Spacecraft engine support and design method thereof

Abstract

The invention 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 and comprises a plurality of thin-shell polyhedral carbon fiber composite material single supports which are independent of one another, and a first single support for installing a main engine serves as a main body support. And the other second to sixth monomer brackets are mounted on the main body bracket and are combined and connected in a manner of mutually gluing and screwing inclined surfaces of the polyhedrons to form the thin-shell polyhedral carbon fiber composite material combined bracket in a complex shape. The combined bracket provides a connecting interface with a spacecraft cabin through a main body bracket for mounting a main engine, and also provides mounting interfaces for a plurality of space layout engines and a large air cylinder outside the cabin. The invention has the advantages of strong adaptability to complex interfaces and large temperature difference environment, good pointing stability and light weight, and provides installation interfaces of multiple groups of main engines and attitude control engines which are intensively installed on the outer side for a light-weight lander cabin.

Description

Technical Field

[0001] The invention relates to a spacecraft engine bracket and a design method thereof, belonging to the technical field of spacecraft structure design. Background Art

[0002] According to the specific mission requirements of a spacecraft, the spacecraft needs to install more than 30 landing, orbit control, and attitude control engines on the outside of the thin-walled cabin, with many engine interfaces and dense distribution; because of the large temperature difference between the operating temperature and the ambient temperature during space flight, landing and takeoff, and engine operation; at the same time, according to the design mission requirements, the structure also needs to be extremely lightweight. At present, it is urgent to find a technology and design solution that can meet the above requirements at the same time. Summary of the invention

[0003] To overcome the shortcomings of the prior art, a spacecraft engine bracket is provided, which belongs to a spacecraft mechanical system and is suitable for centrally installing more than 30 engines and multiple large cylinders outside the thin-walled cabin of a spacecraft in a space environment with a large temperature difference. The bracket has the characteristics of complex interface, high integration, light weight, high rigidity, good mechanical and thermal stability, and good adaptability to large temperature differences. The specific implementation shall prevail according to the actual model.

[0004] The purpose of the present invention is achieved through the following technical solutions:

[0005] A spacecraft engine bracket, the spacecraft engine bracket is a combined bracket, including multiple independent thin-shell polyhedral carbon fiber composite single-body brackets, one of which is a first single-body bracket 1 for mounting a main engine as a main body bracket, and the other second to sixth single-body brackets 2, 3, 4, 5 or 6 are all mounted on the main body bracket and combined and connected by means of screws on the inclined surfaces of the polyhedrons, finally forming a complex-shaped thin-shell polyhedral carbon fiber composite combined bracket. The combined bracket provides a connection interface with the spacecraft cabin through the main body bracket for mounting the main engine, and is then mounted on the outside of the inverted conical cabin of the spacecraft. The combined bracket also provides an installation interface for multiple space-layout engines and large gas cylinders outside the cabin.

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

[0007] Furthermore, in the spacecraft engine bracket, after the individual brackets are face-to-face bonded and screwed, carbon cloth is used to overlap and reinforce the bonded seams.

[0008] Furthermore, in the spacecraft engine bracket, each single bracket adopts a high modulus carbon fiber composite material, which improves the rigidity and strength of the bracket while ensuring that the thermal expansion coefficients of each single bracket match to adapt to a large temperature difference environment.

[0009] Furthermore, in the spacecraft engine bracket, a heat-insulating material gasket is added at the installation interface between the engine and each single bracket, and screws are used to assist in fixing to ensure that the heat-insulating gasket does not debond in an environment with a large temperature difference; the heat-insulating gasket allows overall machining in the assembled state to achieve installation surface accuracy.

[0010] A design method for a spacecraft engine bracket, the configuration and parameter design method of all single brackets includes the following steps:

[0011] First, the column is stretched starting from the main support mounting surface (first single-body support mounting surface). The single-body support mounting surface has the same shape as the target mounting surface of other single-body supports or cabins to ensure continuous load bearing;

[0012] Secondly, by tilting the sides inward or outward, ensure that the main bracket can envelop all the connection interfaces of the engine and other brackets that the single bracket needs to provide;

[0013] Third, cut the column with the plane of the engine interface and other bracket interfaces;

[0014] Fourth, the side surfaces adjacent to the interface planes are tilted based on the principle of minimizing all interfaces;

[0015] Fifth, the formed interface plane polygons are cut and trimmed to further ensure the minimum principle of the interface plane, and at the same time, the sharp edges of the polyhedron with too small angles that are not suitable for processability are trimmed;

[0016] Sixth, shelling the final state polyhedron obtained above;

[0017] Seventh, due to the need for weight reduction and operating space, large holes are dug on the sides of the polyhedron to retain the edge frame load; the shape topology optimization method is used to determine the shape and size of the opening; the optimization is carried out in the assembled state;

[0018] Eighth, the shell wall thickness is determined using parameter optimization methods; after static verification, the wall thickness of the area with insufficient strength is increased for reinforcement; after stability analysis, the components in the area with insufficient stability are reinforced with L-shaped cross-section beams and frames. Parameter optimization, static verification, and stability analysis are performed in the assembled state;

[0019] Ninth, all engine interfaces are obtained in the form of metal threaded flanges. In order to adapt to the large temperature difference environment and reduce the thermal stress generated by dissimilar materials, the metal threaded flange interface will be cut into discrete small metal flange combinations containing only single, two or three threads; after the small metal flange is bonded to the carbon fiber bracket, it is still necessary to use carbon cloth to reinforce the bonding edge to prevent peeling. Therefore, except for the thicker material at the threaded part of the small metal flange, the rest of the area uses a small wall thickness fin design; the thread at the metal flange allows the overall machining in the assembled state to achieve the installation point position accuracy;

[0020] Finally, a heat-insulating gasket can be added to the mounting interface between the engine and each single-body bracket, and screws can be used to assist in fixing to ensure that the heat-insulating gasket does not debond in an environment with a large temperature difference. The heat-insulating gasket allows for overall machining in the assembled state to achieve mounting surface accuracy.

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

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

[0023] (2) Each single-body bracket of the present invention adopts a thin-shell polyhedron configuration, and the force transmission path between the load installation interface and the structural boundary is direct, thereby achieving high efficiency of structural bearing and effectively reducing the weight of the structure;

[0024] (3) The main body of each monomer bracket of the present invention adopts a carbon fiber composite material with a high modulus and a low thermal expansion coefficient, which further reduces the weight of the structure, ensures the rigidity of the structure, and improves the mechanical and thermal stability of the structure; since the thermal expansion coefficients of each monomer bracket are the same, the matching of the thermal expansion coefficients of the interfaces of multiple monomer brackets is ensured, the thermal stress of the interface is reduced, and the adaptability of the structure to large temperature difference environments is improved. The present invention further improves the structural strength of the structure in a large temperature difference working environment by rationally selecting a resin matrix and a structural adhesive as the main material.

[0025] (4) The present invention provides threads through small-sized metal parts, thereby ensuring the screw fastening of the composite bracket and avoiding the debonding problem of the threaded fastened metal parts under large temperature differences. By means of the carbon cloth supplement, the bonding strength of the metal parts is further enhanced;

[0026] (5) The single-body bracket and multi-body bracket of the present invention allow for mirror-image design and recombination to obtain a variety of engine installation configurations. Through simple local replacement, the consistency of the bracket body is achieved, the number of brackets is reduced, and the process difficulty and cost are reduced. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0028] Figure 2 It is a schematic diagram of the decomposition of a single bracket assembly of the present invention;

[0029] Figure 3 The schematic diagram of the configuration of installing two groups of four brackets on the side of the lander cabin of the present invention is shown in FIG. Figure 1 ;

[0030] Figure 4 The schematic diagram of the configuration of installing two groups of four brackets on the side of the lander cabin of the present invention is shown in FIG. Figure 2 ;

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

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

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

[0034] Figure 8 The first auxiliary engine interface of the present invention and the downward third auxiliary engine installation interface;

[0035] Fig. 9 This is a schematic diagram of the configuration of the double-headed second auxiliary engine support frame of the present invention;

[0036] Fig.10 It is a schematic diagram of the configuration of the single-head second auxiliary engine support frame of the present invention at positive and negative angles;

[0037] Fig.11 It is a schematic diagram of the configuration of the third auxiliary engine support frame of the present invention.

[0038] In the figure: 1 is a first monomer bracket; 2 is a second monomer bracket; 3 is a third monomer bracket; 4 is a fourth monomer bracket; 5 is a fifth monomer bracket; 6 is a sixth monomer bracket;

[0039] 11 triangular prism; 12 quadrangular pyramid; 13 middle frame; 21 first side surface; 22 bottom surface of second monomer bracket; 23 second side surface; 31 bottom surface of third monomer bracket; 32 top surface of third monomer bracket; 33-36 inclined surface formed by partially blunting four edges of pyramid; 41 bottom surface of fourth monomer bracket; 42 first end surface of fourth monomer bracket; 43 second end surface of fourth monomer bracket; 44 first mounting surface for mounting second auxiliary engine; 45 second mounting surface for mounting second auxiliary engine; 46 first side surface of fourth monomer bracket; 47 second side surface of fourth monomer bracket; 51 bottom surface of fifth monomer bracket; 52 top surface of fifth monomer bracket; 53 first side surface of fifth monomer bracket; 54 second side surface of fifth monomer bracket;

[0040] 111 first end face; 112 second end face; 113 inverted conical surface; 114 side surface of the first single bracket; 115 angle beam arranged at the first end face; 116 angle beam arranged at the second end face; 117 reinforcement area arranged at the surface where the first end face is located; 118 reinforcement area arranged at the second end face;

[0041] 121 first side surface; 122 second side surface; 123 top surface; 124 front side mounting surface; 125 nut; 126 gasket; 127 front perforated cover plate; 128 rear perforated cover plate; 129 L-shaped cross-section opening frame of the front side mounting surface; 1210 L-shaped cross-section opening frame of the rear perforated cover plate;

[0042] 221 a mounting interface A for mounting the first auxiliary engine; 221 a first mounting interface B for mounting the first auxiliary engine; 223 a second mounting interface for mounting the third auxiliary engine; 231 a diagonal structure; 232 an L-shaped cross-section beam; 24 an independent component;

[0043] 461 diagonal structure of the first side; 462 L-shaped cross-sectional beam of the first side; 471 diagonal structure of the second side; 472 L-shaped cross-sectional beam of the second side;

[0044] 531 is a diagonal structure of the first side surface; 532 is an L-shaped cross-sectional beam of the first side surface; 541 is a diagonal structure of the second side surface. DETAILED DESCRIPTION

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

[0046] Example:

[0047] An engine bracket for a spacecraft, the engine bracket of this embodiment is composed of 5 single bracket groups, and the engine bracket designed by the present invention can realize the installation of 8 engines and 1 large cylinder outside the cabin of the spacecraft. After the single brackets are face-to-face glued and screwed, carbon cloth is used to overlap and reinforce the glued seams. Each single bracket adopts a high modulus carbon fiber composite material, which improves the rigidity and strength of the bracket while ensuring that the thermal expansion coefficients of each single bracket match to adapt to a large temperature difference environment.

[0048] In this embodiment, the design method of the single-body bracket 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 brackets or cabins to ensure continuous load bearing.

[0050] Secondly, by tilting the sides inward or outward, ensure that the main body can envelop all the connection interfaces of the engine and other brackets that the monolithic bracket needs to provide;

[0051] Third, cut the column with the plane of the engine interface and other bracket interfaces;

[0052] Fourth, the side surfaces adjacent to the interface planes are tilted based on the principle of minimizing all interfaces;

[0053] Fifth, the formed interface plane polygons are cut and trimmed to further ensure the minimum principle of the interface plane, and at the same time, the sharp edges of the polyhedron with too small angles that are not good for processability are trimmed;

[0054] Sixth, shelling the final state polyhedron obtained above;

[0055] Seventh, due to the need for weight reduction and operating space, large holes are dug on the sides of the polyhedron to retain the edge frame load; the shape topology optimization method is used to determine the shape and size of the opening; the optimization is carried out in the assembled state;

[0056] Eighth, the shell wall thickness is determined using parameter optimization methods; after static verification, the wall thickness of the area with insufficient strength is increased for reinforcement; after stability analysis, the components in the area with insufficient stability are reinforced with L-shaped cross-section beams and frames. Parameter optimization, static verification, and stability analysis are performed in the assembled state;

[0057] Ninth, in order to adapt to the large temperature difference environment and reduce the thermal stress generated by dissimilar materials, the specific threaded flange interface will be cut discretely into a small metal flange combination containing only a single, two, or three threads; after the small metal flange is bonded to the carbon fiber bracket, it is still necessary to use carbon cloth to reinforce the bonding edge to prevent peeling. Therefore, except for the thicker material at the threaded part of the small metal flange, the rest of the area uses a small wall thickness fin design; the thread at the metal flange allows the overall machining in the assembled state to achieve the installation point position accuracy;

[0058] Finally, a heat-insulating gasket can be added to the mounting interface between the engine and the single-body bracket, and screws can be used to assist in fixing to ensure that the heat-insulating gasket does not debond in an environment with a large temperature difference. The heat-insulating gasket allows for overall machining in the assembled state to achieve mounting surface accuracy.

[0059] The monomer bracket obtained by the above design method is specifically:

[0060] The first single-body bracket 1, i.e. the main engine bracket, is configured as follows Figure 5As shown, it is composed of a triangular prism 11 and a tetrahedral pyramid 12 shell body, and the tetrahedral pyramid 12 is located above the triangular prism 11, that is, the top surface of the triangular prism 11 and the bottom surface of the tetrahedral pyramid 12 are coplanar, and the coplanar surface forms a middle frame 13. The two side surfaces 121 and 122 of the tetrahedral pyramid 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, and the inverted conical surface 113 coincides with the surface of the lander installation area. The first end surface 111 and the second end surface 112 are respectively located at the two ends of the triangular prism. The last outward side surface 114 of the triangular prism 11 provides a mounting surface for the second single body bracket 2, and the second single body bracket 2 is installed with the first auxiliary engine, which is also the first auxiliary engine bracket. The front side surface of the tetrahedral pyramid 12 is the fourth mounting bracket 4, that is, the double-headed second auxiliary engine bracket provides a mounting surface 124. The top surface 123 of the tetrahedral pyramid 12 provides a mounting surface for the main engine bracket and the gas cylinder. 18 customized nuts 125 are evenly distributed on the lower surface of the top surface 123. The upper surface of the top surface 123 is 18 customized gaskets 126 corresponding to the nuts. The top surface of the gasket 126 allows for integral machining to ensure coplanarity. In order to reduce the local stress level at the connection point and improve the bearing capacity of the composite top surface 123, the customized nuts 125 and the customized gaskets 126 are both provided with extended fins to strengthen the connection area of ​​the top surface 123. At the same time, in order to reduce the additional thermal stress generated between the metal parts and the composite body under a large temperature difference range, the customized nuts 125 and the customized gaskets 126 are bonded and installed with the top surface 123 in a separate state. In order to prevent the peeling load generated during the assembly operation from causing accidental detachment, the customized nuts 125 and the customized gaskets 126 are reinforced with external carbon cloth at the fins. To improve the strength, the front side mounting surface 124 and the rear side surface of the quadrangular pyramid 12 are sealed with perforated cover plates 127 and 128 after the final assembly operation is completed. To improve the stability of the thin shell surface, L-shaped cross-section opening frames 129 and 1210 are respectively set at the openings of the front side mounting surface 124 and the rear side surface perforated cover plates 127 and 128 for reinforcement. To improve the stability, the sides 111 and 112 of the quadrangular pyramid 12 are reinforced with L-shaped cross-section corner beams 115 and 116 in the large opening near the inverted conical surface 113 and the middle frame 13. To improve the local strength, the side surfaces 111 and 112 are respectively reinforced with thickened wall thickness at the bevel shell opposite to the corner beams 115 and 116, and the reinforcement areas are 117 and 118. To ensure the connection strength, the wall thickness of the top surface 123 is thickened as a whole. To reduce the generation of additional loads, the top surface 123 should be small enough, and the top surface edge should be as close as possible to the engine mounting nut 125. The mounting surface 123 ensures the installation of the main engine on the lower surface, while the upper surface is completely open. Under the premise of ensuring sufficient strength, the upper surface also provides a bottom connection interface for the bipolar installation of the large gas cylinder outside the cabin. The connection interface on the top of the gas cylinder is realized by other components, but it does not belong to the design scope of this engine bracket.

[0061] The second single-body bracket 1, i.e., the first auxiliary engine bracket, is an oblique triangular prism configuration, including two side surfaces and a bottom surface 22, wherein the two side surfaces are the first side surface 21 and the second side surface 23, and the first side surface 21 has a small angle with the bottom surface 22. The first side surface 21 is connected to the side surface 114 of the main engine bracket. The bottom surface 22 provides two first auxiliary engine mounting interfaces 221, 222 and one third auxiliary engine mounting interface 223. Since the mounting surfaces of the three engines are not coplanar, and in order to meet the requirements of heat insulation installation, the three engine mounting interfaces 221, 222, and 223 all use oblique heat insulation pads of different thicknesses. The second side surface 23 provides a mounting surface for the third auxiliary engine bracket 3. In order to improve the in-plane rigidity, the oblique opening of the second side surface 23 retains a quadrilateral diagonal structure 231. In order to improve stability, the diagonal structure 231 is connected to the L-shaped cross-section beam 232 with glue and screws on the entire surface. Since the 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 angle between the first side surface 21 and the bottom surface 22 are separately cut into independent components 24, and the independent components 24 are separately molded and connected with the main body rubber screw.

[0062] The third single-body bracket 3, i.e., the third auxiliary engine bracket, is a quadrangular pyramid configuration. The bottom surface 31 is connected to the second side surface 23 of the first auxiliary engine bracket. The top surface 32 provides a third auxiliary engine mounting interface, and a special-shaped thermal insulation pad is partially used to meet the requirements of thermal insulation and mounting accuracy. In order to avoid the influence of too small angle of the inclined plane on the processability of the composite material, the edges of the frustum of the quadrangular pyramid configuration are partially blunted to form small inclined planes 33, 34, 35, 36.

[0063] The fourth single-body bracket 4, i.e., the double-headed second auxiliary engine bracket, is of a quadrangular prism-like configuration. The bottom surface 41 is connected to the front side mounting surface 124 of the main engine bracket. The quadrangular prism end surface 42 allows connection with the fifth single-body bracket 5, and the end surface 43 allows connection with or the sixth single-body bracket 6, i.e., the two end surfaces 42, 43 are respectively connected to the corresponding left / right parts of the single-headed second auxiliary engine bracket. In an embodiment, a single combined bracket only installs the left / right parts 5, 6 of the single-headed second auxiliary engine bracket. The mounting surfaces 44, 45 of the two second auxiliary engines are obtained by local chamfering at the outer vertex. The two side surfaces 46, 47 each include a diagonal structure 461, 471 and corresponding L-shaped cross-section beams 462, 472.

[0064] The fifth single-body bracket 5 and the sixth single-body bracket 6 are mirror images of each other, that is, the fifth single-body bracket 5 is the left part of the single-head second auxiliary engine bracket, and the sixth single-body bracket 6 is the right part of the single-head second auxiliary engine bracket. Taking the left-piece fifth single-body bracket 5 as an example, the single-head second auxiliary engine bracket is a quadrangular pyramid configuration, including a bottom surface 51, a top surface 52, a first side surface 53, and a second side surface 54, and 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 a second auxiliary engine interface. The first and second side surfaces 53 and 54 are provided with a diagonal structure 531 and 541 as needed, wherein an L-shaped cross-section beam 532 is provided to strengthen 531 in order to ensure its strength and stability. Except for the second auxiliary engine bracket, the rest of the bracket assemblies are strictly left-right symmetrical parts. When the left part (fifth single-piece bracket 5) and the right part (sixth single-piece bracket 6) of the single-head second auxiliary engine bracket are selected to be installed separately on the left or right side of the double-head second auxiliary engine bracket (fourth single-piece bracket 4), the two assemblies finally formed are also left and right parts that are mirror images of each other, so as to meet the needs of engine layout installation. This design method that keeps most of the components completely consistent can greatly reduce the number of molding molds and reduce production costs.

[0065] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

[0066] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A spacecraft engine bracket, characterized in that: The spacecraft engine bracket is a combined bracket, including multiple independent thin-shell polyhedral carbon fiber composite single-body brackets, with a first single-body bracket 1 for mounting a main engine as the main body bracket, and the other second to sixth single-body brackets are all mounted on the main body bracket and combinedly connected by means of screws on the inclined surfaces of the polyhedrons, finally forming a combined bracket of a complex-shaped thin-shell polyhedral carbon fiber composite.

2. A spacecraft engine bracket according to claim 1, characterized in that: The combined bracket provides a connection interface with the spacecraft cabin by installing the main body bracket of the main engine, and is further installed on the outside of the inverted cone-shaped cabin of the spacecraft.

3. The spacecraft engine bracket according to claim 1, characterized in that: The combined bracket also provides an installation interface for multiple space-arranged engines and large extravehicular cylinders.

4. The spacecraft engine bracket according to claim 1, characterized in that: In the spacecraft engine bracket, each single bracket is bonded face to face and screwed together, and carbon cloth is added to the bonded seams.

5. The spacecraft engine bracket according to claim 1, characterized in that: In the spacecraft engine bracket, each single bracket is made of high modulus carbon fiber composite material.

6. The spacecraft engine bracket according to claim 1, characterized in that: In the spacecraft engine bracket, a heat insulating material gasket is additionally provided at the installation interface between the engine and each single bracket.

7. The spacecraft engine bracket according to claim 1, characterized in that: The first single-body bracket is used to install the main engine; the second single-body bracket is used to install the first auxiliary engine; the third single-body bracket is used to install the third auxiliary engine; the fourth single-body bracket is used to install the double-headed second auxiliary engine; the fifth single-body bracket and the sixth single-body bracket are mirror images of each other, used to install the single-headed second auxiliary engine, and are the left and right parts of the single-headed second auxiliary engine bracket.

8. A method for designing a spacecraft engine bracket according to any one of claims 1 to 7, characterized in that: The configuration and parameter design of all the single-body brackets of the spacecraft engine bracket includes the following steps: First, the column is obtained by stretching the main support mounting surface as the starting point; the mounting surface of the single-body support has the same shape as the target mounting surface of other single-body supports or cabins; Secondly, ensure that the main support envelops all the connection interfaces of the engine and other supports that the single-body support needs to provide by tilting the side inward or outward; Third, cut the column with the plane of the engine interface and other bracket interfaces; Fourth, the side surfaces adjacent to the interface planes are tilted based on the principle of minimizing all interfaces; Fifth, the formed interface plane polygons are cut and trimmed to ensure the minimum principle of the interface plane and trim the sharp edges of the polyhedron; Sixth, shelling the final state polyhedron obtained above; Seventh, large holes are dug on the sides of the polyhedron to retain the edge frame load-bearing; the shape and size of the openings are determined using the shape topology optimization method; the optimization is carried out in the assembled state; Eighth, the shell wall thickness is determined using parameter optimization methods; after static verification, the wall thickness of the area with insufficient strength is increased for reinforcement; after stability analysis, the components in the area with insufficient stability are reinforced with L-shaped cross-section beams and frames; Ninth, the threaded flange interface adopted will be cut into discrete small metal flange combinations containing only single, two or three threads; Finally, gaskets of thermal insulation material are added to the mounting interfaces between the engine and each monocoque bracket.

9. The design method of a spacecraft engine bracket according to claim 8, characterized in that: In the eighth step, parameter optimization, static verification and stability analysis are performed in the assembled state.

10. The design method of a spacecraft engine bracket according to claim 8, 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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