Engine support and carrier rocket

Abstract

The invention provides an engine support and a carrier rocket. The engine support is applied to a carrier rocket and comprises a support body and a mounting frame, the support body is in a table shape with a closed first end and an open second end, and the diameter of the first end of the support body is smaller than that of the second end; the first end of the support body is provided with an engine installation face used for being connected with a two-stage rocket engine, the second end of the support body is used for being connected with the bottom of a propellant storage box, and the outer wall face of the support body is used for installing engine equipment. The mounting frame is arranged on the outer wall face of the support body and used for being detachably connected with a servo swing mechanism of the two-stage rocket engine. The support body is arranged to be table-shaped and arranged at the bottom of the propellant storage box, the size and weight of the engine support can be reduced, and the weight of a carrier rocket can be reduced.

Description

Technical Field

[0001] This application relates to the technical field of launch vehicles. Specifically, this application relates to an engine bracket and a launch vehicle. Background Art

[0002] During the rocket's liftoff, the thrust, inertial force of the engine, and the aerodynamic load acting on the engine connection mechanism are transmitted to the rocket's airframe, which easily causes severe deformation of the rocket airframe. Therefore, an engine bracket is usually added at the connection position between the engine and the rocket airframe. The engine bracket serves to conduct the acting force and reduce the deformation of the rocket airframe, so as to ensure the stability of the rocket during liftoff to the greatest extent.

[0003] Currently, the engine bracket of a second-stage rocket is usually installed on the end frame of the second-stage rocket body. The volume and occupied space of the engine bracket of the second-stage rocket are relatively large, and it cannot adapt to the development trend of the lightweight of launch vehicles. Summary of the Invention

[0004] In view of the shortcomings of the existing methods, this application proposes an engine bracket and a launch vehicle to solve the technical problem that the engine bracket of the second-stage rocket in the related art occupies a large space and cannot adapt to the development trends of the lightweight and miniaturization of launch vehicles.

[0005] In a first aspect, an embodiment of this application provides an engine bracket applied to a launch vehicle, including: A bracket main body, in the shape of a truncated cone with a closed first end and an open second end, the diameter of the first end of the bracket main body being smaller than that of the second end; the first end of the bracket main body has an engine mounting surface for connecting to the second-stage rocket engine, the second end of the bracket main body is for connecting to the bottom of the propellant tank, and the outer wall surface of the bracket main body is for installing engine equipment; A mounting frame, provided on the outer wall surface of the bracket main body, for detachably connecting to the servo swing mechanism of the second-stage rocket engine.

[0006] Optionally, a plurality of groups of through holes are arranged at intervals along the circumferential direction of the bracket main body, and the plurality of through holes in each group of through holes extend along the generatrix direction of the bracket main body.

[0007] Optionally, a first reinforcing rib extending along the generatrix of the bracket main body is provided between two adjacent through holes; At least two of the first reinforcing ribs are integrally formed with an equipment mounting surface, and the equipment mounting surface is for installing the engine equipment.

[0008] Optionally, the through holes include two first through holes and a plurality of second through holes. The width of the first through holes is greater than that of the second through holes. The two first through holes are symmetrically arranged with respect to a first plane. The first plane is coplanar with the axis of the bracket body and perpendicular to the first end of the bracket body. The mounting bracket and the equipment mounting surface are distributed on both sides of the two through holes.

[0009] Optionally, the mounting bracket includes two mounting bracket bodies symmetrically arranged with respect to the first plane and mounting lugs respectively arranged at the first ends of the two mounting bracket bodies. The first ends of the mounting bracket bodies are arranged parallel to the first end of the bracket body. The two mounting lugs are used for mounting the servo swing mechanism.

[0010] Optionally, the mounting bracket body includes: a connecting rib, a first leg, a second leg, and a mounting seat; The connecting rib extends along the outer wall surface of the bracket body; One ends of the first leg and the second leg are both mounted at the second end of the bracket body. The other ends of the first leg and the second leg are connected to the connecting rib through the mounting seat. The mounting seat is arranged parallel to the first end of the bracket body.

[0011] An included angle is formed between each of the first leg, the second leg, and the connecting rib. The mounting lug and the mounting bracket body are integrally formed.

[0012] Optionally, the engine bracket further includes: at least two second reinforcing ribs, which are arranged inside the space enclosed by the bracket body. At least two of the second reinforcing ribs are cross - arranged, and both ends of each second reinforcing rib abut against the inner wall surface of the bracket body.

[0013] Optionally, at least two of the second reinforcing ribs are arranged at one end of the bracket body close to the first end.

[0014] Optionally, the engine bracket is an integrally formed structure made of aluminum alloy material.

[0015] In a second aspect, an embodiment of the present application provides a launch vehicle, including: a propellant tank, a second - stage rocket engine, and the engine bracket described in the above - mentioned embodiment; The bottom of the propellant tank is in a frustum shape. An installation interface is provided at the bottom of the propellant tank. The installation interface is detachably connected to the second end of the engine bracket; The second - stage rocket engine is arranged at the first end of the engine bracket. The propellant tank, the engine bracket, and the second - stage rocket engine are coaxially arranged.

[0016] The beneficial technical effects brought by the technical solution provided in the embodiments of this application include: In the embodiments of this application, an engine support that can be set at the bottom of the propellant tank is designed. The second-stage rocket engine can be installed at one end far from the propellant tank through this engine support. Compared with the form in the related art where the engine support is installed on the second-stage rocket body end frame on the periphery of the propellant tank, the diameter of at least one end face of the engine support can be reduced, thereby reducing the volume and weight of the engine support. Integrating the engine equipment and the servo swing mechanism of the second-stage rocket engine together on the support main body can make the layout inside the launch vehicle more compact. The support main body adopts a table-like structure, and the servo swing mechanism and the engine equipment are installed on the outer wall surface of the support main body. On the premise of ensuring sufficient installation space for the servo swing mechanism and the engine equipment, the volume and weight of the support main body are reduced, which is beneficial to reducing the overall volume and weight of the launch vehicle.

[0017] Additional aspects and advantages of this application will be given in part in the following description, and these will become obvious from the following description, or can be understood through the practice of this application. Description of the Drawings

[0018] The above-mentioned and / or additional aspects and advantages of this application will become obvious and easy to understand from the following description of the embodiments in conjunction with the drawings, where: Figure 1 is a schematic structural diagram of an engine support provided by an embodiment of this application; Figure 2 is a schematic structural diagram of the internal space enclosed by an engine support provided by an embodiment of this application; Figure 3 is a front view structural diagram of another support main body provided by an embodiment of this application; Figure 4 is Figure 3 a cross-sectional view taken along the a-a' direction in Figure 5 is a schematic structural diagram of an engine support installed at the bottom of the second-stage rocket body end frame provided by an embodiment of this application.

[0019] Description of the Reference Numerals: 10 - support main body; 101 - first end; 102 - second end; 103 - engine mounting surface; 11 - through hole; 111 - first through hole; 112 - second through hole; 12 - first reinforcing rib; 121 - equipment mounting surface; 20 - mounting bracket; 21 - Mounting frame body; 211 - Connecting rib; 212 - First leg; 213 - Second leg; 214 - Mounting base; 22 - Mounting ear; 30 - Second reinforcing rib; 40 - Support ring; 50 - Third reinforcing rib; 60 - Propellant tank; 70 - Second - stage rocket body end frame; 80 - Mounting interface. Specific implementation manner

[0020] The embodiments of the present application will be described below with reference to the accompanying drawings in the present application. It should be understood that the implementation manners described below with reference to the accompanying drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application, and do not constitute limitations on the technical solutions of the embodiments of the present application.

[0021] Those skilled in the art of the present technology can understand that, unless specifically stated, the "the" and "this" used here may also include plural forms. It should be further understood that the term "including" used in the specification of the present application means the presence of the described features, integers, steps, operations, elements, and / or components, but does not exclude the presence of other features, information, data, steps, operations, elements, components, and / or their combinations, etc. supported by the art of the present technology. The term "and / or" used here means at least one of the items defined by this term. For example, "A and / or B" can be implemented as "A", or implemented as "B", or implemented as "A and B".

[0022] To make the purpose, technical solutions, and advantages of the present application clearer, the embodiments of the present application will be further described in detail below with reference to the accompanying drawings.

[0023] In the related art, the second - stage rocket engine bracket is usually installed on the end frame of the second - stage rocket body. The volume and occupied space of the second - stage rocket engine bracket are relatively large, and it cannot adapt to the development trend of the lightweight and miniaturization of launch vehicles.

[0024] In the embodiments of the present application, referring to Figures 1-5 , an engine bracket is provided, which is applied to a launch vehicle and includes a bracket body 10 and a mounting frame 20.

[0025] The bracket body 10 is in the shape of a truncated cone with the first end 101 closed and the second end 102 open. The diameter of the first end 101 of the bracket body 10 is smaller than the diameter of the second end 102. The first end 101 of the bracket body 10 has an engine mounting surface 103 for connecting with the second - stage rocket engine. The second end 102 of the bracket body 10 is used for connecting with the bottom of the propellant tank 60. The outer wall surface of the bracket body 10 is used for installing engine equipment. The mounting frame 20 is arranged on the outer wall surface of the bracket body 10 and is used for detachably connecting with the servo swing mechanism of the second - stage rocket engine.

[0026] In the embodiments of the present application, an engine bracket capable of being arranged at the bottom of the propellant tank 60 is designed. The secondary rocket engine can be installed at one end far from the propellant tank 60 through this engine bracket. Compared with the form in the related art where the engine bracket is installed on the secondary rocket body end frame 70 surrounding the propellant tank 60, the diameter of at least one end face of the engine bracket can be reduced, thereby reducing the volume and weight of the engine bracket. Integrating the engine equipment, the servo swing mechanism of the secondary rocket engine, and the secondary rocket engine together on the bracket main body 10 can make the layout inside the launch vehicle more compact. The bracket main body 10 adopts a frustum structure, and the servo swing mechanism and the engine equipment are installed on the outer wall surface of the bracket main body 10. On the premise of ensuring sufficient installation space for the servo swing mechanism and the engine equipment, the volume and weight of the bracket main body 10 are reduced, which is beneficial to reducing the overall volume and weight of the launch vehicle.

[0027] Optionally, referring to Figures 1-2 , multiple groups of through holes 11 are arranged at circumferential intervals on the bracket main body 10, and the multiple through holes 11 in each group of through holes 11 extend along the generatrix direction of the bracket main body 10.

[0028] By arranging multiple groups of through holes 11 on the bracket main body 10, the weight of the bracket main body 10 can be further reduced, and the overall weight of the launch vehicle can be further reduced.

[0029] Optionally, the shape of the through hole 11 adapts to the frustum structure of the bracket main body 10. In the present application, the width of the through hole 11 gradually increases from the first end 101 of the bracket main body 10 to the second end 102 of the bracket main body 10.

[0030] Optionally, a first reinforcing rib 12 extending along the generatrix of the bracket main body 10 is arranged between two adjacent through holes 11. At least two first reinforcing ribs 12 are integrally formed with an equipment installation surface 121, and the equipment installation surface 121 is used for installing the engine equipment.

[0031] The area between two adjacent through holes 11 is a key stress-bearing area for carrying the mounting frame 20 and the engine equipment. Therefore, arranging the first reinforcing rib 12 extending along the generatrix of the bracket main body 10 between two adjacent through holes 11 can improve the support strength of the bracket main body 10 and avoid structural weakening caused by the lightweight design of the bracket main body 10. And an installation surface is arranged on at least two first reinforcing ribs 12, and the equipment installation surface 121 is used to increase the contact area between the outer wall surface of the bracket main body 10 and the engine equipment, thereby improving the connection stability between the engine equipment and the bracket main body 10.

[0032] In addition, in the embodiment of the present application, the equipment mounting surface 121 and the first reinforcing rib 12 are integrally formed, avoiding the generation of solder joints at the connection between the equipment mounting surface 121 and the first reinforcing rib 12, eliminating the stress concentration points of the split assembly, and ensuring the installation stability of the engine equipment.

[0033] Optionally, the width of the first reinforcing rib 12 provided with the equipment mounting surface 121 can be appropriately widened, and the widths of the remaining first reinforcing ribs 12 can remain unchanged, so as to further ensure the connection stability between the engine equipment and the bracket main body 10 and minimize the increase in the weight of the bracket main body 10 as much as possible.

[0034] Optionally, the through hole 11 includes two first through holes 111 and a plurality of second through holes 112. The width of the first through hole 111 is greater than the width of the second through hole 112, so as to facilitate the swing hose of the servo swing mechanism to pass through the first through hole 111. The two first through holes 111 are symmetrically arranged with respect to the first plane, optimizing the layout of the swing hose of the servo swing mechanism.

[0035] It should be noted here that the first plane is coplanar with the axis of the bracket main body 10 and perpendicular to the first end 101 of the bracket main body 10.

[0036] Optionally, the mounting bracket 20 and the equipment mounting surface 121 are distributed on both sides of the two through holes 11. Specifically, assuming there is a second plane, the second plane is coplanar with the axis of the bracket main body 10 and perpendicular to the first plane. The mounting bracket 20 and the equipment mounting surface 121 are distributed on the bracket main body 10 on both sides of the second plane, that is, the mounting bracket 20 and the equipment mounting surface 121 are oppositely arranged with respect to the second plane.

[0037] In the embodiment of the present application, by reasonably arranging the positions of the mounting bracket 20, the servo swing mechanism, the swing hose and the engine equipment, the layout of the servo swing mechanism, the secondary rocket engine and the engine equipment is made more compact, so as to optimize the internal layout of the launch vehicle and reduce the volume of the launch vehicle.

[0038] Optionally, referring to Figures 3-4 , in another parallel embodiment, the bracket main body 10 is in the shape of a table with the first end 101 closed and the second end 102 open. The difference between the embodiment of the present application and the above embodiment is that: the bracket main body 10 is in a ring-shaped hollow structure, that is, the bracket main body 10 includes a plurality of support rings 40 arranged at intervals in the height direction. The plurality of support rings 40 are connected and fixed by a plurality of third reinforcing ribs 50 extending along the generatrix of the bracket main body 10, and the plurality of third reinforcing ribs 50 are arranged at intervals around the circumference of the bracket main body. The swing hose of the servo swing mechanism extends out from the gap between two adjacent support rings 40.

[0039] Another alternative structural form is designed for the support body 10 in the embodiments of the present application. The annular layout of the support body 10 is more effective in withstanding pressure or dispersing loads, reducing the possibility of stress concentration. Therefore, the stress on the outer wall surface of the support body 10 is evenly distributed, thereby improving the support strength of the support body 10 and reducing the probability of deformation of the support body 10. Integrating the engine equipment, the secondary rocket engine, and the servo swing mechanism on the support body 10 can optimize the spatial layout inside the launch vehicle.

[0040] Optionally, referring to Figure 4 , in order to further enhance the strength of the support body 10 in the embodiments of the present application, a gradient design can also be selected for the thickness of the support ring. That is, the thickness of the inner side of the support ring 40 can be designed to be less than the thickness of the outer side of the support ring 40, and the thickness transition region adopts a curvature transition.

[0041] It should be noted here that the inner side of the support ring 40 refers to the side of the support ring 40 close to the hollow inside of the support body 10, and the inner side of the support ring 40 mainly undertakes the functions of vibration transmission and local stress dispersion. The outer side of the support ring 40 refers to the outer wall surface of the support body 10, that is, the side where the equipment mounting surface 121 and the mounting bracket 20 are provided, which is the key area for bearing the main load (such as engine thrust).

[0042] By setting the thickness of the inner side of the support ring 40 to be less than that of the outer side, not only can the weight of the support body 10 be reduced, but also the load on the equipment mounting surface 121 can be increased by increasing the thickness of the outer side of the support ring 40, and the vibration energy can be reduced by reducing the thickness of the inner side of the support ring 40, thereby further improving the strength of the support body 10.

[0043] Optionally, referring to Figure 1 , the mounting bracket 20 includes two mounting bracket 20 bodies symmetrically arranged with respect to the first plane and mounting lugs 22 respectively provided at the first ends 101 of the two mounting bracket 20 bodies. The first ends 101 of the mounting bracket 20 bodies are arranged parallel to the first end 101 of the support body 10, and the two mounting lugs 22 are used for mounting the servo swing mechanism.

[0044] It should be noted here that the space formed between the two mounting lugs 22 forms a mounting space for mounting the servo swing mechanism.

[0045] Optionally, the servo swing mechanism is connected to the mounting lug 22 by bolts to achieve detachable connection with the support body 10.

[0046] Optionally, referring to Figure 1, the main body of the mounting bracket 20 includes a connecting rib 211, a first leg 212, a second leg 213, and a mounting seat 214. The connecting rib 211 extends along the outer wall surface of the bracket main body 10. One end of each of the first leg 212 and the second leg 213 is mounted on the second end 102 of the bracket main body 10. The other ends of the first leg 212 and the second leg 213 are connected to the connecting rib 211 through the mounting seat 214, and the mounting seat 214 is arranged in parallel with the first end 101 of the bracket main body 10.

[0047] In the embodiment of the present application, by providing the connecting rib 211 extending along the outer wall surface of the bracket main body 10 and connecting the first leg 212 and the second leg 213 to the connecting rib 211, the support strength of the bracket main body 10 for the mounting bracket 20 and the servo swing mechanism can be enhanced, thereby improving the anti-deformation ability of the bracket main body 10.

[0048] By designing the structure of the main body of the mounting bracket 20, gaps exist between the first leg 212 and the second leg 213, between the first leg 212 and the connecting rib 211, and between the second leg 213 and the connecting rib 211, so that the volume and weight of the main body of the mounting bracket 20 are reduced, thereby reducing the weight of the engine bracket of the present application and further reducing the overall weight of the launch vehicle.

[0049] Optionally, an included angle is formed between each two of the first leg 212, the second leg 213, and the connecting rib 211, and the mounting lug 22 is integrally formed with the main body of the mounting bracket 20.

[0050] In the embodiment of the present application, an included angle is formed between the first leg 212 and the second leg 213, and it is set that from the end close to the second end 102 of the bracket main body 10 to the end far from the second end 102 of the bracket main body 10, the distance between the first leg 212 and the second leg 213 gradually decreases. The first leg 212, the second leg 213, and the mounting seat 214 form a pyramid structure, so that the support stability of the first leg 212 and the second leg 213 for the mounting seat 214 is further improved.

[0051] Optionally, referring to Figure 2 , the engine bracket further includes a radial reinforcing member arranged inside the space enclosed by the bracket main body 10. The radial reinforcing member is used to improve the support strength and bending stiffness of the bracket main body 10 and reduce the probability of deformation of the bracket main body 10.

[0052] In an optional embodiment, the radial reinforcing member includes at least two second reinforcing ribs 30. At least two second reinforcing ribs 30 are arranged inside the space enclosed by the bracket main body 10, and at least two second reinforcing ribs 30 are cross-arranged. Both ends of each second reinforcing rib 30 abut against the inner wall surface of the bracket main body 10.

[0053] By arranging at least two second reinforcing ribs 30 inside the space enclosed by the bracket main body 10 and abutting both ends of the second reinforcing ribs 30 against the inner wall surface of the bracket main body 10, the concentrated load generated by the engine thrust is dispersed along the second reinforcing ribs 30 to the bracket main body 10, reducing the probability of deformation of the bracket main body 10 under the impact of the thrust of the second-stage rocket engine. Arranging at least two second reinforcing ribs 30 in a cross pattern can further improve the geometric stability of the second reinforcing ribs 30 and enhance the flexural stiffness of the second reinforcing ribs 30 and the bracket main body 10.

[0054] Optionally, referring to Figure 2 , when the number of the second reinforcing ribs 30 is two, the two second reinforcing ribs 30 are arranged in a cross pattern. This application only takes the case where the number of the second reinforcing ribs 30 is two and the two second reinforcing ribs 30 are arranged in a cross pattern as an example for illustration Optionally, when the number of the second reinforcing ribs 30 is greater than two, the multiple second reinforcing ribs 30 are arranged in a cross-shaped network to form a cross-shaped network structure.

[0055] The cross-shaped network structure generally refers to a grid-like structure formed by multiple lines or components intersecting and connecting in different directions. The cross-shaped network structure can be used to reduce weight while improving the flexural and compressive resistance of the structure.

[0056] Optionally, the cross-shaped network structure formed by multiple second reinforcing ribs 30 can form a uniform network structure, that is, the mesh sizes and mesh densities at all positions in the cross-shaped network structure are the same, so that the forces at all positions of the bracket main body 10 are more uniform; it can also be a non-uniform structure. It can be that under the premise that the mesh densities at all positions are the same, the mesh sizes at some positions are larger and the mesh sizes at some positions are smaller, or under the premise that the mesh sizes are the same, the mesh densities at some positions are larger and the mesh densities at some positions are smaller. Thus, the shape of the second reinforcing ribs 30 can be reasonably arranged according to the force relationship between the mounting frame 20, the servo swing mechanism, and the engine equipment, so that the bracket main body 10 obtains better load-bearing performance.

[0057] Optionally, the cross-shaped structure or cross-shaped network structure formed by the second reinforcing ribs 30 can be coplanar or non-coplanar. When the cross-shaped structure or cross-shaped network structure formed by the second reinforcing ribs 30 is coplanar, the plane formed by the cross-shaped structure or cross-shaped network structure formed by the second reinforcing ribs 30 can be perpendicular to the first plane or the second plane, or can form an angle with the first plane or the second plane.

[0058] Optionally, the second reinforcing ribs 30 are arranged at one end of the bracket main body 10 close to the first end 101. Thus, the support strength of the second reinforcing ribs 30 for the bracket main body 10 is further improved.

[0059] Optionally, in another parallel embodiment, the radial reinforcement member includes a plate body provided with a plurality of holes, and the plate body is arranged at one end of the bracket main body 10 close to the first end 101.

[0060] Optionally, the plurality of holes are uniformly distributed on the plate body, and the shape of the holes can be square, circular, regular hexagon, etc., which is not limited herein. Thus, the connection between the radial reinforcement member and the bracket main body 10 is a surface connection, increasing the contact area between the radial reinforcement member and the bracket main body 10, thereby further improving the support strength of the bracket main body 10 and enhancing the support strength and bending stiffness of the engine bracket of the present application.

[0061] Optionally, the engine bracket is an integrally formed structure made of aluminum alloy material.

[0062] In the embodiment of the present application, by using lightweight aluminum alloy to replace traditional steel, the weight of the engine bracket of the present application is lighter, thereby reducing the overall weight of the launch vehicle. The use of the integral casting process to achieve integral molding of parts eliminates the need for welding or bolt connection, simplifies the manufacturing process, improves manufacturing efficiency, and saves manufacturing costs.

[0063] Based on the same inventive concept, referring to Figure 5 , the embodiment of the present application further provides a launch vehicle, including a propellant tank 60, a second-stage rocket engine, and the engine bracket of the above embodiment.

[0064] The bottom of the propellant tank 60 is in a frustum shape, and an installation interface 80 is provided at the bottom of the propellant tank 60. The installation interface 80 is detachably connected to the second end 102 of the engine bracket. The second-stage rocket engine is arranged at the first end 101 of the engine bracket, and the propellant tank 60, the engine bracket, and the second-stage rocket engine are coaxially arranged.

[0065] In the embodiment of the present application, the bottom of both the engine bracket and the propellant tank 60 is in a frustum shape. The engine bracket is detachably connected to the bottom of the propellant tank 60 through the installation interface 80. Compared with the form in the related art where the engine bracket is installed on the secondary rocket body end frame 70 outside the propellant tank 60, the diameter of the two end faces of the engine bracket is reduced, thereby reducing the volume and weight of the engine bracket and being able to reduce the overall volume and weight of the launch vehicle.

[0066] Optionally, the installation interface 80 is arranged circumferentially around the propellant tank 60 to ensure the stable connection between the engine bracket and the propellant tank.

[0067] Optionally, in an alternative embodiment, the installation interface 80 can be a connection seat with bolt mounting holes reserved. Using bolts to detachably connect the engine bracket and the connection seat can quickly achieve the detachable connection between the engine bracket and the propellant tank 60.

[0068] The beneficial technical effects brought by the technical solution provided in the embodiment of the present application include: Design an engine bracket that can be set at the bottom of the propellant tank 60, and the second-stage rocket engine can be installed at one end far from the propellant tank 60 through this engine bracket. Compared with the form in the related art where the engine bracket is installed on the end frame 70 of the second-stage rocket body surrounding the propellant tank 60, the diameter of at least one end face of the engine bracket can be reduced, thereby reducing the volume and weight of the engine bracket; Integrate the engine equipment, the servo swing mechanism of the second-stage rocket engine, and the second-stage rocket engine together on the bracket main body 10, which can make the layout inside the launch vehicle more compact; The bracket main body 10 adopts a table-like structure, and the servo swing mechanism and the engine equipment are installed on the outer wall surface of the bracket main body 10. On the premise of ensuring sufficient installation space for the servo swing mechanism and the engine equipment, the volume and weight of the bracket main body 10 are reduced, which is beneficial to reducing the overall volume and weight of the launch vehicle.

[0069] Arrange radial strengthening members in the space enclosed inside the bracket main body 10, which is beneficial to reducing the probability of deformation of the bracket main body 10 during the flight of the launch vehicle, and enhancing the bending stiffness and anti-deformation ability of the bracket main body 10.

[0070] In the description of the present application, the directions or positional relationships indicated by words such as "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are based on the exemplary directions or positional relationships shown in the drawings, and are for the convenience of describing or simplifying the embodiments of the present application, rather than indicating or implying that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore cannot be construed as a limitation of the present application.

[0071] The terms "first" and "second" are only used for descriptive purposes, and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present application, unless otherwise stated, the meaning of "a plurality" is two or more.

[0072] In the description of the present application, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", and "coupled" shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be directly connected, or indirectly connected through an intermediate medium, and it may be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0073] In the description of this specification, specific features, structures, materials, or characteristics may be combined in any one or more embodiments or examples in a suitable manner.

[0074] The above are only some implementation manners of the present application. It should be noted that for those of ordinary skill in the art, without departing from the technical concept of the present application, other similar implementation means based on the technical idea of the present application also belong to the protection scope of the embodiments of the present application.

Claims

1. An engine mount, characterized in that, Applied to a launch vehicle, including: A bracket main body, in a shape of a truncated cone with a closed first end and an open second end, the diameter of the first end of the bracket main body being smaller than that of the second end; the first end of the bracket main body has an engine mounting surface for connecting to a second-stage rocket engine, the second end of the bracket main body is used for connecting to the bottom of the propellant tank, and the outer wall surface of the bracket main body is used for mounting engine equipment; A mounting frame, arranged on the outer wall surface of the bracket main body, for detachably connecting to the servo swing mechanism of the second-stage rocket engine.

2. The engine mount according to claim 1, wherein, A plurality of groups of through holes are arranged at intervals around the circumference of the bracket main body, and the plurality of through holes in each group of through holes extend along the generatrix direction of the bracket main body.

3. The engine mount according to claim 2, wherein, A first reinforcing rib extending along the generatrix of the bracket main body is arranged between two adjacent through holes; At least two of the first reinforcing ribs are integrally formed with an equipment mounting surface, and the equipment mounting surface is used for mounting the engine equipment.

4. The engine mount according to claim 2, characterized in that, The through holes include two first through holes and a plurality of second through holes, the width of the first through hole is greater than that of the second through hole, the two first through holes are symmetrically arranged with respect to a first plane, the first plane is coplanar with the axis of the bracket main body and perpendicular to the first end of the bracket main body, and the mounting frame and the equipment mounting surface are distributed on both sides of the two through holes.

5. The engine mount according to claim 4, characterized in that, The mounting frame includes two mounting frame main bodies symmetrically arranged with respect to the first plane and mounting lugs respectively arranged at the first ends of the two mounting frame main bodies, the first ends of the mounting frame main bodies are arranged parallel to the first end of the bracket main body, and the two mounting lugs are used for mounting the servo swing mechanism.

6. The engine mount according to claim 5, characterized in that, The mounting frame main body includes: a connecting rib, a first leg, a second leg and a mounting seat; The connecting rib extends along the outer wall surface of the bracket main body; One ends of the first leg and the second leg are both mounted at the second end of the bracket main body, the other ends of the first leg and the second leg are connected to the connecting rib through the mounting seat, and the mounting seat is arranged parallel to the first end of the bracket main body; An included angle is formed between the first leg, the second leg and the connecting rib pairwise, and the mounting lug is integrally formed with the mounting frame main body.

7. The engine mount according to claim 1, wherein, It further includes: At least two second reinforcing ribs, arranged inside the space enclosed by the bracket main body, at least two of the second reinforcing ribs are cross-arranged, and both ends of each second reinforcing rib abut against the inner wall surface of the bracket main body.

8. The engine mount according to claim 7, characterized in that, At least two of the second reinforcing ribs are arranged at one end of the bracket main body close to the first end.

9. The engine mount according to claim 1, characterized in that, The engine bracket is an integrally formed structure made of aluminum alloy material.

10. A launch vehicle, characterized in that, Including a propellant tank, a second-stage rocket engine and the engine bracket according to any one of claims 1-9; The bottom of the propellant tank is in a shape of a truncated cone, and an installation interface is arranged at the bottom of the propellant tank, and the installation interface is detachably connected to the second end of the engine bracket; The second-stage rocket engine is arranged at the first end of the engine bracket, and the propellant tank, the engine bracket and the second-stage rocket engine are coaxially arranged.

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