 4, arranged in pairs, with eight pairs of first connecting rods 4 corresponding to eight third support rods 222. The end of each pair of first connecting rods 4 closest to its corresponding third support rod 222 is fixedly connected to the center of the corresponding third support rod 222, while the end of each pair of first connecting rods 4 furthest from its corresponding third support rod 222 is fixedly connected to the four included angles of the square structure formed by the four first support rods 211. That is, each pair of first connecting rods 4 forms a V-shaped structure, and the included angles of the V-shaped structure formed by each pair of first connecting rods 4 are fixedly connected to the center of the corresponding third support rod 222.

[0050] Preferably, in this embodiment, such as Figure 3 As shown, there are at least four second connecting rods 5. One end of each of the four second connecting rods 5 is fixedly connected to the intersection of the cross structure formed by the two second support rods 221, and the other end of each of the four second connecting rods 5 is fixedly connected to the four included corners of the regular quadrilateral structure formed by the four first support rods 211.

[0051] Preferably, in this embodiment, such as Figure 3 As shown, the number of third connecting rods 6 is at least eight. One end of each of the eight third connecting rods 6 is fixedly connected to one of the eight included corners of the regular octagonal structure formed by the eight third support rods 222, and the other end of each of the eight third connecting rods 6 is fixedly connected to one of the eight included corners of the regular octagonal structure formed by the eight fifth support rods 232.

[0052] Optionally, in this embodiment, the eight third connecting rods 6 can be located in the same vertical plane as the eight fourth support rods 231.

[0053] Optionally, in this embodiment, as Figure 1 As shown, the number of main support ears 7 can be at least four, and the four main support ears 7 can be fixedly connected to the four included corners of the regular quadrilateral structure formed by the four first support rods 211. Among them, the four main support ears 7 can each pass through the skin 11 and the stringer 12, thereby realizing the fixed connection between the main support ears 7 and the first support rods 211.

[0054] Optionally, in this embodiment, as Figure 3 As shown, a column 3 is fixedly installed between the engine layer frame 22 and the lower layer frame 23. The number of columns 3 is at least four, and they are evenly arranged sequentially along the circumference of the cabin 1. The number of auxiliary lugs 8 is also at least four, and all four auxiliary lugs 8 can be transmitted through the first force transmission assembly 81 and the second force transmission assembly 82 (see reference). Figure 7 ) are fixedly connected to the four columns 3 respectively.

[0055] Optionally, in this embodiment, the number of columns 3 can also be eight, and the four secondary lugs 8 can be fixedly connected to any four of the eight columns 3 that are spaced apart.

[0056] Specifically, the first force transmission component 81 can be set on the side wall of the secondary support lug 8, and the second force transmission component 82 can be set on the bottom wall of the secondary support lug 8. Both the first force transmission component 81 and the second force transmission component 82 can be a number of high-strength bolts that can penetrate the skin 11 and the stringer 12, so as to achieve a high-strength fixed connection between the secondary support lug 8 and the column 3.

[0057] Optionally, in this embodiment, the frame 2, skin 11 and stringers 12 can all be made of aluminum alloy, and there is no particular limitation.

[0058] In this embodiment, unless otherwise specified, all the above-mentioned fixed connections can be one or a combination of bolted connections, welded connections, riveted connections, or other connection methods, and are not particularly limited here. For example, the entire frame 2 (that is, the various components in the frame 2) can be connected by bolted connections.

[0059] In some embodiments of the present invention, the primary tail section may also be produced by integral molding methods such as 3D printing, and this is not particularly limited here.

[0060] With the above configuration, this first-stage tail section has at least the following technical advantages compared to existing technologies: 1. The force transmission paths of the support rods (such as the first support rod 211, the second support rod 221, etc.) and connecting rods (such as the first connecting rod 4, the second connecting rod 5, etc.) in the first-stage tail section are clear, and the internal space layout of the cabin 1 is reasonable, which can meet the layout requirements of multiple machines (such as nine machines in parallel in this embodiment).

[0061] 2. This first-stage tail section can meet the requirements of the traction release operation of reusable rockets.

[0062] 3. This first-stage tail section can meet the landing requirements of reusable rockets.

[0063] 4. The tail section of this rocket body is relatively lightweight, which meets the overall requirement for strict control of structural weight.

[0064] 5. This first-stage tail section has a wide range of applications and can meet the needs of various numbers of engines.

[0065] It should be understood that the above-described embodiments or examples of the present invention can be combined with each other and have corresponding technical effects.

[0066] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A first-stage tail section for a multi-engine, high-thrust, reusable rocket, characterized in that: It includes a cabin (1) with a cylindrical structure and a frame (2) installed in the cabin (1); The frame (2) includes an upper frame (21), an engine frame (22) and a lower frame (23) all installed on the inner wall of the cabin (1), with the engine frame (22) located between the upper frame (21) and the lower frame (23). The upper frame (21) is equipped with a plurality of first support rods (211) forming a regular polygon structure; the engine frame (22) is equipped with a plurality of second support rods (221) forming a cross structure; the engine frame (22) is equipped with a plurality of third support rods (222) forming a regular polygon structure; the third support rods (222) are connected to the engine frame (22) through the second support rods (221); the second support rods (221) are used to install the central engine; the third support rods (222) are used to install the outer ring engine; the lower frame (23) is equipped with a plurality of fifth support rods (232) forming a regular polygon structure; the fifth support rods (232) are connected to the lower frame (23) through the fourth support rods (231). The upper frame (21) is connected to the third support rod (222) via the first connecting rod (4), the upper frame (21) is connected to the second support rod (221) via the second connecting rod (5), and the third support rod (222) is connected to the fifth support rod (232) via the third connecting rod (6). The outer wall of the cabin (1) is equipped with a main support lug (7) corresponding to the upper layer frame (21) and a secondary support lug (8) corresponding to the lower layer frame (23).

2. The first-stage tail section of a multi-engine, high-thrust, reusable rocket according to claim 1, characterized in that, The cabin (1) is a cylindrical structure; The upper frame (21), the engine frame (22) and the lower frame (23) are all annular structures. The outer wall diameters of the upper frame (21), the engine frame (22) and the lower frame (23) are the same as the inner wall diameter of the cabin (1).

3. The first-stage tail section of a multi-engine, high-thrust, reusable rocket according to claim 1, characterized in that, The cabin (1) includes a skin (11) and stringers (12); the skin (11) is a cylindrical structure, and the number of stringers (12) is several and they are evenly installed on the inner wall of the skin (11) along the circumference of the skin (11); The upper frame (21), the engine frame (22) and the lower frame (23) are all installed on the stringer (12). Both the main support ear (7) and the secondary support ear (8) are installed on the outer wall of the skin (11).

4. The first-stage tail section of a multi-engine, high-thrust, reusable rocket according to claim 2, characterized in that, The number of the first support rods (211) is at least four and they form a regular quadrilateral structure. The regular quadrilateral structure formed by the four first support rods (211) is concentrically arranged with the upper layer frame (21). The number of the second support rods (221) is at least two and they form a cross structure. The intersection of the cross structure formed by the two second support rods (221) is located at the center of the engine layer frame (22). The number of the third support rods (222) is at least eight and they form a regular octagon structure. The regular octagon structure formed by the eight third support rods (222) is concentrically arranged with the engine layer frame (22). The two second support rods (221) are connected at any four included angles of the regular octagonal structure formed by the eight third support rods (222); The number of the fifth support rods (232) is at least eight and they form a regular octagonal structure. The regular octagonal structure formed by the eight fifth support rods (232) is concentrically arranged with the lower end frame (23). The number of the fourth support rods (231) is at least eight. The eight fourth support rods (231) all point to the center position of the lower end frame (23) and are respectively arranged at the eight included corners of the regular octagonal structure formed by the eight fifth support rods (232).

5. The first-stage tail section of a multi-engine, high-thrust, reusable rocket according to claim 4, characterized in that, A connector (212) is installed at each of the four included corners of the regular quadrilateral structure formed by the four first support rods (211). The fourth support rod (231) is an I-beam.

6. The first-stage tail section of a multi-engine, high-thrust reusable rocket according to claim 4, characterized in that, The number of central engines is one, and it is installed at the intersection of the cross structure formed by the two second support rods (221); The number of outer ring engines is eight, and they are respectively installed at the center of the eight third support rods (222).

7. The first-stage tail section of a multi-engine, high-thrust, reusable rocket according to claim 6, characterized in that, A first engine mounting base (223) is installed at the intersection of the cross structure formed by the two second support rods (221), and the central engine is mounted at the intersection of the cross structure formed by the two second support rods (221) through the first engine mounting base (223); Each of the eight third support rods (222) has a second engine mounting base (224) installed at its center, and the eight outer ring engines are respectively mounted at the center of the eight third support rods (222) via the eight second engine mounting bases (224).

8. The first-stage tail section of a multi-engine, high-thrust reusable rocket according to claim 4, characterized in that, The number of the first connecting rods (4) is at least sixteen and they are arranged in pairs. The eight pairs of the first connecting rods (4) are respectively arranged in correspondence with the eight third support rods (222). The end of each pair of the first connecting rods (4) near the third support rod (222) is connected to the center of the third support rod (222) and the end of each pair of the first connecting rods (4) away from the third support rod (222) is connected to the four included corners of the square structure formed by the four first support rods (211). The number of the second connecting rods (5) is at least four. One end of each of the four second connecting rods (5) is connected to the intersection of the cross structure formed by the two second support rods (221), and the other end of each of the four second connecting rods (5) is connected to the four included corners of the regular quadrilateral structure formed by the four first support rods (211). The number of the third connecting rods (6) is at least eight. One end of each of the eight third connecting rods (6) is connected to one of the eight included corners of the regular octagonal structure formed by the eight third support rods (222), and the other end of each of the eight third connecting rods (6) is connected to one of the eight included corners of the regular octagonal structure formed by the eight fifth support rods (232).

9. The first-stage tail section of a multi-engine, high-thrust, reusable rocket according to claim 4, characterized in that, The number of main support ears (7) is at least four, and the four main support ears (7) are respectively connected to the four included corners of the regular quadrilateral structure formed by the four first support rods (211).

10. The first-stage tail section of a multi-engine, high-thrust reusable rocket according to claim 4, characterized in that, A column (3) is installed between the engine layer frame (22) and the lower end layer frame (23), and the number of the column (3) is at least four and they are evenly arranged along the circumference of the cabin (1). The number of the secondary support lugs (8) is at least four, and the four secondary support lugs (8) are respectively connected to the four columns (3) through the first force transmission component (81) and the second force transmission component (82).

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