A spacecraft engine mount and method of designing the same

Abstract

The application provides a spacecraft engine support and a design method thereof, and belongs to the technical field of spacecraft structure design. The spacecraft engine support is a combined support, comprising a plurality of mutually independent thin-shell polyhedral carbon fiber composite single supports. One of the single supports is used as a main support for mounting a main engine, and the other second to sixth single supports are combined and connected to each other by being mounted on the main support and being mutually glued and screwed through the inclined surfaces of the polyhedrons, thereby forming a thin-shell polyhedral carbon fiber composite combined support. The combined support provides a connection interface with a spacecraft cabin through the main support for mounting the main engine, and also provides mounting interfaces for a plurality of spatially distributed engines and an extravehicular gas cylinder. The application comprises a plurality of sets of mounting interfaces for a plurality of main engines and attitude control engines which are centrally mounted on the outside of a lightweight lander cabin and have strong adaptability to complex interfaces and large temperature difference environments, good pointing stability and light weight.

Description

Technical Field

[0001] This invention relates to a spacecraft engine bracket and its design method, belonging to the field of spacecraft structural design technology. Background Technology

[0002] Based on the specific mission requirements of a spacecraft, more than thirty landing, orbit control, and attitude control engines need to be installed on the outer side of the thin-walled cabin. These engines have numerous and densely distributed interfaces. Due to the large temperature differences in the operating environment during spaceflight, landing, takeoff, and engine operation, the structure also needs to be extremely lightweight according to the design requirements. There is an urgent need to find a technology and design solution that can simultaneously meet all of these requirements. Summary of the Invention

[0003] To overcome the shortcomings of existing technologies, a spacecraft engine bracket is provided. Belonging to a spacecraft mechanical system, it is suitable for the centralized installation of over thirty engines and multiple extravehicular atmospheric cylinders on the thin-walled exterior of a spacecraft in environments with large temperature differences. The bracket features complex interfaces, high integration, light weight, high rigidity, good mechanical and thermal stability, and good adaptability to large temperature differences. Specific implementation details may vary depending on the actual model.

[0004] The objective of this invention is achieved through the following technical solutions:

[0005] A spacecraft engine support bracket is disclosed. This bracket is a composite bracket comprising multiple independent thin-shell polyhedral carbon fiber composite unit brackets. A first unit bracket (1), which mounts the main engine, serves as the main support bracket. The other second to sixth unit brackets (2, 3, 4, 5, or 6) are connected to the main support bracket via interlocking screws on the inclined surfaces of the polyhedrons, ultimately forming a complex-shaped thin-shell polyhedral carbon fiber composite composite bracket. This composite bracket provides a connection interface to the spacecraft cabin via the main support bracket for mounting the main engine, and is subsequently installed on the outside of the spacecraft's inverted conical cabin. This composite bracket also provides mounting interfaces for multiple space-configured engines and extravehicular atmospheric cylinders.

[0006] Furthermore, the first single-unit bracket is used to install the main engine, i.e., the main engine bracket. The second single-unit bracket 2 is used to install the first auxiliary engine, i.e., the first auxiliary engine bracket. The third single-unit bracket 3 is used to install the third auxiliary engine, i.e., the third auxiliary engine bracket. The fourth single-unit bracket 4 is used to install the dual-head second auxiliary engine, i.e., the dual-head second auxiliary engine bracket. The fifth single-unit bracket 5 and the sixth single-unit bracket 6 are mirror images of each other, used to install the single-head second auxiliary engine, and are the left and right parts of the single-head second auxiliary engine bracket.

[0007] Furthermore, in the aforementioned spacecraft engine bracket, after the individual brackets are glued and screwed together face-to-face, carbon cloth is used to reinforce the glued joints.

[0008] Furthermore, in the aforementioned spacecraft engine support, each individual support is made of high-modulus carbon fiber composite material, which improves the rigidity and strength of the support while ensuring that the thermal expansion coefficients of each individual support are matched to adapt to environments with large temperature differences.

[0009] Furthermore, in the aforementioned spacecraft engine bracket, heat-insulating gaskets are added at the mounting interfaces between the engine and each individual bracket. Screws are used for auxiliary fixing to ensure that the heat-insulating gaskets do not detach in environments with large temperature differences. The heat-insulating gaskets can be machined as a whole in the assembled state to achieve the accuracy of the mounting surface.

[0010] A design method for a spacecraft engine support, comprising the following steps for designing the configuration and parameters of all individual support units:

[0011] First, the column is obtained by stretching from the main support mounting surface (the first single-unit support mounting surface). The single-unit support mounting surface has the same shape as the target mounting surface of the corresponding other single-unit supports or cabins to ensure continuous load-bearing capacity.

[0012] Secondly, by tilting the main support inward or outward, ensure that the main support can cover all the connection interfaces of the engine and other supports required by the individual supports.

[0013] Third, the column is cut using the planes of the engine interface and other bracket interfaces;

[0014] Fourth, tilt the adjacent sides of the interface plane to minimize the total number of interfaces;

[0015] Fifth, the resulting interface plane polygon is cut and trimmed to further ensure the principle of minimizing the interface plane, while also trimming the sharp edges of polyhedra with excessively small angles that are difficult to manufacture.

[0016] Sixth, the final polyhedron obtained above is shelled;

[0017] Seventh, due to the need for weight reduction and operating space, large holes were drilled on all sides of the polyhedron, while the edge frame was retained for load-bearing; the shape and size of the openings were determined using shape topology optimization methods; optimization was carried out in the combined state.

[0018] Eighth, the shell wall thickness was determined using parameter optimization methods; after static verification, areas with insufficient strength were reinforced by increasing the wall thickness; after stability analysis, components in areas with insufficient stability were reinforced using L-shaped beams and frames. Parameter optimization, static verification, and stability analysis were performed under the combined state.

[0019] Ninth, all engine interfaces are provided via threaded metal flanges. To adapt to environments with large temperature differences and reduce thermal stress caused by dissimilar materials, the threaded metal flange interfaces are cut and discrete into small metal flange assemblies containing only one, two, or three threads. After the small metal flanges are bonded to the carbon fiber brackets, carbon cloth is still needed to reinforce the bonding edges to prevent peeling. Therefore, except for the threaded areas where the material is thicker, the remaining areas of the small metal flanges use a thin-walled fin design. The threads at the metal flanges can be machined as a whole in the assembled state to achieve the accuracy of the mounting point position.

[0020] Finally, heat-insulating gaskets can be added to the mounting interfaces between the engine and each unit bracket. Screws can be used to assist in fixing to ensure that the heat-insulating gaskets do not detach in environments with large temperature differences. The heat-insulating gaskets can be machined as a whole in the assembled state to achieve the accuracy of the mounting surface.

[0021] Compared with the prior art, the present invention has the following advantages:

[0022] (1) The present invention adopts a thin-shell polyhedral combination splicing form, which can achieve a high degree of integration of the engine interface within the narrow space of the launch vehicle envelope and the lander installation interface.

[0023] (2) The main body of each unit support of the present invention adopts a thin shell polyhedral structure, and the force transmission path between the load installation interface and the structural boundary is direct, which realizes the high efficiency of structural bearing and effectively reduces the structural weight.

[0024] (3) The main body of each individual support in this invention is made of carbon fiber composite material with high modulus and low coefficient of thermal expansion, which further reduces the structural weight, ensures structural rigidity, and improves the mechanical and thermal stability of the structure. Since the coefficient of thermal expansion of each individual support is the same, the matching of the coefficients of thermal expansion of multiple individual support interfaces is ensured, reducing interfacial thermal stress and improving the adaptability of the structure to large temperature difference environments. This invention further improves the structural strength of the structure under large temperature difference working environments by rationally selecting resin matrix and structural adhesive as the main body materials.

[0025] (4) The present invention provides threads through small-sized metal parts, which ensures the screw fastening of the composite support and avoids the problem of the threaded fastening metal parts detaching under large temperature difference. The bonding strength of the metal parts is further strengthened by the supplementary carbon cloth.

[0026] (5) The present invention allows for mirror design and recombination of single and multi-body brackets to obtain a variety of engine installation configurations. Through simple local replacement, the consistency of the bracket body is achieved, reducing the number of brackets and lowering the process difficulty and cost. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the configuration of a single support assembly of the present invention;

[0028] Figure 2 This is an exploded view of a single support assembly of the present invention;

[0029] Figure 3 This is a schematic diagram of the configuration of the present invention, in which two sets of four brackets are installed on the side of the lander hull. Figure 1 ;

[0030] Figure 4 This is a schematic diagram of the configuration of the present invention, in which two sets of four brackets are installed on the side of the lander hull. Figure 2 ;

[0031] Figure 5 This is a schematic diagram of the main engine support structure of the present invention;

[0032] Figure 6 This is a partial schematic diagram of the main engine mounting interface of the present invention;

[0033] Figure 7 This is a schematic diagram of the first auxiliary engine support structure of the present invention;

[0034] Figure 8 This invention relates to the first auxiliary engine interface and the downward third auxiliary engine mounting interface;

[0035] Figure 9 This is a schematic diagram of the dual-head second auxiliary engine support structure of the present invention;

[0036] Figure 10 This is a schematic diagram of the single-head second auxiliary engine support structure of the present invention from both positive and negative angles;

[0037] Figure 11 This is a schematic diagram of the third auxiliary engine support structure of the present invention.

[0038] In the diagram: 1 First single-unit support; 2 Second single-unit support; 3 Third single-unit support; 4 Fourth single-unit support; 5 Fifth single-unit support; 6 Sixth single-unit support;

[0039] 11 Triangular prism; 12 Frustum of a square pyramid; 13 Middle frame; 21 First side surface; 22 Bottom surface of the second unit support; 23 Second side surface; 31 Bottom surface of the third unit support; 32 Top surface of the third unit support; 33-36 Bevels formed by partially blunting the four edges of the frustum; 41 Bottom surface of the fourth unit support; 42 First end face of the fourth unit support; 43 Second end face of the fourth unit support; 44 First mounting surface for mounting the second auxiliary engine; 45 Second mounting surface for mounting the second auxiliary engine; 46 First side surface of the fourth unit support; 47 Second side surface of the fourth unit support; 51 Bottom surface of the fifth unit support; 52 Top surface of the fifth unit support; 53 First side surface of the fifth unit support; 54 Second side surface of the fifth unit support;

[0040] 111 First end face; 112 Second end face; 113 Inverted conical surface; 114 Side of the first single-unit support; 115 Corner beam arranged at the first end face; 116 Corner beam arranged at the second end face; 117 Reinforcing area arranged on the surface where the first end face is located; 118 Reinforcing area arranged on the second end face;

[0041] 121 First side surface; 122 Second side surface; 123 Top surface; 124 Front side mounting surface; 125 Nut; 126 Washer; 127 Front perforated cover plate; 128 Rear perforated cover plate; 129 L-shaped cross-section frame of the front side mounting surface; 1210 L-shaped cross-section frame of the rear perforated cover plate;

[0042] 221 Mounting interface A for mounting the first auxiliary engine; 221 First mounting interface B for mounting the first auxiliary engine; 223 Second mounting interface for mounting the third auxiliary engine; 231 Diagonal structure; 232 L-shaped cross-section beam; 24 Independent component;

[0043] 461 Diagonal structure on the first side; 462 L-shaped cross-section beam on the first side; 471 Diagonal structure on the second side; 472 L-shaped cross-section beam on the second side;

[0044] 531 Diagonal structure on the first side; 532 L-shaped cross-section beam on the first side; 541 Diagonal structure on the second side. Detailed Implementation

[0045] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0046] Example:

[0047] An engine bracket for spacecraft is disclosed in this embodiment, comprising five individual bracket units. This bracket design enables the installation of eight spacecraft engines and one extravehicular atmosphere cylinder. The individual bracket units are joined face-to-face with adhesive bonding and screwing, and then reinforced with carbon fiber cloth at the seams. Each individual bracket unit utilizes high-modulus carbon fiber composite material, improving the rigidity and strength of the bracket while ensuring matching thermal expansion coefficients to adapt to environments with large temperature differences.

[0048] In this embodiment, the design method of a single support includes the following steps:

[0049] First, the column is stretched starting from the bracket mounting surface. The bracket mounting surface has the same shape as the target mounting surface of other corresponding brackets or cabins to ensure continuous load-bearing capacity.

[0050] Secondly, by tilting inward or outward from the side, ensure that the main body can encompass all the connection interfaces of the engine and other supports required by the single bracket.

[0051] Third, the column is cut using the planes of the engine interface and other bracket interfaces;

[0052] Fourth, tilt the adjacent sides of the interface plane to minimize the total number of interfaces;

[0053] Fifth, the resulting interface plane polygon is cut and trimmed to further ensure the principle of minimizing the interface plane, while also trimming the sharp edges of polyhedra with excessively small angles that are difficult to manufacture.

[0054] Sixth, the final polyhedron obtained above is shelled;

[0055] Seventh, due to the need for weight reduction and operating space, large holes were drilled on all sides of the polyhedron, while the edge frame was retained for load-bearing; the shape and size of the openings were determined using shape topology optimization methods; optimization was carried out in the combined state.

[0056] Eighth, the shell wall thickness was determined using parameter optimization methods; after static verification, areas with insufficient strength were reinforced by increasing the wall thickness; after stability analysis, components in areas with insufficient stability were reinforced using L-shaped beams and frames. Parameter optimization, static verification, and stability analysis were performed under the combined state.

[0057] Ninth, to adapt to environments with large temperature differences and reduce thermal stress caused by dissimilar materials, the specific threaded flange interface will be cut and discretized into small metal flange assemblies containing only one, two, or three threads; after the small metal flange is bonded to the carbon fiber bracket, carbon cloth is still needed to reinforce the bonding edges to prevent peeling. Therefore, except for the threaded areas where the material is thicker, the small metal flange uses a thin-walled fin design in other areas; the threads at the metal flange can be machined as a whole in the assembled state to achieve the accuracy of the installation point position;

[0058] Finally, a heat-insulating gasket can be added to the mounting interface between the engine and the unit bracket. The gasket is secured with screws to ensure that it does not detach in environments with large temperature differences. The heat-insulating gasket can be machined as a whole in the assembled state to achieve the accuracy of the mounting surface.

[0059] The individual stent obtained through the above design method is specifically:

[0060] The first single-unit bracket 1, i.e., the main engine bracket, has the following configuration: Figure 5As shown, the shell is integrally composed of a triangular prism 11 and a frustum 12. The frustum 12 is located above the triangular prism 11, meaning the top surface of the triangular prism 11 and the bottom surface of the frustum 12 are coplanar, forming a middle frame 13. The two side surfaces 121 and 122 of the frustum shell are coplanar with the two end surfaces 111 and 112 of the triangular prism 11. The side of the triangular prism 11 facing the lander is an inverted conical surface 113, which coincides with the surface of the lander mounting area. The first end surface 111 and the second end surface 112 are located at the two ends of the triangular prism, respectively. The last outward-facing side surface 114 of the triangular prism 11 provides a mounting surface for the second single-unit support 2, which mounts the first auxiliary engine and also serves as the first auxiliary engine support. The front side surface of the frustum 12 provides a mounting surface 124 for the fourth mounting bracket 4, i.e., the double-headed second auxiliary engine support. The top surface 123 of the truncated pyramid 12 provides a mounting surface for the main engine bracket and gas cylinder. Eighteen custom-made nuts 125 are evenly distributed on the lower surface of the top surface 123, and eighteen custom-made washers 126 corresponding to the nuts are on the upper surface of the top surface 123. The top surfaces of the washers 126 allow for integral machining to ensure coplanarity. To reduce the local stress level at the connection points and improve the load-bearing capacity of the composite top surface 123, both the custom-made nuts 125 and the custom-made washers 126 are equipped with extended fins to reinforce the connection area of ​​the top surface 123. Simultaneously, to reduce additional thermal stress generated between the metal parts and the composite body under large temperature differences, the custom-made nuts 125 and custom-made washers 126 are installed separately and bonded to the top surface 123. To prevent accidental detachment due to peel loads generated during final assembly, the custom-made nuts 125 and custom-made washers 126 are reinforced at the fins with external carbon cloth. To improve strength, the front mounting surface 124 and rear side of the quadrangular pyramid 12 are sealed with perforated cover plates 127 and 128 after final assembly. To enhance the stability of the thin-shell surface, L-shaped cross-section frames 129 and 1210 are installed at the openings of the perforated cover plates 127 and 128 on the front mounting surface 124 and rear side, respectively. To improve stability, the sides 111 and 112 of the quadrangular pyramid 12 are reinforced with L-shaped corner beams 115 and 116 near the large openings close to the inverted conical surface 113 and the middle frame 13, respectively. To improve local strength, the sides 111 and 112 are reinforced with thickened walls on the opposite inclined shell of the corner beams 115 and 116, respectively, in areas 117 and 118. To ensure connection strength, the top surface 123 is thickened overall. To reduce additional loads, the top surface 123 should be sufficiently small, and its edges should be as close as possible to the engine mounting nut 125. Mounting surface 123 ensures the installation of the main engine on its lower surface, while its upper surface is completely open. Provided sufficient strength, the upper surface also provides bottom connection interfaces for the external bi-directional mounting of large gas cylinders. The connection interface at the top of the gas cylinders is achieved by other components, but is not part of the design scope of this engine mount.

[0061] The second single-unit bracket 1, namely the first auxiliary engine bracket, has a slanted triangular prism configuration, including two sides and a bottom surface 22. The two sides are the first side 21 and the second side 23, and the angle between the first side 21 and the bottom surface 22 is small. The first side 21 is connected to the side 114 of the main engine bracket. The bottom surface 22 provides two first auxiliary engine mounting interfaces 221 and 222 and one third auxiliary engine mounting interface 223. Since the three engine mounting surfaces are not coplanar, and in order to meet the requirements for heat insulation installation, the three engine mounting interfaces 221, 222, and 223 all use slanted heat insulation pads of different thicknesses. The second side 23 provides a mounting surface for the third auxiliary engine bracket 3. To improve in-plane rigidity, the slanted opening of the second side 23 retains a quadrilateral diagonal structure 231. To improve stability, the diagonal structure 231 is connected to an L-shaped cross-section beam 232 with glue threads across its entire surface. Because the included angle between the first side surface 21 and the bottom surface 22 is too small, in order to ensure the molding processability of the composite material, the ends of the included angle between the first side surface 21 and the bottom surface 22 are cut into independent components 24. The independent components 24 are molded separately and connected to the body with glue screws.

[0062] The third unit bracket 3, namely the third auxiliary engine bracket, is a frustum-shaped quadrangular pyramid. Its bottom surface 31 connects to the second side surface 23 of the first auxiliary engine bracket. The top surface 32 provides a mounting interface for the third auxiliary engine, and locally uses irregularly shaped heat-insulating pads to meet the requirements for heat insulation and installation accuracy. To avoid the small included angle of the bevels affecting the processability of the composite material, the edges of the frustum-shaped quadrangular pyramid are locally blunted to form small bevels 33, 34, 35, and 36.

[0063] The fourth unit bracket 4, namely the dual-head second auxiliary engine bracket, has a prism-like configuration. The bottom surface 41 connects to the front mounting surface 124 of the main engine bracket. The prism end face 42 allows connection to the fifth unit bracket 5, and the end face 43 allows connection to the sixth unit bracket 6; that is, the two end faces 42 and 43 are respectively connected to the corresponding left / right components of the single-head second auxiliary engine bracket. In this embodiment, only the left / right components 5 and 6 of the single-head second auxiliary engine bracket are installed on a single assembly bracket. The outer apex is partially beveled to obtain the mounting surfaces 44 and 45 of the two second auxiliary engines. The two sides 46 and 47 each contain a diagonal structure 461 and 471, and corresponding L-shaped cross-section beams 462 and 472.

[0064] The fifth unit bracket 5 and the sixth unit bracket 6 are mirror images of each other; that is, the fifth unit bracket 5 is the left component of the single-head second auxiliary engine bracket, and the sixth unit bracket 6 is the right component of the single-head second auxiliary engine bracket. Taking the left component, the fifth unit bracket 5, as an example, the single-head second auxiliary engine bracket has a frustum-shaped quadrangular pyramid configuration, including a bottom surface 51, a top surface 52, a first side surface 53, and a second side surface 54. Its bottom surface 51 is connected to the first end surface 42 of the double-head second auxiliary engine bracket. The top surface 52 provides an interface for a second auxiliary engine. The first and second side surfaces 53 and 54 are provided with a diagonal structure 531 and 541 as needed. To ensure the strength and stability of 531, an L-shaped cross-section beam 532 is provided for reinforcement. Except for the second auxiliary engine bracket, the remaining bracket assemblies are strictly symmetrical. When the left component (fifth unit bracket 5) and right component (sixth unit bracket 6) of the single-head second auxiliary engine bracket are installed separately on the left or right side of the double-head second auxiliary engine bracket (fourth unit bracket 4), the resulting assemblies are also mirror images of each other, thus meeting the requirements for engine layout and installation. This design method, which retains most components as identical, can greatly reduce the number of molding dies and lower production costs.

[0065] The contents not described in detail in this specification are common knowledge to those skilled in the art.

[0066] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A spacecraft engine support, characterized in that, The spacecraft engine bracket is a combined bracket, which includes multiple independent thin-shell polyhedral carbon fiber composite single brackets. The first single bracket (1) that installs the main engine is used as the main bracket. The other second to sixth single brackets are all connected by being mounted on the main bracket and connected by the inclined surfaces of the polyhedrons. Finally, a complex-shaped thin-shell polyhedral carbon fiber composite combined bracket is formed. The combined support provides a connection interface with the spacecraft cabin through the main support for mounting the main engine, and is then installed on the outside of the inverted conical cabin of the spacecraft; The first single-unit bracket is used to install the main engine; the second single-unit bracket is used to install the first auxiliary engine; the third single-unit bracket is used to install the third auxiliary engine; the fourth single-unit bracket is used to install the dual-head second auxiliary engine; the fifth and sixth single-unit brackets are mirror images of each other and are used to install the single-head second auxiliary engine, serving as the left and right components of the single-head second auxiliary engine bracket.

2. The spacecraft engine support according to claim 1, characterized in that, The combined support also provides installation interfaces for multiple space-layout engines and external atmospheric cylinders.

3. A spacecraft engine support according to claim 1, characterized in that, In the aforementioned spacecraft engine support, each individual support unit is joined face-to-face with adhesive bonding and screwing, and carbon cloth is added to the joints of the adhesive bonding.

4. A spacecraft engine support according to claim 1, characterized in that, In the aforementioned spacecraft engine support structure, each individual support unit is made of high-modulus carbon fiber composite material.

5. A spacecraft engine support according to claim 1, characterized in that, In the aforementioned spacecraft engine bracket, heat-insulating gaskets are added to the mounting interfaces between the engine and each individual bracket.

6. A design method for a spacecraft engine bracket according to any one of claims 1-5, characterized in that, The configuration and parameter design of all individual supports for the spacecraft engine bracket includes the following steps: First, the column is obtained by stretching from the main support mounting surface; the mounting surface of a single support has the same shape as the target mounting surface of other corresponding single supports or cabins. Secondly, by tilting inward or outward from the side, ensure that the main support covers all the connection interfaces of the engine and other supports required by the individual supports. Third, the column is cut using the planes of the engine interface and other bracket interfaces; Fourth, tilt the adjacent sides of the interface plane to minimize the total number of interfaces; Fifth, the resulting interface plane polygon is cut and trimmed to ensure the minimum interface plane size, while also trimming the sharp edges of the polyhedron. Sixth, the final polyhedron obtained in step five is shelled; Seventh, large holes are drilled on all sides of the polyhedron, while retaining the edge frame for load-bearing; the shape and size of the openings are determined using shape topology optimization methods; optimization is performed in the combined state; Eighth, use parameter optimization methods to determine the shell wall thickness; after static verification, increase the wall thickness to reinforce areas with insufficient strength; after stability analysis, use L-shaped cross-section beams and frames to reinforce components in areas with insufficient stability. Ninth, the threaded flange interface used will be cut into small metal flange combinations containing only one, two, or three threads; Finally, heat-insulating gaskets are added to the mounting interfaces between the engine and each unit bracket.

7. The design method for a spacecraft engine bracket according to claim 6, characterized in that, In the eighth step, parameter optimization, static verification, and stability analysis are performed in the combined state.

8. The design method for a spacecraft engine bracket according to claim 6, characterized in that, In the ninth step, after the small metal flange is bonded to the carbon fiber bracket, carbon cloth is used to reinforce the bonding edge to prevent peeling, and a small wall thickness fin design is added.

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