A multi-engine parallel force transmission structure for a launch vehicle

Abstract

The present invention discloses a multi-engine parallel force transmission structure for a carrier rocket, which belongs to the technical field of spacecraft structure design, and includes a main bearing skin, a force transmission bracket and a gimbal; the main bearing skin is a circular ring structure; the force transmission bracket is fixed inside the main bearing skin, and is used to transmit the thrust of the engine to the rocket body; the force transmission bracket includes a first force transmission component radially arranged along the main bearing skin and a second force transmission component inclined relative to the radial plane of the main bearing skin; the gimbal seat and the second force transmission component are respectively arranged on both sides of the first force transmission component, and the gimbal seat is fixedly connected to the first force transmission component; the gimbal seat includes a central gimbal seat and a plurality of outer gimbal seats; the center of the central gimbal seat is located on the axis of the main bearing skin; and the plurality of outer gimbal seats are evenly distributed on a circle centered on the central gimbal seat. The present invention can realize multi-engine parallel connection while greatly reducing the structural weight and effectively improving the carrying capacity of the rocket.

Description

Technical Field

[0001] The invention relates to the technical field of spacecraft structure design, and in particular to a multi-engine parallel force transmission structure for a carrier rocket. Background Art

[0002] In order to increase the carrying capacity of launch vehicles, multiple machines are usually connected in parallel to increase thrust. Therefore, the multi-machine parallel force transmission structure is one of the key components of large launch vehicles.

[0003] At present, the force transmission structure of the liquid rocket engine is heavy, and the thrust transmission path and structural form are relatively simple. The application number is 202311671297.X, and the name is a rocket compartment multi-engine parallel engine force transmission system, in which the engine and the rear transition section are designed independently, that is, the multi-engine parallel force transmission structure is installed in the rocket rear transition section, and the engine thrust passes through the thrust chamber to the gimbal, and then to the engine frame, and finally acts on the multi-engine parallel structure. This design method can decouple the engine design from the rear transition section design, and only needs to ensure the interface coordination between the two.

[0004] However, under the condition of a certain engine thrust, the dry weight of the rocket is one of the key factors restricting the carrying capacity. In order to increase the carrying capacity, it is necessary to reduce the structural weight as much as possible. The coupling design between the engine and the rear transition section is one of the directions to reduce weight.

[0005] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0006] In order to solve the above-mentioned technical problems, the present application provides a multi-engine parallel force transmission structure for a launch vehicle, which can realize multi-engine parallel connection while greatly reducing the structural weight and effectively improving the carrying capacity of the rocket.

[0007] A launch vehicle multi-engine parallel force transmission structure, comprising:

[0008] Main load-bearing skin; the main load-bearing skin is a ring-shaped structure;

[0009] A force transmission bracket; the force transmission bracket is fixed inside the main bearing skin and is used to transmit the thrust of the engine to the rocket body; the force transmission bracket includes a first force transmission component arranged along the radial direction of the main bearing skin and a second force transmission component arranged obliquely relative to the radial plane of the main bearing skin;

[0010] A gimbal; the gimbal and the second force transmission component are respectively arranged on both sides of the first force transmission component, and the gimbal is fixedly connected to the first force transmission component; the gimbal includes a central gimbal and a plurality of outer gimbals; the center of the central gimbal is located on the axis of the main bearing skin; the plurality of outer gimbals are evenly distributed on a circle centered on the central gimbal.

[0011] Preferably, the first force transmission component comprises a plurality of Y-shaped frames; the plurality of Y-shaped frames are evenly distributed on a circle centered on the axis of the main load-bearing skin; one end of the Y-shaped frame having an opening is fixedly connected relative to the inner wall of the main load-bearing skin, and the non-opening end of the Y-shaped frame is fixedly connected to the central gimbal;

[0012] The second force transmission component includes an oblique support rod; the oblique support rod is obliquely arranged at the upper part of the Y-shaped frame; the Y-shaped frame and the oblique support rod are the same in number and their positions correspond one to one; one end of the oblique support rod close to the axis of the main bearing skin is fixedly connected to the upper part of the Y-shaped frame, and one end of the oblique support rod away from the axis of the main bearing skin is fixedly connected to the main bearing skin.

[0013] Preferably, the first force transmission component also includes a plurality of outer ring annular reinforcement ribs forming a regular polygon or a circle; the outer ring annular reinforcement ribs and the Y-shaped frame are located on the same plane; the outer ring annular reinforcement ribs are fixedly arranged between adjacent Y-shaped frames; the center of the regular polygon or circle formed by the plurality of outer ring annular reinforcement ribs is located on the axis of the main load-bearing skin; the outer ring annular reinforcement ribs are fixedly connected to the connection nodes of the Y-shaped frame.

[0014] Preferably, the external gimbal is fixedly connected to the bottom of the Y-shaped frame at the connection node of the Y-shaped frame.

[0015] Preferably, the first force transmission component also includes a plurality of inner ring annular reinforcement ribs forming a regular polygon or a circle; the inner ring annular reinforcement ribs and the Y-shaped frame are located on the same plane; the inner ring annular reinforcement ribs are fixed between adjacent Y-shaped frames; the center of the regular polygon or circle formed by the inner ring annular reinforcement ribs is located on the axis of the main load-bearing skin.

[0016] Preferably, the launch vehicle multi-engine parallel force transmission structure also includes a reinforced skin; the reinforced skin is fixed on the inner wall of the main load-bearing skin, and its position corresponds to the position of the Y-shaped frame.

[0017] Preferably, the multi-engine parallel force transmission structure of the launch vehicle also includes a plurality of stringers arranged parallel to the axial direction of the main load-bearing skin; the stringers are fixedly connected to the outer side wall of the main load-bearing skin; the stringers include weak stringers and strong stringers; the strong stringers are fixed to the outer side wall of the main load-bearing skin corresponding to the reinforced skin; the weak stringers are fixed to the outer side wall of the main load-bearing skin not covered by the strong stringers.

[0018] Preferably, the Y-shaped frame includes an inner end arc plate, an outer end arc plate, a support bottom plate and a support top plate; the inner end arc plate is vertically arranged and fixedly connected to the side surface of the center gimbal; the outer end arc plate is vertically arranged and fixedly connected to the inner wall of the reinforced skin; the support bottom plate is a Y-shaped flat plate structure; one end of the support bottom plate is fixedly connected to the outer side wall of the inner end arc plate, and the other end of the support bottom plate is fixedly connected to the inner side wall of the outer end arc plate; the support top plate is a Y-shaped bent plate structure; one end of the support top plate is fixedly connected to the outer side wall of the inner end arc plate, and the other end of the support top plate is fixedly connected to the inner side wall of the outer end arc plate; the inner end arc plate, the outer end arc plate, the support bottom plate and the support top plate are combined to form a frame structure with side through-holes.

[0019] Preferably, the supporting top plate includes a first supporting flat plate, a first supporting inclined plate, a second supporting inclined plate and a second supporting flat plate which are fixedly connected in sequence; the first supporting flat plate and the second supporting flat plate are arranged parallel to each other; the acute angle of the first supporting inclined plate relative to the first supporting flat plate is greater than the acute angle of the second supporting inclined plate relative to the first supporting flat plate.

[0020] Preferably, the Y-shaped frame further comprises a support leg side upright plate arranged at the opening of the Y-shaped frame; the upper portion of the support leg side upright plate is fixedly connected to the support top plate; and the lower portion of the support leg side upright plate is fixedly connected to the support bottom plate.

[0021] Compared with the prior art, this application has at least the following beneficial effects:

[0022] 1. In the present invention, the engine frame and the engine gimbal are combined into one, and the engine does not need an extra frame, which can greatly reduce the structural weight and effectively improve the carrying capacity of the rocket.

[0023] 2. The present invention adopts a Y-shaped frame for support and force transmission, which can further effectively reduce the weight of the structure. At the same time, the Y-shaped frame is connected to the main load-bearing skin at its open end, which can increase the connection area and facilitate the rapid diffusion of the concentrated force of the engine to the bulkhead.

[0024] 3. The Y-shaped frame of the present invention adopts a variable cross-section design, which can ensure the load-bearing capacity while further reducing the structural weight.

[0025] 4. The present invention adopts a structural solution of alternately installing weak beams and strong beams, which is beneficial to the transmission of axial loads and the diffusion of axial forces, and can reduce the weight of the structure while ensuring the axial load. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale. In the accompanying drawings:

[0027] Figure 1 It is a schematic diagram of the three-dimensional structure of the multi-engine parallel force transmission structure of the carrier rocket of the present invention;

[0028] Figure 2 It is a bottom-up structural schematic diagram of the multi-engine parallel force transmission structure of the carrier rocket of the present invention;

[0029] Figure 3 for Figure 2 A partial enlarged view of position B in the middle;

[0030] Figure 4 It is a structural schematic diagram of the Y-shaped frame of the present invention;

[0031] Figure 5 for Figure 4 Cross-sectional view at the AA position.

[0032] The above drawings include the following reference numerals:

[0033] 1. Main load-bearing skin; 2. Weak girder; 3. Strong girder; 4. Reinforced skin; 5. Y-shaped frame; 6. Center gimbal; 7. Inner ring circumferential reinforcement ribs; 8. Outer ring circumferential reinforcement ribs; 9. Oblique support rods; 10. Outer gimbal; 51. Inner end arc plate; 52. Outer end arc plate; 53. Support bottom plate; 54. Support top plate; 55. Support leg side plates; 541. First support flat plate; 542. First support inclined plate; 543. Second support inclined plate; 544. Second support flat plate. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0035] Combine the following Figure 1-Figure 5Describing the launch vehicle multi-engine parallel force transmission structure of the present invention, it can be understood that the gimbals shown in the drawings of the present invention are 9 pieces, including 8 outer gimbals 10 and 1 central gimbal 6, which can achieve the fixation of 9 engines, that is, the parallel connection of 9 engines. Of course, according to the different rocket carrying capacity and the thrust of a single rocket engine, it can be designed according to the actual working conditions, and the gimbals can also be set to other numbers other than 9.

[0036] It should be noted that the carrier rocket multi-engine parallel force transmission structure of the present invention is applicable to a rocket with multiple engines in parallel, and is particularly applicable to a carrier rocket with a diameter of 4200 mm when the scheme has 8 outer gimbals 10 and 1 central gimbal 6. However, under the premise of satisfying the rocket carrying capacity, the technical solution of the present invention can also be applied to rockets with multiple engines in parallel of other sizes.

[0037] In addition, the launch vehicle multi-engine parallel force transmission structure of the present invention is particularly suitable for the parallel connection of multiple liquid rocket engines. Of course, under the premise of meeting the design requirements, the launch vehicle multi-engine parallel force transmission structure of the present invention can be applied to the parallel connection of multiple solid rocket engines.

[0038] As an embodiment of the present invention, a multi-engine parallel force transmission structure for a carrier rocket includes: a main load-bearing skin 1, a force transmission bracket and a gimbal. Among them, the main load-bearing skin 1 is a circular ring structure. The force transmission bracket is fixed inside the main load-bearing skin 1, and is used to transmit the thrust of the engine to the rocket body. The force transmission bracket includes a first force transmission component arranged radially along the main load-bearing skin 1 and a second force transmission component inclined at a certain angle relative to the radial plane of the main load-bearing skin 1. The gimbal and the second force transmission component are respectively arranged on both sides of the first force transmission component, and the gimbal is fixedly connected to the first force transmission component. The gimbal includes a Y-center gimbal 6 and a plurality of outer gimbals 10; the center of the Y-center gimbal 6 is located on the axis of the main load-bearing skin 1; and the plurality of outer gimbals 10 are evenly distributed on a circle centered on the Y-center gimbal 6.

[0039] Specifically, the first force transmission component includes a plurality of Y-shaped frames 5, the main part of the Y-shaped frame 5 is a "Y"-shaped structure, including a main body and two legs fixedly connected to the main body, the two legs form an opening, and the end is the opening end of the Y-shaped frame 5. The plurality of Y-shaped frames 5 are evenly distributed on a circle centered on the axis of the main bearing skin 1, one end of the Y-shaped frame 5 with an opening is fixedly connected relative to the inner wall of the main bearing skin 1, and the non-opening end of the Y-shaped frame 5 is fixedly connected to the Y-center gimbal 6.

[0040] The Y-shaped frame 5 adopts a Y-shaped design scheme, which can increase the connection area when its two legs are connected to the main load-bearing skin 1, so as to facilitate the rapid diffusion of the concentrated force of the engine to the bulkhead.

[0041] The second force transmission component includes an oblique support rod 9. The oblique support rod 9 is obliquely arranged at the upper part of the Y-shaped frame 5, and the Y-shaped frame 5 is the same as the number of the oblique support rods 9 and the positions correspond one to one. That is to say, in the present embodiment, each oblique support rod 9 corresponds to one Y-shaped frame 5, and in the axial direction of the rocket, each oblique support rod 9 is arranged above the Y-shaped frame 5 corresponding thereto. Specifically, one end of the oblique support rod 9 close to the axis of the main bearing skin 1 is fixedly connected to the upper part of the Y-shaped frame 5, and one end of the oblique support rod 9 away from the axis of the main bearing skin 1 is fixedly connected to the main bearing skin 1.

[0042] As another embodiment of the present invention, the first force transmission component also includes a plurality of outer ring annular reinforcement ribs 8 forming a regular polygon or a circle; the outer ring annular reinforcement ribs 8 and the Y-shaped frame 5 are located on the same plane; the outer ring annular reinforcement ribs 8 are fixedly arranged between adjacent Y-shaped frames 5; the center of the regular polygon or circle formed by the plurality of outer ring annular reinforcement ribs 8 is located on the axis of the main load-bearing skin 1; the outer ring annular reinforcement ribs 8 are fixedly connected to the connection nodes of the Y-shaped frame 5.

[0043] The manner in which the outer ring annular reinforcement ribs 8 are fixedly connected to the connection nodes of the Y-shaped frame 5 can effectively improve the structural strength of the first force transmission component, especially the structural strength of the connection nodes of the Y-shaped frame 5. When the outer ring annular reinforcement ribs 8 form a regular polygonal or circular structure, the forces between the Y-shaped frames 5 can be more balanced, and deformation or damage of a single Y-shaped frame 5 due to excessive force can be avoided.

[0044] Preferably, the outer gimbal 10 is fixedly connected to the lower part of the Y-shaped frame 5 at the connection node of the Y-shaped frame 5. The outer gimbal 10 and the Y-shaped frame 5 are directly fixedly connected, so that the engine frame and the engine gimbal can be combined into one, and the engine does not need an extra frame, which can greatly reduce the structural weight and effectively improve the carrying capacity of the rocket.

[0045] As another embodiment of the present invention, the first force transmission component further includes a plurality of inner ring annular reinforcement ribs 7 forming a regular polygon or a circle; the inner ring annular reinforcement ribs 7 and the Y-shaped frame 5 are located on the same plane; the inner ring annular reinforcement ribs 7 are fixedly arranged between adjacent Y-shaped frames 5; the center of the regular polygon or circle formed by the inner ring annular reinforcement ribs 7 is located on the axis of the main bearing skin 1. The inner ring annular reinforcement ribs 7 are arranged inside the regular polygon or circle formed by the outer ring annular reinforcement ribs 8.

[0046] Similarly, the arrangement of the inner ring annular reinforcement ribs 7 can effectively improve the structural strength of the first force transmission component. At the same time, when the inner ring annular reinforcement ribs 7 form a regular polygon or circular structure, the forces between the Y-shaped frames 5 can be more balanced, thereby preventing a single Y-shaped frame 5 from being deformed or damaged due to excessive force.

[0047] As another embodiment of the present invention, the multi-engine parallel force transmission structure of the carrier rocket also includes a reinforced skin 4, which is fixedly arranged on the inner side wall of the main load-bearing skin 1, and its position corresponds to the position of the Y-frame 5. It should be noted that the position of the reinforced skin 4 corresponding to the Y-frame 5 is actually corresponding to one end of the Y-frame 5 with an opening. Specifically, the specific size of the reinforced skin 4 can be calculated according to the design requirements of the rocket, and it can be arranged between the Y-frame 5 and the main load-bearing skin 1, and the Y-frame 5 is fixedly connected to the inner side wall of the reinforced skin 4, and the reinforced skin 4 is fixedly connected to the inner side wall of the main load-bearing skin 1. In addition, the Y-frame 5 can also be fixedly connected to the inner side wall of the main load-bearing skin 1, and the reinforced skin 4 is fixedly arranged in the inner side wall region of the main load-bearing skin 1 not covered by the Y-frame 5, so as to improve the structural strength.

[0048] As another embodiment of the present invention, the multi-engine parallel force transmission structure of the carrier rocket also includes a plurality of stringers axially arranged parallel to the main load-bearing skin 1, and the stringers are fixedly connected to the outer side wall of the main load-bearing skin 1. The stringers include weak stringers 2 and strong stringers 3, and the strong stringers 3 are fixedly arranged on the outer side wall of the main load-bearing skin 1 corresponding to the reinforced skin 4; the weak stringers 2 are fixedly arranged on the outer side wall of the main load-bearing skin 1 not covered by the strong stringers 3. It should be noted that the structural strength of the strong stringers 3 is greater than that of the weak stringers 2. From the specific structure, the width of the strong stringers 3 is greater than that of the weak stringers 2 or the thickness of the strong stringers 3 is greater than that of the weak stringers 2. The structural scheme of alternately installing the weak stringers 2 and the strong stringers 3 adopted in the present invention can ensure the axial load of the rocket while reducing the structural weight.

[0049] As another embodiment of the present invention, the Y-shaped frame 5 includes an inner end arc plate 51, an outer end arc plate 52, a support bottom plate 53 and a support top plate 54; the inner end arc plate 51 is vertically arranged and fixedly connected to the side of the Y center gimbal 6; the outer end arc plate 52 is vertically arranged and fixedly connected to the inner side wall of the reinforced skin 4; the support bottom plate 53 is a Y-shaped flat plate structure; one end of the support bottom plate 53 is fixedly connected to the outer side wall of the inner end arc plate 51, and the other end of the support bottom plate 53 is fixedly connected to the inner side wall of the outer end arc plate 52; the support top plate 54 is a Y-shaped bending plate structure; one end of the support top plate 54 is fixedly connected to the outer side wall of the inner end arc plate 51, and the other end of the support top plate 54 is fixedly connected to the inner side wall of the outer end arc plate 52; the inner end arc plate 51, the outer end arc plate 52, the support bottom plate 53 and the support top plate 54 are surrounded by a frame structure with side penetration. The frame-shaped structure of the Y-shaped frame 5 can effectively reduce the weight while ensuring the structural strength, so that the rocket has a higher carrying capacity. The Y-shaped frame 5 is formed by welding plates, which can effectively reduce the manufacturing cost.

[0050] Preferably, the support top plate 54 includes a first support flat plate 541, a first support inclined plate 542, a second support inclined plate 543 and a second support flat plate 544 which are fixedly connected in sequence; the first support flat plate 541 and the second support flat plate 544 are arranged parallel to each other; the acute angle of the first support inclined plate 542 relative to the first support flat plate 541 is greater than the acute angle of the second support inclined plate 543 relative to the first support flat plate 541. The Y-shaped frame 5 adopts a variable cross-section design, which can further ensure the load-bearing capacity while reducing the structural weight.

[0051] As another embodiment of the present invention, the Y-shaped frame 5 may not include the inner end arc plate 51 and the outer end arc plate 52, but the two ends of the support bottom plate 53 and the support top plate 54 are respectively fixedly connected to the central gimbal 6 and the main bearing skin 1, so as to realize the support and force transmission function of the Y-shaped frame 5.

[0052] As another embodiment of the present invention, the Y-shaped frame 5 further includes a leg side vertical plate 55 disposed at the opening of the Y-shaped frame 5; the upper portion of the leg side vertical plate 55 is fixedly connected to the support top plate 54; and the lower portion of the leg side vertical plate 55 is fixedly connected to the support bottom plate 53. It should be noted that the cross-sectional structure of the leg side vertical plate 55 is adapted to the structure of the support bottom plate 53 and the support top plate 54, so that it can be fixedly connected to the edges of the support bottom plate 53 and the support top plate 54. The leg side vertical plate 55 can connect and support the support bottom plate 53 and the support top plate 54 at the open end of the Y-shaped frame 5, effectively improving the structural strength of the Y-shaped frame 5.

[0053] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0054] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0055] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0056] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A multi-engine parallel force transmission structure for a launch vehicle, comprising a main bearing skin, a force transmission bracket and a gimbal; characterized in that: The main load-bearing skin is a ring-shaped structure; The force transmission bracket is fixed inside the main bearing skin and is used to transmit the thrust of the engine to the rocket body; the force transmission bracket includes a first force transmission component arranged along the radial direction of the main bearing skin and a second force transmission component arranged obliquely relative to the radial plane of the main bearing skin; The gimbal and the second force transmission component are respectively arranged on both sides of the first force transmission component, and the gimbal is fixedly connected to the first force transmission component; the gimbal comprises a central gimbal and a plurality of outer gimbals; the center of the central gimbal is located on the axis of the main bearing skin; the plurality of outer gimbals are evenly distributed on a circle centered on the central gimbal; The first force transmission component includes a plurality of Y-shaped frames; the plurality of Y-shaped frames are evenly distributed on a circle centered on the axis of the main load-bearing skin; one end of the Y-shaped frame with an opening is fixedly connected relative to the inner wall of the main load-bearing skin, and the non-opening end of the Y-shaped frame is fixedly connected to the central gimbal; The second force transmission component comprises an oblique support rod; the oblique support rod is obliquely arranged at the upper part of the Y-shaped frame; the Y-shaped frame has the same number as the oblique support rods and their positions correspond one to one; one end of the oblique support rod close to the axis of the main bearing skin is fixedly connected to the upper part of the Y-shaped frame, and one end of the oblique support rod far from the axis of the main bearing skin is fixedly connected to the main bearing skin; The carrier rocket multi-engine parallel force transmission structure also includes a reinforced skin; the reinforced skin is fixedly arranged on the inner side wall of the main bearing skin, and its position corresponds to the position of the Y-shaped frame; The Y-shaped frame includes an inner end arc plate, an outer end arc plate, a support bottom plate and a support top plate; the inner end arc plate is vertically arranged and fixedly connected to the side of the central gimbal; the outer end arc plate is vertically arranged and fixedly connected to the inner wall of the reinforced skin; the support bottom plate is a Y-shaped flat plate structure; one end of the support bottom plate is fixedly connected to the outer side wall of the inner end arc plate, and the other end of the support bottom plate is fixedly connected to the inner side wall of the outer end arc plate; the support top plate is a Y-shaped bent plate structure; one end of the support top plate is fixedly connected to the outer side wall of the inner end arc plate, and the other end of the support top plate is fixedly connected to the inner side wall of the outer end arc plate; the inner end arc plate, the outer end arc plate, the support bottom plate and the support top plate are combined to form a frame structure with side through-holes.

2. The launch vehicle multi-engine parallel force transmission structure according to claim 1, characterized in that: The first force transmission component also includes a plurality of outer ring annular reinforcement ribs forming a regular polygon or a circle; the outer ring annular reinforcement ribs and the Y-shaped frame are located on the same plane; the outer ring annular reinforcement ribs are fixedly arranged between adjacent Y-shaped frames; the center of the regular polygon or circle formed by the plurality of outer ring annular reinforcement ribs is located on the axis of the main load-bearing skin; the outer ring annular reinforcement ribs are fixedly connected to the connection nodes of the Y-shaped frame.

3. The launch vehicle multi-engine parallel force transmission structure according to claim 2, characterized in that: The external gimbal is fixedly connected to the bottom of the Y-shaped frame at the Y-shaped frame connection node.

4. The launch vehicle multi-engine parallel force transmission structure according to claim 3, characterized in that: The first force transmission component also includes a plurality of inner ring annular reinforcement ribs forming a regular polygon or a circle; the inner ring annular reinforcement ribs and the Y-shaped frame are located on the same plane; the inner ring annular reinforcement ribs are fixed between adjacent Y-shaped frames; the center of the regular polygon or circle formed by the inner ring annular reinforcement ribs is located on the axis of the main load-bearing skin.

5. The launch vehicle multi-engine parallel force transmission structure according to claim 1, characterized in that: The multi-engine parallel force transmission structure of the launch vehicle also includes a plurality of stringers arranged parallel to the axial direction of the main load-bearing skin; the stringers are fixedly connected to the outer side wall of the main load-bearing skin; the stringers include weak stringers and strong stringers; the strong stringers are fixed to the outer side wall of the main load-bearing skin corresponding to the reinforced skin; the weak stringers are fixed to the outer side wall of the main load-bearing skin not covered by the strong stringers.

6. The launch vehicle multi-engine parallel force transmission structure according to claim 5, characterized in that: The supporting top plate includes a first supporting flat plate, a first supporting inclined plate, a second supporting inclined plate and a second supporting flat plate which are fixedly connected in sequence; the first supporting flat plate and the second supporting flat plate are arranged parallel to each other; the acute angle of the first supporting inclined plate relative to the first supporting flat plate is greater than the acute angle of the second supporting inclined plate relative to the first supporting flat plate.

7. The launch vehicle multi-engine parallel force transmission structure according to claim 6, characterized in that: The Y-shaped frame also includes a support leg side vertical plate arranged at the opening of the Y-shaped frame; the upper portion of the support leg side vertical plate is fixedly connected to the support top plate; and the lower portion of the support leg side vertical plate is fixedly connected to the support bottom plate.

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