Flat-panel satellite

Abstract

The present application provides a flat-panel satellite, which relates to the field of satellite technology. The flat-panel satellite provided by the present application is in the shape of a flat plate, and includes a load-bearing component, a floor plate, and a ceiling plate. The load-bearing component is used to provide support and accommodate loads; the floor plate is connected to the lower side of the load-bearing component; and the ceiling plate is connected to the upper side of the load-bearing component. The present application uses the load-bearing component, the floor plate, and the ceiling plate to form a flat-panel satellite, which has a simple structure and high layout space utilization.

Description

Technical Field

[0001] The present application relates to the field of satellite technology, and in particular to a flat-panel satellite. Background Art

[0002] With the development and application of satellite technology, especially in the field of satellite communications, the demand for mass-launching satellites to achieve rapid networking has become increasingly strong, which has also prompted mass manufacturing and satellite launch to become a research hotspot in recent years. Flat-panel satellites have become a key research direction for mass manufacturing and satellite launch because of their low satellite platform height and the advantage of facilitating the launch of multiple satellites in one rocket.

[0003] In recent years, with the increase in satellite functions and performance enhancement, the number of payloads and platform units on the entire satellite has gradually increased, and the energy demand and power consumption have also gradually increased, which has put forward higher requirements for the structural design and layout of flat-panel satellites. Most existing flat-panel satellites are three-point separation. The satellite platform structure usually directly connects the three points to shorten the force transmission path, but at the same time it also cuts the layout space into multiple triangular areas, reducing the layout space utilization rate, which is not conducive to the layout of multiple satellite payloads. Summary of the invention

[0004] Based on this, the present application provides a flat-panel satellite that can improve carrying capacity and layout space.

[0005] The flat-panel satellite provided in this application is in the shape of a flat plate, and includes:

[0006] Load-bearing components, used to provide support and accommodate loads;

[0007] For floors, connect to the underside of the load-bearing components;

[0008] The top plate is connected to the upper side of the load-bearing components.

[0009] Optionally, the load-bearing component includes:

[0010] A load-bearing outer frame, the interior of which forms a closed load layout space, and the outer shape of the load-bearing outer frame matches the semicircular or approximately semicircular space range;

[0011] The internal load-bearing beam is arranged inside the load-bearing outer frame and is connected to the load-bearing outer frame as a whole. The internal load-bearing beam and the load-bearing outer frame constitute a main force transmission path for bearing the force acting on the flat-panel satellite.

[0012] Optionally, the load-bearing outer frame includes:

[0013] first outer frame transverse beam;

[0014] The second outer frame transverse beam is parallel to the first outer frame transverse beam and is arranged at an interval;

[0015] an outer frame longitudinal beam, perpendicular to the first outer frame transverse beam and the second outer frame transverse beam;

[0016] A bending portion, located in the middle of the first outer frame transverse beam and recessed toward one side of the second outer frame transverse beam, with both ends of the bending portion being connected to the first outer frame transverse beam as a whole;

[0017] The first oblique side is symmetrically arranged on both sides of the first outer frame transverse beam and is respectively connected to the first outer frame transverse beam and the outer frame longitudinal beam as a whole;

[0018] The second oblique side is symmetrically arranged on both sides of the second outer frame transverse beam, and is respectively connected to the second outer frame transverse beam and the outer frame longitudinal beam as a whole, and the length of the second oblique side is smaller than that of the first oblique side.

[0019] Optionally, the internal load-bearing beam comprises:

[0020] An internal transverse beam, the two ends of which are connected between the first hypotenuse and the longitudinal beam of the outer frame;

[0021] The first internal longitudinal beam intersects at the middle of the internal transverse beam and is perpendicular to the internal transverse beam. One end of the first internal longitudinal beam is connected to the bending portion as a whole, and the other end is connected to the second outer frame transverse beam as a whole. The intersection point of the internal transverse beams on the first internal longitudinal beam is located on the half side close to the bending portion, and the first internal longitudinal beam and the internal transverse beam form a cross structure.

[0022] Optionally, the internal load-bearing beam further comprises:

[0023] The second internal longitudinal beam has one end connected to the internal transverse beam and the other end connected between the first outer frame transverse beam and the first hypotenuse. The second internal longitudinal beam, the first hypotenuse and the internal transverse beam form a triangular structure.

[0024] Optionally, the upper surface and the lower surface of the load-bearing component have connection points, and the connection points are used to connect with at least one of the floor slab and the ceiling slab.

[0025] Optionally, a plurality of external connection interfaces are provided on the outer side of the load-bearing outer frame, and the external connection interfaces include a device installation interface and a stacking column interface, which are used to connect to the device and the stacking column respectively.

[0026] Optionally, the load-bearing assembly further includes two pairs of convex beam groups that are symmetrical to each other with the first internal longitudinal beam as the symmetry axis, and each pair of convex beam groups includes:

[0027] A first internal convex beam, one end of which is connected to the internal transverse beam as a whole and is perpendicular to the internal transverse beam;

[0028] The second internal convex beam has one end connected to the second outer frame transverse beam as a whole, and the other end corresponds to the position of the first internal convex beam. The positions of the first internal convex beam and the second internal convex beam are in the same straight line, and a disconnection portion is formed between the first internal convex beam and the second internal convex beam.

[0029] Optionally, a reinforcement portion is further included, and the reinforcement portion includes:

[0030] Longitudinal ribs are arranged on the side of the load-bearing component to improve the strength and rigidity of the load-bearing component;

[0031] The connecting boss is located at the end of the longitudinal rib and is connected with the longitudinal rib and the load-bearing component as a whole, so as to further improve the connection strength and rigidity of the load-bearing component.

[0032] Optionally, a plurality of holes are provided on the surface of the load-bearing component along the side direction for weight reduction and threading.

[0033] Optionally, the internal load-bearing beam is provided with a U-shaped groove for passing cables.

[0034] Optionally, the internal load-bearing beam divides the load layout space into multiple spaces, and the load layout space is rectangular or approximately rectangular.

[0035] Optionally, the flat-panel satellite provided by the present application further includes:

[0036] The rubidium clock plate is installed on the load-bearing component and is thermally insulated from the load-bearing component to form an independent temperature control zone, which is in the shape of a triangle.

[0037] Optionally, a heat insulating member is provided between the rubidium clock plate and the load-bearing component, and the heat insulating member is used to isolate the rubidium clock plate and the load-bearing component from heat transfer.

[0038] The flat-panel satellite provided in the present application is a flat-panel satellite composed of a load-bearing component, a floor plate and a ceiling plate. The flat-panel satellite has a simple structure and a high layout space utilization rate, so that the load can be distributed in a consistent and regular manner in the load-bearing component, thereby increasing the layout area and improving the load-bearing capacity and space utilization rate of the load-bearing component. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without exceeding the scope of protection required by the present application.

[0040] Figure 1 is a schematic exploded diagram of the structure of the flat-panel satellite provided by the present application;

[0041] Figure 2It is a structural schematic diagram of a load-bearing component in a flat-panel satellite provided by the present application;

[0042] Figure 3 is a side view of a structural schematic diagram of a flat-panel satellite provided by the present application;

[0043] Figure 4 It is a front view of the structural schematic diagram of the flat-panel satellite provided by the present application;

[0044] Figure 5 It is an enlarged diagram of the structural schematic diagram of the reinforcement part in the flat-panel satellite provided by the present application;

[0045] Figure 6 yes Figure 1 A schematic enlarged view of the structure shown in FIG.

[0046] Explanation of the accompanying drawings: 1. load-bearing component; 11. load-bearing outer frame; 111. first outer frame transverse beam; 112. second outer frame transverse beam; 113. outer frame longitudinal beam; 114. bending portion; 115. first hypotenuse; 116. second hypotenuse; 12. internal load-bearing beam; 121. internal transverse beam; 122. first internal longitudinal beam; 123. second internal longitudinal beam; 124. U-shaped groove; 13. convex beam group; 131. first internal convex beam; 132. second internal convex beam; 133. disconnection portion; 2. floor; 3. ceiling; 4. rubidium clock plate; 5. load layout space; 6. external interface; 7. reinforcement portion; 71. longitudinal rib; 72. connecting boss; 8. hole; 100. stacking column; 200. solar wing; 300. rubidium clock load. DETAILED DESCRIPTION

[0047] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are 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 those skilled in the art without creative work are within the scope of protection of the present application.

[0048] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", etc., indicating the orientation or position relationship, are based on the orientation or position 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 corresponding orientation, be constructed and operated in a corresponding orientation, and therefore cannot be understood as a limitation on 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 technical features indicated. Therefore, the features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present application, "multiple" means two or more, unless otherwise clearly and specifically defined.

[0049] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or mutual communication; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0050] In the present application, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0051] refer to Figure 1 The flat panel satellite provided in the present application is in the shape of a flat plate, and includes a load-bearing component 1, a floor plate 2, and a ceiling plate 3. The load-bearing component 1 is used to provide support and accommodate loads; the floor plate 2 is connected to the lower side of the load-bearing component 1. The ceiling plate 3 is connected to the upper side of the load-bearing component 1.

[0052] The load-bearing component 1, the floor plate 2 and the ceiling plate 3 together form a flat-plate satellite, so that the load distribution in the load-bearing component 1 is regular and uniform, the layout area is increased, and the load-bearing capacity and space utilization of the load-bearing component 1 are improved.

[0053] In some embodiments, the floor plate 2 and the ceiling plate 3 are both made of aluminum skin and aluminum honeycomb, and the load-bearing component 1 is integrally cast from a cast aluminum alloy.

[0054] refer to Figure 1 and Figure 2 As an optional embodiment, the load-bearing component 1 includes a load-bearing outer frame 11 and an internal load-bearing beam 12. The load-bearing outer frame 11 is connected end to end to form a closed shape, thereby improving the strength of the load-bearing component 1. The inside of the load-bearing outer frame 11 forms a closed load layout space 5, and the outer shape of the load-bearing outer frame 11 is similar to the following. Figure 2 The shape is matched with the semicircular or approximately semicircular space range shown. So that when the flat-panel satellite is carried inside the carrier, it can fit the curved inner wall of the carrier. And the flat-panel satellites at the same level inside the carrier can be combined in pairs, so that the two combined flat-panel satellites are circular or approximately circular in shape that fits the inner wall of the carrier. The internal bearing beam 12 is arranged inside the bearing outer frame 11 and is connected to the bearing outer frame 11 as a whole. The internal bearing beam 12 and the bearing outer frame 11 constitute the main force transmission path, which is used to bear the force acting on the flat-panel satellite, or transfer the load on the flat-panel satellite to the carrier.

[0055] In some embodiments, the load-bearing outer frame 11 is an I-beam in cross section, and the internal load-bearing beam 12 is a C-beam.

[0056] As an optional embodiment, the load-bearing outer frame 11 includes a first outer frame transverse beam 111, a second outer frame transverse beam 112, an outer frame longitudinal beam 113, a bending portion 114, a first hypotenuse 115 and a second hypotenuse 116. Among them, the second outer frame transverse beam 112 is parallel to the first outer frame transverse beam 111 and is arranged at intervals. The outer frame longitudinal beam 113 is perpendicular to the first outer frame transverse beam 111 and the second outer frame transverse beam 112. The bending portion 114 is located in the middle of the first outer frame transverse beam 111 and is recessed to one side of the second outer frame transverse beam 112, and the two ends of the bending portion 114 are connected to the first outer frame transverse beam 111 as a whole. The first hypotenuse 115 is symmetrically arranged on both sides of the first outer frame transverse beam 111, and is respectively connected to the first outer frame transverse beam 111 and the outer frame longitudinal beam 113 as a whole. The second oblique sides 116 are symmetrically arranged on both sides of the second outer frame transverse beam 112 , and are respectively connected to the second outer frame transverse beam 112 and the outer frame longitudinal beam 113 as a whole, and the length of the second oblique side 116 is smaller than that of the first oblique side 115 .

[0057] As an optional embodiment, the internal load-bearing beam 12 includes an internal transverse beam 121 and a first internal longitudinal beam 122. The two ends of the internal transverse beam 121 are connected between the first hypotenuse 115 and the outer frame longitudinal beam 113. The first internal longitudinal beam 122 intersects at the middle of the internal transverse beam 121 and is perpendicular to the internal transverse beam 121. One end of the first internal longitudinal beam 122 is connected to the bending portion 114 as a whole, and the other end is connected to the second outer frame transverse beam 112 as a whole. The intersection point of the internal transverse beam 121 on the first internal longitudinal beam 122 is located at the half side close to the bending portion 114, and the first internal longitudinal beam 122 and the internal transverse beam 121 form a cross structure. The first internal longitudinal beam 122 and the internal transverse beam 121 intersect perpendicularly to each other, so that the shape of the internal load-bearing beam 12 is cross-shaped, and is connected to the load-bearing outer frame 11 as a whole, so that the structure of the load-bearing component 1 is simple, and the number of reinforcing beams is reduced and the weight is reduced on the premise of meeting the use, so as to facilitate mass production.

[0058] As an optional embodiment, the internal load-bearing beam 12 further includes a second internal longitudinal beam 123, one end of the second internal longitudinal beam 123 is connected to the internal transverse beam 121, and the other end is connected between the first outer frame transverse beam 111 and the first oblique side 115, and the second internal longitudinal beam 123, the first oblique side 115, and the internal transverse beam 121 form a triangular structure, thereby improving the stability and bearing capacity of the internal load-bearing beam 12.

[0059] As an optional embodiment, the upper surface and the lower surface of the load-bearing component 1 have connection points (not shown in the figure), and the connection points are used to connect with at least one of the floor plate 2 and the ceiling plate 3.

[0060] refer to Figure 1 , Figure 3 and Figure 6 As an optional implementation, a plurality of external connection interfaces 6 are provided on the outer side of the load-bearing outer frame 11 , and the external connection interfaces 6 include a device installation interface and a stacking column interface, which are used to connect to the device and the stacking column 100 , respectively.

[0061] The device installation interface is used to connect with the device, and the stacking column interface can be connected with multiple stacking columns 100. For example, Figure 3 As shown, the stacking column interface can be connected to three stacking columns 100. The load on the flat-panel satellite and the force generated during the launch process are transmitted to the load-bearing component 1 through the sky plate 3 and the floor plate 2, and then transmitted to the stacking column 100 through the load-bearing outer frame 11 and the internal load-bearing beam 12 of the load-bearing component 1, and finally transmitted to the carrier through the stacking column 100. The stacking column 100 enables multiple flat-panel satellites to be stacked and placed, so as to facilitate the batch launch of multiple flat-panel satellites and quickly form a network.

[0062] As an optional embodiment, the load-bearing component 1 also includes two pairs of convex beam groups 13 that are symmetrical to each other with the first internal longitudinal beam 122 as the symmetry axis, and each pair of convex beam groups 13 includes a first internal convex beam 131 and a second internal convex beam 132. Among them, one end of the first internal convex beam 131 is connected to the internal transverse beam 121 as a whole, and is perpendicular to the internal transverse beam 121. One end of the second internal convex beam 132 is connected to the second outer frame transverse beam 112 as a whole, and the other end corresponds to the position of the first internal convex beam 131. The positions of the first internal convex beam 131 and the second internal convex beam 132 are in the same straight line, and a disconnection portion 133 is formed between the first internal convex beam 131 and the second internal convex beam 132. The disconnection portion 133 is used to connect the cables between the equipment installed on the floor 2 and the ceiling 3 through the disconnection portion 133, thereby improving the utilization rate of the load layout space 5.

[0063] The solar wing 200 is carried by the first inner convex beam 131 and the second inner convex beam 132 of the convex beam group 13, which is conducive to enhancing the rigidity of the floor 2 and the ceiling 3. At the same time, the convex beam group 13 is prevented from dividing the load layout space 5 through the disconnection portion 133, thereby improving the integrity of the load layout space 5, increasing the layout area of ​​the floor 2 and the ceiling 3, and facilitating the interconnection of the cables on the floor 2 and the ceiling 3.

[0064] refer to Figure 3 and Figure 4 As an optional embodiment, the flat-panel satellite further includes a reinforcement part 7, which includes a longitudinal rib 71 and a connecting boss 72. The longitudinal rib 71 is arranged on the side of the load-bearing component 1 to improve the strength and rigidity of the load-bearing component 1. The connecting boss 72 is located at the end of the longitudinal rib 71, and is connected to the longitudinal rib 71 and the load-bearing component 1 as a whole, so as to further improve the connection strength and rigidity of the load-bearing component 1.

[0065] In some embodiments, at least one of the connection point and the external interface 6 is provided with a reinforcement portion 7 for improving the structural strength of the connection point and the external interface 6 .

[0066] refer to Figure 1 and Figure 5 As an optional embodiment, a plurality of holes 8 are opened laterally on the surface of the load-bearing component 1, and the holes 8 are used for weight reduction and threading, so that the cables can be connected to each other through the holes 8, thereby facilitating the interconnection of the load equipment cables between the floor 2 and the ceiling 3.

[0067] As an optional embodiment, the internal load-bearing beam 12 is provided with a U-shaped groove 124 for passing cables, and the opening of the U-shaped groove 124 faces one side of the top plate 3. The cables that need to pass between two adjacent load layout spaces 5 can be directly placed in the U-shaped groove 124 when closing the compartment, so as to facilitate direct closing of the top plate 3 and the load-bearing component 1.

[0068] As an optional implementation, the internal load-bearing beam 12 divides the load layout space 5 into multiple parts, and the load layout space 5 is rectangular or approximately rectangular.

[0069] The multiple load layout spaces 5 separated by the load-bearing outer frame 11 and the internal load-bearing beams 12 are rectangular or approximately rectangular, making the load layout spaces 5 more regular, thereby improving the utilization rate of the load layout spaces 5 and the bearing capacity of the load-bearing component 1.

[0070] refer to Figure 1 and Figure 2 As an optional implementation, the flat-panel satellite provided by the present application also includes a rubidium clock plate 4, which is installed on the load-bearing component 1 and is heat-insulated from the load-bearing component 1 to form an independent temperature control zone. The independent temperature control zone is independent from the outside world and is used to install and accommodate loads that have high temperature requirements and require precise temperature control, such as the layout of the rubidium clock load 300. This is conducive to the precise temperature control of the rubidium clock, the timing load on the satellite. The independent temperature control zone is triangular, which can improve the strength and stability of the main load-bearing component 1.

[0071] The independent temperature control zone is used to independently and accurately control the temperature of the rubidium clock board 4, so as to avoid the influence of the working heat of other load components on the rubidium clock board 4 and reduce the temperature fluctuation, thereby meeting the working temperature range requirements of the rubidium atomic clock on the rubidium clock board 4. The rubidium clock load 300 on the rubidium clock board 4 is used to provide timing information, thereby realizing satellite positioning, speed measurement, etc.

[0072] In some embodiments, the rubidium clock plate 4 is made of aluminum skin and aluminum honeycomb.

[0073] refer to Figure 5 As an optional implementation, a heat insulating member (not shown in the figure) is provided between the rubidium clock plate 4 and the load-bearing component 1. The heat insulating member is used to isolate the rubidium clock plate 4 from the load-bearing component 1 from heat transfer, thereby reducing the influence of the temperature of the load-bearing component 1 on the timing load rubidium clock installed on the rubidium clock plate 4, so as to improve the accuracy of temperature control of the on-board timing rubidium clock load 300.

[0074] The embodiments of the present application are described in detail above. Specific examples are used herein to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method and its core idea of ​​the present application. At the same time, changes or deformations made by those skilled in the art based on the ideas of the present application, the specific implementation methods and the scope of application of the present application, all belong to the scope of protection of the present application. In summary, the content of this specification should not be construed as a limitation on the present application.

Claims

1. A flat-panel satellite, characterized in that: The flat-panel satellite is in a flat-panel shape and includes: Load-bearing components, used to provide support and accommodate loads; For the floor, connected to the lower side of the load-bearing component; The top plate is connected to the upper side of the load-bearing component.

2. The flat-panel satellite according to claim 1, characterized in that: The load-bearing component comprises: A load-bearing outer frame, wherein a load layout space is formed inside the load-bearing outer frame, and the outer shape of the load-bearing outer frame matches the semicircular space range; The internal load-bearing beam is arranged inside the load-bearing outer frame and connected to the load-bearing outer frame as a whole. The internal load-bearing beam and the load-bearing outer frame constitute a main force transmission path for bearing the force acting on the flat-panel satellite.

3. The flat-panel satellite according to claim 2, characterized in that: The load-bearing outer frame comprises: first outer frame transverse beam; A second outer frame transverse beam is parallel to the first outer frame transverse beam and is arranged at an interval; an outer frame longitudinal beam, perpendicular to the first outer frame transverse beam and the second outer frame transverse beam; A bending portion, located in the middle of the first outer frame transverse beam and recessed toward one side of the second outer frame transverse beam, with two ends of the bending portion being connected to the first outer frame transverse beam as a whole; A first hypotenuse is symmetrically arranged on both sides of the first outer frame transverse beam and is respectively connected to the first outer frame transverse beam and the outer frame longitudinal beam as a whole; The second oblique side is symmetrically arranged on both sides of the second outer frame transverse beam, and is respectively connected to the second outer frame transverse beam and the outer frame longitudinal beam as a whole, and the length of the second oblique side is smaller than that of the first oblique side.

4. The flat-panel satellite according to claim 3, characterized in that: Internal load-bearing beams include: An internal transverse beam, the two ends of which are connected between the first hypotenuse and the outer frame longitudinal beam; The first internal longitudinal beam intersects at the middle of the internal transverse beam and is perpendicular to the internal transverse beam. One end of the first internal longitudinal beam is connected to the bending portion as a whole, and the other end is connected to the second outer frame transverse beam as a whole. The intersection point of the internal transverse beam on the first internal longitudinal beam is located at the half side close to the bending portion, and the first internal longitudinal beam and the internal transverse beam form a cross structure.

5. The flat-panel satellite according to claim 4, characterized in that: The internal load-bearing beam further comprises: A second internal longitudinal beam has one end connected to the internal transverse beam and the other end connected between the first outer frame transverse beam and the first hypotenuse. The second internal longitudinal beam, the first hypotenuse and the internal transverse beam form a triangular structure.

6. The flat-panel satellite according to claim 1, characterized in that: The upper surface and the lower surface of the load-bearing component have connection points, and the connection points are used to connect with at least one of the floor plate and the ceiling plate.

7. The flat-panel satellite according to claim 2, characterized in that: A plurality of external connection interfaces are provided on the outer side of the load-bearing outer frame, and the external connection interfaces include a device installation interface and a stacking column interface, which are respectively used for connecting with the device and the stacking column.

8. The flat-panel satellite according to claim 4, characterized in that: The load-bearing assembly further includes two pairs of convex beam groups that are symmetrical to each other with the first internal longitudinal beam as the symmetry axis, and each pair of convex beam groups includes: A first internal convex beam, one end of which is integrally connected to the internal transverse beam and is perpendicular to the internal transverse beam; The second internal convex beam has one end connected to the second outer frame transverse beam as a whole, and the other end corresponds to the position of the first internal convex beam. The positions of the first internal convex beam and the second internal convex beam are in the same straight line, and a disconnection portion is formed between the first internal convex beam and the second internal convex beam.

9. The flat-panel satellite according to claim 1, characterized in that: Also included is a reinforcement portion, the reinforcement portion comprising: Longitudinal ribs, arranged on the side of the load-bearing component, for improving the strength and rigidity of the load-bearing component; The connecting boss is located at the end of the longitudinal rib and is connected to the longitudinal rib and the load-bearing component as a whole, so as to further improve the connection strength and rigidity of the load-bearing component.

10. The flat-panel satellite according to claim 1, characterized in that: The surface of the load-bearing component is provided with a plurality of holes along the side direction for weight reduction and threading.

11. The flat-panel satellite according to claim 2, characterized in that: The internal load-bearing beam is provided with a U-shaped groove for allowing the cable to pass through.

12. The flat-panel satellite according to claim 2, characterized in that: The internal load-bearing beam divides the load layout space into multiple parts, and the load layout space is rectangular.

13. The flat-panel satellite according to claim 1, characterized in that: Also includes: The rubidium clock plate is installed on the load-bearing component and is thermally insulated from the load-bearing component to form an independent temperature control zone, which is in a triangular shape.

14. The flat-panel satellite according to claim 13, characterized in that: A heat insulating member is arranged between the rubidium clock plate and the load-bearing component, and the heat insulating member is used to isolate the rubidium clock plate and the load-bearing component from heat transfer.

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