Communication satellite structure and carrier rocket

Abstract

The utility model provides a communication satellite structure and a carrier rocket, and relates to the technical field of satellites. The communication satellite structure provided by the utility model comprises box body plates, wherein the box body plates form a trapezoidal box body structure; the partition plates are arranged in the box body plate at intervals, and the partition plates and the inner wall of the box body plate form a single machine mounting surface; and the main bearing corner box is arranged at least one of the corner of the box body plate and the position between the partition plate and the box body plate. According to the invention, through the hollow trapezoidal box body structure formed by the box body plates, the communication satellite structure is light in weight, the space utilization rate is improved, and the number of the communication satellite structures which can be carried by a carrier rocket is increased, so that batch and large-scale launching of the communication satellite structures is realized; the overall rigidity and strength of the communication satellite structure are improved through the partition plates and the main bearing corner boxes, and meanwhile the area of a single-machine installation face is increased, so that satellite single-machine installation is facilitated.

Description

Technical Field

[0001] This application relates to the field of satellite technology, and particularly to a communication satellite structure and a launch vehicle. Background Art

[0002] To meet the air-ground communication requirements and the current development trend of constellation and networking of communication satellites at home and abroad. Taking the Starlink satellites in the United States and the Star Network constellation in China as examples, hundreds or even thousands of satellites with the same functions are required to complete the networking. Existing satellites usually have high manufacturing costs and large weights, making it difficult to achieve mass launch and production.

[0003] Therefore, a low-cost satellite structure that can achieve mass launch and manufacturing is particularly important. For the cost of satellite structures, it mainly includes launch weight cost and manufacturing cost. On the premise of meeting the mechanical performance of the whole satellite and the equipment installation requirements, minimizing the use of metal materials and adopting lightweight design of the structure system become the primary goal of batch satellite structure design. Utility Model Content

[0004] Based on this, this application provides a communication satellite structure and a launch vehicle, which can reduce the costs of launch and manufacturing and achieve lightweight mass launch and manufacturing.

[0005] A communication satellite structure provided by this application includes:

[0006] A box body plate, which forms a trapezoidal box body structure;

[0007] Partition boards, which are arranged at intervals inside the box body plate, and the partition boards and the inner walls of the box body plate form single-machine installation surfaces;

[0008] Main load-bearing angle boxes, which are arranged at least at the corners of the box body plate and between the partition boards and the box body plate;

[0009] At least one of the box body plate and the partition boards includes:

[0010] A honeycomb sandwich structure plate, which is provided with connecting members. The connecting members are connected between two adjacent honeycomb sandwich structure plates, and one end of the connecting member is buried inside the sandwich of the honeycomb sandwich structure plate.

[0011] Optionally, the box body plate includes longitudinal plates, transverse plates and vertical plates; among them,

[0012] The longitudinal plates include positive longitudinal plates and negative longitudinal plates, the positive longitudinal plates and the negative longitudinal plates are arranged oppositely and are respectively connected to the transverse plates and the vertical plates;

[0013] The transverse plates include positive transverse plates and negative transverse plates, and the positive transverse plates and the negative transverse plates are symmetrically and obliquely arranged on both sides of the vertical plate;

[0014] The vertical plates include positive vertical plates and negative vertical plates, which are arranged oppositely. The positive vertical plates and negative vertical plates are respectively connected to the longitudinal plates and transverse plates to form a trapezoidal box structure.

[0015] Optionally, the connecting member includes a first connecting device, and the first connecting device includes:

[0016] The first embedded parts are respectively arranged inside the vertical plates and longitudinal plates to improve the connection strength between the vertical plates and longitudinal plates;

[0017] The straight-edge hole sleeves are arranged on the vertical plates or longitudinal plates and are located at the positions of the first embedded parts;

[0018] One end of the first connecting piece is arranged inside the straight-edge hole sleeve, and the other end passes through the straight-edge hole sleeve to connect the adjacent vertical plate with the first embedded part inside the longitudinal plate.

[0019] Optionally, the connecting member includes a second connecting device, and the second connecting device includes:

[0020] The second embedded parts are respectively arranged inside the transverse plates and vertical plates to improve the connection strength between the vertical plates and longitudinal plates; 9]

[0021] The bevel-edge hole sleeves are arranged on the transverse plates and are located at the positions of the second embedded parts;

[0022] One end of the second bolt is arranged inside the bevel-edge hole sleeve, and the other end passes through the bevel-edge hole sleeve to connect the adjacent transverse plate with the second embedded part inside the vertical plate.

[0023] Optionally, the first embedded part or the second embedded part includes:

[0024] The embedded body is provided with a friction part with uneven surface, and the friction part is respectively attached to the inside of the honeycomb sandwich structure board;

[0025] The strengthening part is arranged on the embedded body, and the cross-section formed by the strengthening part and the embedded body is in the shape of an I.

[0026] Optionally, the communication satellite structure further includes a solar panel mounting part, which is arranged on the box body plate and is used for mounting solar panels, and includes:

[0027] The first connecting part is arranged on the box body plate, and the mounting surface of the first connecting part is attached to the box body plate;

[0028] The second connecting part is arranged at the center of the first connecting part at intervals and is provided with mounting holes; the mounting surface of the second connecting part intersects with the mounting surface of the first connecting part and forms an included angle;

[0029] The mounting part connecting pieces are respectively arranged on the mounting surfaces of the first connecting part and the second connecting part.

[0030] Optionally, the communication satellite structure further includes:

[0031] A connecting beam, disposed inside the box body plate, for enhancing the strength of the box body plate or the partition plate.

[0032] Optionally, the main load-bearing corner box includes a box body, reinforcing ribs, a weight-reducing mesh, and a corner box embedded part; wherein,

[0033] The box body is attached to at least one of the box body plate and the partition plate, and the box body is provided with buried holes that cooperate with the corner box embedded part;

[0034] The reinforcing ribs are disposed at the edges of the box body and are perpendicular to the edges of the box body;

[0035] The weight-reducing mesh is disposed on the box body and is located at the edge of the box body;

[0036] One end of the corner box embedded part is connected to the box body plate, and the other end is connected to the box body through the buried hole.

[0037] Optionally, the box body plate is provided with an equipment mounting rack, including: a rack body, a mounting reinforcing part, and a connecting reinforcing part; wherein, the rack body is disposed on the box body plate; the mounting reinforcing part is disposed on the rack body for mounting equipment; the connecting reinforcing part is disposed on the rack body for connecting two adjacent box body plates.

[0038] This application also provides a launch vehicle, including the above-mentioned communication satellite structure.

[0039] The communication satellite structure and the launch vehicle provided by this application form an internal hollow structure of a trapezoidal box structure through the box body plate, making the communication satellite structure lightweight. At the same time, multiple communication satellite structures are evenly distributed within the launch space envelope of the launch vehicle for launching satellites, improving space utilization rate and increasing the number of communication satellite structures that can be carried by the launch vehicle, which helps to achieve batch large-scale launch of communication satellite structures. By arranging partition plates inside the box body plate at intervals, the overall rigidity and strength of the communication satellite structure are increased, and at the same time, the area of the single-machine mounting surface is increased to facilitate the installation of satellite single machines; the main load-bearing corner box further increases the connection strength and connection area between the box body plate itself and between the partition plate and the box body plate. The box body plate and the partition plate reduce the overall mass of the communication satellite structure through the honeycomb sandwich structure plate, and adjacent box body plates and between the box body plate and the partition plate are connected through connecting members, and one end of the connecting member is buried inside the sandwich of the honeycomb sandwich structure plate to improve the connection strength and reliability. Description of the Drawings

[0040] To more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the accompanying drawings required for the description of the embodiments. Obviously, the accompanying drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other accompanying drawings can also be obtained based on these drawings without exceeding the scope of protection required by the present application.

[0041] Figure 1 is an exploded structural schematic diagram of the communication satellite structure provided by the present application;

[0042] Figure 2 is a structural schematic diagram of the communication satellite structure provided by the present application;

[0043] Figure 3 is a structural schematic diagram of the first connecting device in the communication satellite structure provided by the present application;

[0044] Figure 4 is a structural schematic diagram of the second connecting device in the communication satellite structure provided by the present application;

[0045] Figure 5 is a structural schematic diagram of the main load-bearing angle box in the communication satellite structure provided by the present application;

[0046] Figure 6 is a side structural schematic diagram of the communication satellite structure provided by the present application;

[0047] Figure 7 is a structural schematic diagram of the solar panel mounting part in the communication satellite structure provided by the present application;

[0048] Figure 8 is a structural schematic diagram of the bevel connecting embedded part in the communication satellite structure provided by the present application;

[0049] Figure 9 is a structural schematic diagram of the main load-bearing angle box in the communication satellite structure provided by the present application;

[0050] Figure 10 is a structural schematic diagram of the equipment mounting rack in the communication satellite structure provided by the present application.

[0051] Description of reference numerals: 1, box body plate; 11, longitudinal plate; 111, positive longitudinal plate; 112, negative longitudinal plate; 12, transverse plate; 121, positive transverse plate; 122, negative transverse plate; 13, vertical plate; 131, positive vertical plate; 132, negative vertical plate; 2, partition; 3, solar wing mounting part; 31, first connecting part; 32, second connecting part; 33, mounting part connecting piece; 4, main load-bearing angle box; 41, box body; 42, reinforcing rib; 43, weight-reducing mesh; 44, buried hole; 5, connecting member; 51, first connecting device; 511, first embedded part; 512, straight-edge hole sleeve; 513, first connecting piece; 52, second connecting device; 521, second embedded part; 522, bevel-edge hole sleeve; 523, second bolt; 6, connecting beam; 7, robotic arm mounting point; 8, equipment mounting rack; 81, rack body; 82, mounting reinforcing part; 83, connecting reinforcing part. Detailed implementation manners

[0052] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative efforts shall fall within the protection scope of the present application.

[0053] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be understood as a limitation to the present application. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, the features defined with "first", "second", etc. may explicitly or implicitly include one or more of the described features. In the description of the present application, the meaning of "a plurality" is two or more, unless otherwise specifically defined.

[0054] In the description of the present application, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", and "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection, an electrical connection, or a connection that allows for mutual communication; it may be directly connected, or indirectly connected through an intermediate medium, and it may be the internal communication between two components or the interaction relationship between 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.

[0055] In the present application, unless otherwise clearly specified and defined, the first feature being "on" or "under" the second feature may include the direct contact between the first and second features, or may include the situation where the first and second features are not in direct contact but in contact through additional features therebetween. Moreover, the first feature being "above", "over", and "on top of" the second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature has a higher horizontal height than the second feature. The first feature being "under", "beneath", and "underneath" the second feature includes the first feature being directly below and obliquely below the second feature, or simply indicating that the first feature has a lower horizontal height than the second feature.

[0056] Reference Figure 1 , a communication satellite structure, including a box body plate 1, a partition plate 2, and a main load-bearing angle box 4. The box body plate 1 forms a trapezoidal box structure; the partition plate 2 is disposed at intervals inside the box body plate 1, and the partition plate 2 and the inner wall of the box body plate 1 form a single-unit installation surface. The main load-bearing angle box 4 is disposed at least at one of the corners of the box body plate 1 and at the position between the partition plate 2 and the box body plate 1; at least one of the box body plate 1 and the partition plate 2 includes a honeycomb sandwich structure plate, and the honeycomb sandwich structure plate is provided with a connecting member 5. The connecting member 5 is connected between two adjacent honeycomb sandwich structure plates, and one end of the connecting member 5 is embedded inside the sandwich of the honeycomb sandwich structure plate.

[0057] The box body plate 1 forms an internal hollow structure of a trapezoidal box body structure, which lightens the communication satellite structure. At the same time, multiple communication satellite structures are evenly distributed within the launch space envelope of the launch vehicle for launching satellites, improving space utilization rate and increasing the number of communication satellite structures that can be carried by a single launch vehicle, so as to facilitate the realization of batch large-scale launch of communication satellite structures. The partition 2 is arranged at intervals inside the box body plate 1 to increase the overall rigidity and strength of the communication satellite structure, and at the same time increase the area of the single-machine installation surface to facilitate the installation of satellite single machines. The main load-bearing angle box 4 further increases the connection strength and connection area between the box body plate 1 itself and between the partition 2 and the box body plate 1. The main load-bearing angle box 4 includes a large angle box and a small angle box, and the large angle box and the small angle box are respectively arranged at the corners of the box body plate 1 or between the partition 2 and the box body plate 1. The box body plate 1 and the partition 2 reduce the overall mass of the communication satellite structure through the honeycomb sandwich structure plate, and are connected between adjacent box body plates 1 and between the box body plate 1 and the partition 2 through the connecting member 5, and one end of the connecting member 5 is buried inside the sandwich of the honeycomb sandwich structure plate to improve the connection strength and reliability.

[0058] The honeycomb sandwich structure plate can be selected as a pure aluminum honeycomb sandwich structure plate to improve the strength, stiffness and equipment installation accuracy of the communication satellite structure composed of the box body plate 1 and the partition 2. And it has the advantages of light weight, low processing cost and short production cycle.

[0059] The main load-bearing angle box 4 and the box body plate 1 or the partition 2 can be connected through a bush, a pre-embedded part and a bolt.

[0060] The design reference and process reference of the communication satellite structure formed by the box body plate 1 and the partition 2 are located at the geometric center of the satellite-rocket separation surface, that is, the design reference and process reference are located at the center of the surface of the box body plate 1 that is connected to the launch vehicle.

[0061] Reference Figure 1 and Figure 2 , as an alternative implementation, the box body plate 1 includes a longitudinal plate 11, a transverse plate 12 and a vertical plate 13; wherein, the longitudinal plate 11 includes a positive longitudinal plate 111 and a negative longitudinal plate 112, the positive longitudinal plate 111 and the negative longitudinal plate 112 are arranged opposite to each other and are respectively connected to the transverse plate 12 and the vertical plate 13; the transverse plate 12 includes a positive transverse plate 121 and a negative transverse plate 122, and the positive transverse plate 121 and the negative transverse plate 122 are symmetrically and obliquely arranged on both sides of the vertical plate 13; the vertical plate 13 includes a positive vertical plate 131 and a negative vertical plate 132, the positive vertical plate 131 and the negative vertical plate 132 are arranged opposite to each other, and the positive vertical plate 131 and the negative vertical plate 132 are respectively connected to the longitudinal plate 11 and the transverse plate 12 to form a trapezoidal box body structure.

[0062] As an alternative implementation, the longitudinal plate 11 is provided with a propulsion device installation part for installing a propulsion device.

[0063] Reference Figure 1 and Figure 7 As an optional implementation, the communication satellite structure further includes a solar panel mounting part 3. The solar panel mounting part 3 is disposed on the box body plate 1, such as on the transverse plates 12 on both sides of the box body plate 1, for setting and mounting solar panels. The solar panel mounting part 3 includes a first connection part 31, a second connection part 32 and a mounting part connecting piece 33. Among them, the first connection part 31 is disposed on the box body plate 1, and the mounting surface of the first connection part 31 is in contact with the transverse plate 12. The second connection part 32 is disposed at the center of the first connection part 31 at intervals and is provided with mounting holes. The mounting surface of the second connection part 32 intersects with the mounting surface of the first connection part 31 and forms an angle. The mounting part connecting pieces 33 are respectively disposed on the mounting surfaces of the first connection part 31 and the second connection part 32.

[0064] The first connection part 31 of the solar panel mounting part 3 is connected to the box body plate 1, such as the transverse plate 12 in the box body plate 1, through the mounting part connecting piece 33. The second connection part 32 is used for setting and mounting solar panels. During installation, the SADA (high-precision rotating device) can be installed on the mounting surface of the second connection part 32 through the mounting part connecting piece 33, and then the rotating shaft of the solar panel is connected to the SADA to complete the installation. The mounting surface of the first connection part 31 intersects, and an angle is formed between the axis of the mounting surface of the second connection part 32 and the mounting surface of the first connection part 31 to adapt to the relative position between the SADA and the transverse plate 12. The mounting surface of the second connection part 32 is spaced from the mounting surface of the first connection part 31 circumferentially to provide installation space and redundancy for the SADA and the solar panels, and to prevent the inner wall of the first connection part 31 of the solar panel mounting part 3 from hindering or affecting the installation of the SADA and the solar panels.

[0065] As an optional implementation, the vertical plate 13 is provided with a main payload mounting part for mounting the main payload.

[0066] As an optional implementation, the vertical plate 13 is provided with a satellite-rocket mounting support. Through the satellite-rocket mounting support, it is convenient to dock and mount the vertical plate 13 within the launch space envelope of the launch vehicle. The satellite-rocket mounting support and the main payload mounting part can be respectively disposed on the negative vertical plate 132 and the positive vertical plate 131 of the vertical plate 13.

[0067] Reference Figure 3, As an alternative embodiment, the connecting member 5 includes a first connecting device 51. The first connecting device 51 includes a first embedded part 511, a straight-edge hole sleeve 512, and a first connecting member 513. Among them, the first embedded part 511 is respectively arranged inside the vertical plate 13 and the longitudinal plate 11 to improve the connection strength between the vertical plate 13 and the longitudinal plate 11. The straight-edge hole sleeve 512 is arranged on the vertical plate 13 or the longitudinal plate 11 and is located at the first embedded part 511. One end of the first connecting member 513 is arranged inside the straight-edge hole sleeve 512, and the other end passes through the straight-edge hole sleeve 512 to connect the first embedded parts 511 inside the adjacent vertical plate 13 and the longitudinal plate 11.

[0068] Reference Figure 4 , As an alternative embodiment, the connecting member 5 includes a second connecting device 52. The second connecting device 52 includes a second embedded part 521, an inclined-edge hole sleeve 522, and a second bolt 523. Among them, the second embedded part 521 is respectively arranged inside the transverse plate 12 and the vertical plate 13 to improve the connection strength between the vertical plate 13 and the vertical plate 13. The inclined-edge hole sleeve 522 is arranged on the transverse plate 12 and is located at the second embedded part 521. One end of the second bolt 523 is arranged inside the inclined-edge hole sleeve 522, and the other end passes through the inclined-edge hole sleeve 522 to connect the second embedded parts inside the adjacent transverse plate 12 and the vertical plate 13.

[0069] In addition to the above embodiments, the connecting member 5 can also be arranged at any position of the box body plate 1 and the partition plate 2 for connection, so as to facilitate the assembly and fixation of the trapezoidal box body structure. Among them, the first connecting member 513 and the second connecting device 52 can be selected from screws or bolts.

[0070] Reference Figure 8 , As an alternative embodiment, the first embedded part 511 or the second embedded part 521 includes an embedded body 501 and a strengthening part 502. The embedded body 501 is provided with a friction part with an uneven surface, and the friction part is respectively attached to the inside of the honeycomb sandwich structure board. The strengthening part 502 is arranged on the embedded body 501, and the cross-section formed by the strengthening part 502 and the embedded body 501 is in an I shape.

[0071] The embedded body 521 is arranged inside the box body plate 1. For example, the embedded body 501 of the second embedded part 521 as shown Figure 8 is respectively arranged inside the transverse plate 12 and the vertical plate 13, so as to realize the connection between the transverse plate 12 and the vertical plate 13. The cross-section formed by the strengthening part 502 and the embedded body 501 is in an I shape, thereby improving the stiffness and strength at the connection of the transverse plate 12 and the vertical plate 13. The embedded body 501 is provided with a friction part with an uneven surface to improve the reliability of fixation when the embedded body 501 is arranged inside the box body plate 1 and prevent slippage.

[0072] As an alternative embodiment, the longitudinal plate 11 is provided with a lifting point.

[0073] refer to Figure 6 As an optional embodiment, the transverse plate 12 is provided with a robot arm mounting point 7.

[0074] The lifting point or the mechanical arm mounting point 7 provides a connection point or lifting traction point for connecting with a processing and production equipment such as a mechanical arm during the production and installation process of the communication satellite structure, so as to facilitate batch and automated production.

[0075] refer to Figure 2 As an optional embodiment, it also includes a connecting beam 6, which is arranged inside the box plate 1, such as the junction between the longitudinal plate 11 and the vertical plate 13. The connecting beam 6 can also be assembled into a trapezoidal frame shape to improve the connection strength and increase the connection area.

[0076] refer to Figure 5 and Figure 9 As an optional embodiment, the main load-bearing corner box 4 includes a box body 41, reinforcing ribs 42, a weight-reducing net 43 and a corner box embedded part; wherein, the box body 41 is fitted with at least one of the box body plate 1 and the partition plate 2, and the box body 41 is provided with a buried hole 44 that cooperates with the corner box embedded part; the reinforcing ribs 42 are arranged at the edge of the box body 41 and are perpendicular to the edge of the box body 41; the weight-reducing net 43 is arranged in the box body 41 and is located at the edge of the box body 41; one end of the corner box embedded part is connected to the box body plate 1, and the other end is connected to the box body 41 through the buried hole 44.

[0077] When the main load-bearing angle box 4 is connected to the box body plate 1 or the partition plate 2, the box body 41 is in contact with at least one of the box body plate 1 and the partition plate 2, or as shown in FIG. Figure 9 As shown, the box body 41 is first connected to the connecting beam 6 to provide an installation reference surface, and then connected to the box body plate 1 and the partition 2 to increase the connection strength and rigidity of the box body plate 1 and the partition 2. A mesh connection structure is formed by the weight-reducing net 43, which provides connection strength while reducing the weight of the communication satellite structure. The stability of the connection between the box body 41 and the box body plate 1 or the partition 2 is improved by the corner box embedded parts and embedded holes 44.

[0078] refer to Figure 10 As an optional embodiment, the box panel 1 is provided with an equipment mounting frame 8, including: a frame body 81, an installation reinforcement portion 82 and a connection reinforcement portion 83; wherein, the frame body 81 is arranged on the box panel 1; the installation reinforcement portion 82 is arranged on the frame body 81 for installing equipment; the installation reinforcement portion 82 is H-shaped, and the connection reinforcement portion 83 is arranged on the frame body 81 for connecting two adjacent box panels 1, and the connection reinforcement portion 83 is triangular or trapezoidal, and is perpendicular to the box panel 1 respectively.

[0079] The structural stiffness in the area is increased by the installation strengthening part 82 arranged in an H shape and the connection strengthening part 83 arranged in a triangular or trapezoidal shape, and the connection stability of the communication satellite structure and the equipment installed in the communication satellite structure is improved.

[0080] A launch vehicle provided by this application includes the above communication satellite structure.

[0081] The embodiments of this application have been introduced in detail above. Specific examples are used in this text to elaborate on the principle and implementation manner of this application. The description of the above embodiments is only used to help understand the method and its core idea of this application. At the same time, any changes or deformations made by those skilled in the art based on the idea of this application, within the specific implementation manner and application scope of this application, fall within the protection scope of this application. In summary, the content of this specification should not be construed as a limitation to this application.

Claims

1. A communication satellite structure, characterized in that, include: Box plates, the box plates forming a trapezoidal box structure; A partition plate is arranged at intervals inside the box body plate, and the partition plate and the inner wall of the box body plate form a single-machine installation surface; A main load-bearing corner box is provided at least at one of the corners of the box body plate and between the partition plate and the box body plate; The solar wing mounting portion is provided on the box plate and is used to mount the solar wing, including: A first connecting portion is provided on the box body plate, wherein a mounting surface of the first connecting portion is in contact with the box body plate; A second connecting portion is spaced apart and arranged at the center of the first connecting portion, and is provided with a mounting hole; a mounting surface of the second connecting portion is staggered with the mounting surface of the first connecting portion, and forms an angle; Mounting part connectors, respectively provided on the mounting surfaces of the first connecting part and the second connecting part; At least one of the box plate and the partition plate comprises: A honeycomb sandwich structure panel is provided with a connecting member, wherein the connecting member is connected between two adjacent honeycomb sandwich structure panels, and one end of the connecting member is buried inside the interlayer of the honeycomb sandwich structure panel.

2. The communication satellite structure according to claim 1, wherein The box body panels include longitudinal panels, transverse panels and vertical panels; wherein, The longitudinal plate includes a positive longitudinal plate and a negative longitudinal plate, the positive longitudinal plate and the negative longitudinal plate are arranged opposite to each other and are respectively connected to the transverse plate and the vertical plate; The transverse plate includes a positive transverse plate and a negative transverse plate, and the positive transverse plate and the negative transverse plate are symmetrically inclined and arranged on both sides of the vertical plate; The vertical plates include a positive vertical plate and a negative vertical plate, which are arranged opposite to each other and are respectively connected to the longitudinal plate and the transverse plate to form the trapezoidal box structure.

3. The communication satellite structure according to claim 2, characterized in that, The connecting member includes a first connecting device, and the first connecting device includes: First embedded parts are respectively arranged inside the vertical plate and the longitudinal plate to improve the connection strength between the vertical plate and the longitudinal plate; A straight-edge hole sleeve is provided on the vertical plate or the longitudinal plate and is located at the first embedded part; A first connecting piece has one end disposed in the straight-side hole sleeve and the other end passing through the straight-side hole sleeve to connect the adjacent vertical plate with the first embedded piece in the longitudinal plate.

4. The communication satellite structure according to claim 3, characterized in that, The connecting member includes a second connecting device, and the second connecting device includes: Second embedded parts are respectively arranged inside the transverse plate and the vertical plate to improve the connection strength between the vertical plate and the longitudinal plate; A bevel hole sleeve is provided on the transverse plate and is located at the second embedded part; A second bolt has one end disposed in the bevel hole sleeve and the other end passing through the bevel hole sleeve to connect the adjacent transverse plate with the second embedded part in the vertical plate.

5. The communication satellite structure according to claim 4, characterized in that, The first embedded part or the second embedded part includes: An embedded body, wherein the embedded body is provided with a friction portion with an uneven surface, and the friction portion is respectively fitted with the interior of the honeycomb sandwich structure plate; The reinforcing portion is arranged on the embedded body, and the cross section formed by the reinforcing portion and the embedded body is in an I-shape.

6. The communication satellite structure according to any one of claims 1-5, characterized in that, Also includes: The connecting beam is arranged inside the box body plate and is used to enhance the strength of the box body plate or the partition board.

7. The communication satellite structure according to any one of claims 1-5, characterized in that, The main load-bearing angle box includes a box body, reinforcing ribs, a weight-reducing mesh and an angle box embedded part; wherein, The box body is attached to at least one of the box body plate and the partition board, and the box body is provided with a buried hole that cooperates with the angle box embedded part; The reinforcing ribs are arranged at the edge lines of the box body and are perpendicular to the edge lines of the box body; The weight-reducing mesh is arranged on the box body and is located at the edge of the box body; One end of the angle box embedded part is connected to the box body plate, and the other end is connected to the box body through the buried hole.

8. The communication satellite structure according to any one of claims 1-5, characterized in that, The box body plate is provided with an equipment mounting rack, including: a rack body, a mounting reinforcing part and a connecting reinforcing part; wherein, The rack body is arranged on the box body plate; The mounting reinforcing part is arranged on the rack body and is used for mounting equipment; The connecting reinforcing part is arranged on the rack body and is used for connecting two adjacent box body plates.

9. A launch vehicle, characterized in that, It includes the communication satellite structure according to any one of claims 1-8.

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