Remote communication integrated satellite configuration

Abstract

The utility model relates to the technical field of satellites, in particular to a remote communication integrated satellite configuration, which is characterized in that a platform cabin and a load cabin are sequentially arranged in a satellite frame, one end of an optical load is fixed in the load cabin, the other end of the optical load extends out of one Z-direction end of the satellite frame, and an antenna platform is fixed at one Z-direction end of the satellite frame and is positioned on one side of the optical load; the expandable first communication antenna and the expandable second communication antenna are both fixed to the antenna platform, a satellite-rocket separation base is fixed to the other end of the satellite frame in the Z direction, and the two solar wings are fixedly connected with the two sides of the satellite frame in the Y direction respectively. Communication and remote sensing are integrated, one end of the optical load is installed in the load cabin of the satellite frame, the other end of the optical load extends out of the satellite frame, an overlarge satellite frame does not need to be arranged, and the lightweight requirement is met. The stand-alone equipment is placed in the platform cabin, and the stand-alone equipment with large heat productivity, the optical load and the antenna are placed in different areas, thereby facilitating satellite heat dissipation. The antenna platform is installed in a space beside the optical load, the structure is compact, and the space utilization rate is high.

Description

Technical Field

[0001] The utility model relates to the technical field of satellites, in particular to a communication and remote control integrated satellite configuration. Background Art

[0002] Remote sensing is an important means in disaster relief, maritime monitoring, global target detection and other scenarios, and requires a minute-level response. However, many factors limit the speed of obtaining remote sensing information. The integration of remote sensing and communications is an effective way to improve the speed of emergency response.

[0003] Existing integrated communication and remote sensing satellites usually adopt a rectangular structure. For larger optical payloads, a larger rectangular frame structure is required. The satellite structure is not compact enough and has unnecessary structure and weight, which makes it difficult to meet the requirements for lightweight micro-nano satellites. Utility Model Content

[0004] The technical problem to be solved by the utility model is how to provide a lightweight integrated communication and remote sensing satellite with high space utilization.

[0005] The utility model provides a technical solution for solving the above-mentioned technical problems as follows: a communication and remote sensing integrated satellite configuration, comprising a satellite frame, an optical payload, a deployable communication antenna 1, a communication antenna 2, a solar wing and a satellite-rocket separation seat, wherein a platform cabin and a payload cabin are sequentially arranged in the satellite frame, one end of the optical payload is fixed in the payload cabin, and the other end thereof extends out of one end of the satellite frame in the Z direction, an antenna station is fixed at one end of the satellite frame in the Z direction, the antenna station is located on one side of the optical payload, the deployable communication antenna 1 and the communication antenna 2 are both fixedly connected to the antenna station, the satellite frame in the Z direction is fixed with the satellite-rocket separation seat, there are two solar wings, and the two solar wings are respectively fixedly connected to both sides of the satellite frame in the Y direction.

[0006] The beneficial effects of the utility model are as follows: the integrated satellite configuration integrates communication and remote sensing, the solar wing can be folded or unfolded and receives solar energy, and the satellite-rocket separation seat is used to realize the separation of the satellite and the rocket. One end of the optical payload is installed in the payload cabin of the satellite frame, and the other end extends out of the satellite frame. There is no need to set a satellite frame that is too large in volume, which meets the lightweight requirements. The platform cabin is used to place the stand-alone equipment of each subsystem, and the stand-alone equipment with large heat generation is arranged on the ±Y plane of the satellite; the heat dissipation surface of the optical payload is arranged on the -X plane of the satellite, and the stand-alone equipment with large heat generation is placed in a partition with the optical payload and the antenna, which is conducive to the heat dissipation of the satellite. The antenna station is installed using the space on the side of the optical payload, with a compact structure and high space utilization. In addition, the antenna station is at one end of the satellite frame in the Z direction, and the beam of the antenna will not be blocked by the lens barrel of the optical payload, avoiding mutual interference between the optical payload and the antenna. The antenna station is assembled at the end of the satellite frame. When the satellite is assembled, the antenna station can be assembled in advance and docked and installed with the top plate of the satellite frame as an independent compartment to improve the assembly efficiency.

[0007] On the basis of the above technical solution, the present invention can also be improved as follows.

[0008] Furthermore, the satellite frame includes a bottom plate, a middle partition plate, a top plate and side plates, there are multiple side plates, the multiple side plates are connected end to end in sequence and enclose a prismatic cylinder, the bottom plate and the top plate are parallel to each other and are respectively fixedly connected to the two ends of the prismatic cylinder in the Z direction, the middle partition plate is fixed to the middle part of the prismatic cylinder, and divides the interior of the prismatic cylinder into the platform cabin and the payload cabin, the top plate has a load avoidance hole, one end of the optical load is fixedly connected to the middle partition plate, and the other end thereof passes through the load avoidance hole, the antenna station and the satellite-rocket separation seat are respectively fixedly connected to the top plate and the bottom plate, and the solar wing is fixedly connected to the side plate.

[0009] The beneficial effect of adopting the above further solution is that the satellite frame body is a prismatic structure with high structural strength.

[0010] Furthermore, the satellite frame also includes a long partition of the platform cabin and a short partition of the platform cabin, and the long partition of the platform cabin and the short partition of the platform cabin are both fixed in the platform cabin. There are two long partitions of the platform cabin, and the two long partitions of the platform cabin are parallel to each other and arranged at intervals, and divide the platform cabin into three platform cabin first areas, wherein at least one platform cabin first area is provided with at least one short partition of the platform cabin.

[0011] The beneficial effect of adopting the above further solution is that the platform cabin is divided into several areas by the platform cabin long partition and the platform cabin short partition, so that the electronic devices in the platform cabin can be placed in different areas, the internal structure is regular and compact, and the structural strength of the platform cabin is increased, and the supporting strength of the middle partition for the optical load is increased.

[0012] Furthermore, the satellite frame also includes a payload compartment partition, and there are multiple payload compartment partitions. The multiple payload compartment partitions are fixed in the payload compartment at intervals, and the payload compartment partition is arranged coplanar with the platform compartment long partition, and the two ends of the payload compartment partition are respectively fixedly connected to the top plate and the middle partition.

[0013] The beneficial effect of adopting the above further scheme is that the load compartment partition supports the top plate and the middle partition, and at the same time the load compartment partition is arranged coplanar with the platform compartment long partition, with high supporting strength, avoiding deformation of the middle partition due to different force positions on both sides.

[0014] Furthermore, a plurality of metal reinforcing embedded parts are pre-embedded in the middle partition, and the optical load is fixedly connected to the position of the middle partition where the metal reinforcing embedded parts are provided.

[0015] The beneficial effect of adopting the above further solution is that the metal reinforcing embedded parts increase the structural strength of the optical load connection, thereby avoiding errors in the detection results caused by changes in the installation position of the optical load.

[0016] Furthermore, a mounting plate is fixed to the surface of the middle partition corresponding to the metal reinforcing embedded part.

[0017] The beneficial effect of adopting the above further solution is that a mounting plate with high flatness is mounted on the surface of the middle partition plate to ensure the flatness requirement of the optical load mounting surface, while reducing the fine machining plane and reducing the machining difficulty.

[0018] Furthermore, a middle partition through hole is provided in the middle of the middle partition.

[0019] The beneficial effect of adopting the above further solution is: a middle partition through hole is provided on the middle partition, and the electronic devices in the platform cabin can be connected to the optical payload and receive the signals collected by the optical payload.

[0020] Furthermore, the antenna station includes antenna mounting plate 1 and antenna mounting plate 2, one end of the antenna mounting plate 1 in the Z direction is fixedly connected to one end of the satellite frame in the Z direction, the other end of the antenna mounting plate 1 in the Z direction is fixedly connected to one end of the antenna mounting plate 2 in the Y direction, the antenna mounting plate 2 is parallel to the end face of the satellite frame, the deployable communication antenna 1 is fixedly connected to the antenna mounting plate 1, and the communication antenna 2 is fixedly connected to the antenna mounting plate 2.

[0021] The beneficial effect of adopting the above further solution is that the deployable communication antenna 1 and the communication antenna 2 are respectively fixed on the antenna mounting plate 1 and the antenna mounting plate 2, providing sufficient installation space for the antennas.

[0022] Furthermore, the antenna station also includes two side trapezoidal plates, the two side trapezoidal plates are arranged in parallel and are respectively fixedly connected to the two ends of the antenna mounting plate in the X direction.

[0023] The beneficial effect of adopting the above further solution is that the two side trapezoidal plates support the antenna mounting plate 1 and the antenna mounting plate 2, thereby increasing the supporting strength.

[0024] Furthermore, a first side support plate of an antenna station parallel to the two side trapezoidal plates is provided at intervals on the side facing each other, and the side trapezoidal plate is fixedly connected to the first side support plate of the antenna station via a second side support plate of the antenna station, and a plurality of antenna station partitions are also fixed at intervals along the Z direction in the area enclosed by the side trapezoidal plate, the first side support plate of the antenna station, the second side support plate of the antenna station and the antenna mounting plate.

[0025] The beneficial effect of adopting the above further scheme is that the side trapezoidal plate, the first side support plate of the antenna station and the second side support plate of the antenna station form a prismatic support structure at both ends of the antenna mounting plate 1 in the X direction, thereby increasing the supporting strength of the antenna mounting plate 1 and the antenna mounting plate 2. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 A three-dimensional diagram of a satellite configuration for communication and remote sensing in one according to the utility model;

[0027] Figure 2 An exploded view of the satellite frame of the utility model;

[0028] Figure 3 A three-dimensional diagram of the antenna station of the utility model;

[0029] Figure 4 It is a three-dimensional diagram of the load compartment-XY partition of the utility model;

[0030] Figure 5 It is a top view of the load compartment-XY partition of the utility model;

[0031] Figure 6 It is a top view of the partition in the utility model;

[0032] Figure 7 It is the front view of the partition in the utility model.

[0033] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0034] 1. Satellite frame; 101. Bottom plate; 102. Middle partition; 1021. Mounting plate; 103. Top plate; 104. Platform cabin-Y long partition; 105. Platform cabin +Y long partition; 106. Platform cabin-XY short partition; 107. Platform cabin +XY short partition; 108. Platform cabin-X+Y short partition; 109. Platform cabin +X+Y short partition; 110. Payload cabin +X+Y partition; 111. Payload cabin +XY partition; 112. Payload cabin-XY partition; 11 21. Load compartment bulkhead mounting ears; 113. Load compartment -X+Y bulkhead; 114. -X side panel; 115. +X side panel; 116. +Y side panel; 117. -Y side panel; 118. Antenna mounting plate 1; 119. Antenna platform -X side trapezoidal plate; 120. Antenna platform +X side trapezoidal plate; 121. Antenna mounting plate 2; 122. Antenna platform +X side support plate; 123. Antenna platform -X side support plate; 124. Antenna platform bulkhead; 125. Antenna platform -Y side support plate;

[0035] 2. Optical payload; 3. Deployable communication antenna 1; 4. Communication antenna 2; 5. Solar wing; 6. Satellite-rocket separation seat. DETAILED DESCRIPTION

[0036] The principles and features of the present invention are described below. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention.

[0037] like Figure 1-Figure 7 As shown, this embodiment provides a communication and remote sensing integrated satellite configuration, including a satellite frame 1, an optical payload 2, a deployable communication antenna 1 3, a communication antenna 2 4, a solar wing 5 and a satellite-rocket separation seat 6, wherein the satellite frame 1 is provided with a platform cabin and a payload cabin in sequence, one end of the optical payload 2 is fixed in the payload cabin, and the other end thereof extends out of one end of the satellite frame 1 in the Z direction, an antenna station is fixed to one end of the satellite frame 1 in the Z direction, and the antenna station is located on one side of the optical payload 2, the deployable communication antenna 1 3 and the communication antenna 2 4 are both fixedly connected to the antenna station, the satellite-rocket separation seat 6 is fixed to the other end of the satellite frame 1 in the Z direction, and there are two solar wings 5, which are respectively fixedly connected to both sides of the satellite frame 1 in the Y direction.

[0038] The integrated satellite configuration integrates communication and remote sensing. The solar wing 5 can be folded or unfolded to receive solar energy. The satellite-rocket separation seat 6 is used to separate the satellite from the rocket. One end of the optical payload 2 is installed in the payload cabin of the satellite frame 1, and the other end extends out of the satellite frame 1. There is no need to set up a satellite frame 1 that is too large, which meets the lightweight requirements. The platform cabin is used to place the stand-alone equipment of each subsystem. The stand-alone equipment with high heat generation is arranged on the ±Y plane of the satellite; the heat dissipation surface of the optical payload 2 is arranged on the -X plane of the satellite. The stand-alone equipment with high heat generation is placed in a partition with the optical payload and the antenna, which is conducive to the heat dissipation of the satellite. The antenna station is installed using the space on the side of the optical payload 2, with a compact structure and high space utilization. In addition, the antenna station is at one end of the satellite frame in the Z direction, and the antenna beam will not be blocked by the lens barrel of the optical payload, avoiding mutual interference between the optical payload and the antenna. The antenna station is assembled at the end of the satellite frame. During the general assembly of the satellite, the antenna station can be assembled in advance and docked and installed with the top plate of the satellite frame as an independent compartment to improve the assembly efficiency.

[0039] Specifically, all cabin panels of the satellite frame 1 adopt a sandwich structure of aluminum honeycomb + aluminum skin.

[0040] On the basis of the above technical solution, the satellite frame 1 includes a bottom plate 101, a middle partition plate 102, a top plate 103 and side plates. There are multiple side plates, and the multiple side plates are connected end to end in sequence to form a prismatic cylinder. The bottom plate 101 and the top plate 103 are parallel to each other and are respectively fixedly connected to the two ends of the prismatic cylinder in the Z direction. The middle partition plate 102 is fixed to the middle part of the prismatic cylinder, and divides the interior of the prismatic cylinder into the platform cabin and the payload cabin. The top plate 103 has a load avoidance hole, one end of the optical load 2 is fixedly connected to the middle partition plate 102, and the other end thereof passes through the load avoidance hole, the antenna station and the satellite-rocket separation seat 6 are respectively fixedly connected to the top plate 103 and the bottom plate 101, and the solar wing 5 is fixedly connected to the side plate.

[0041] The main body of the satellite frame 1 is a prismatic structure with high structural strength.

[0042] Specifically, there are four satellite-rocket separation seats 6 , which are all connected to the base plate 101 and are distributed at the four corners of the base plate 101 . Each of the satellite-rocket separation seats 6 has four connection points with the base plate 101 .

[0043] Optionally, there are three, four, five or more side panels to form a polygonal prism. In one specific example, there are four side panels, which are -X side panel 114, +X side panel 115, +Y side panel 116 and -Y side panel 117. The four side panels, top panel 103 and bottom panel 101 form a rectangular satellite frame 1, and two solar wings 5 ​​are respectively installed on +Y side panel 116 and -Y side panel 117 in a folded state.

[0044] On the basis of the above technical solution, the satellite frame 1 also includes a long partition of the platform cabin and a short partition of the platform cabin, and the long partition of the platform cabin and the short partition of the platform cabin are both fixed in the platform cabin. There are two long partitions of the platform cabin, and the two long partitions of the platform cabin are parallel to each other and arranged at intervals, and divide the platform cabin into three platform cabin first areas, wherein at least one of the platform cabin first areas is provided with at least one short partition of the platform cabin.

[0045] The platform cabin is divided into several areas by the long partition and the short partition, so that the electronic devices in the platform cabin can be placed in different areas, and the internal structure is regular and compact. At the same time, the structural strength of the platform cabin is increased, and the supporting strength of the middle partition 102 for the optical payload 2 is increased.

[0046] In which, in the first area of ​​each platform cabin, no platform cabin short partition may be provided, or at least one platform cabin short partition may be provided.

[0047] In one specific example, Figure 2 As shown, a platform cabin is formed between the bottom plate 101 and the middle partition 102, the two platform cabin long partitions are respectively a platform cabin-Y long partition 104 and a platform cabin+Y long partition 105, and the platform cabin short partitions include a platform cabin-XY short partition 106, a platform cabin+XY short partition 107, a platform cabin-X+Y short partition 108 and a platform cabin+X+Y short partition 109. The platform cabin is divided into three platform cabin first areas along the Y direction, and two platform cabin first areas at both ends are respectively provided with two platform cabin short partitions, dividing each platform cabin first area into three areas along the X direction.

[0048] On the basis of the above technical solution, the satellite frame 1 also includes a payload compartment partition, and there are multiple payload compartment partitions. The multiple payload compartment partitions are fixed in the payload compartment at intervals, and the payload compartment partition is arranged coplanar with the platform compartment long partition, and the two ends of the payload compartment partition are respectively fixedly connected to the top plate 103 and the middle partition 102.

[0049] The load compartment partition supports the top plate 103 and the middle partition 102. At the same time, the load compartment partition is arranged on the same plane as the platform compartment long partition, and has high supporting strength, thereby preventing the middle partition 102 from being deformed due to different force positions on both sides.

[0050] Specifically, the multiple load compartment partitions are divided into two groups, and the two groups of load compartment partitions correspond to the two platform compartment long partitions above and below. One end of the load compartment partition is fixedly connected to the middle partition 102, and the other end is fixedly connected to the top plate 103.

[0051] In one specific example, Figure 2 , Figure 4 and Figure 5 As shown, there are four load compartment partitions, namely, load compartment +X+Y partition 110, load compartment +XY partition 111, load compartment -XY partition 112 and load compartment -X+Y partition 113. Load compartment partition mounting ears 1121 are provided at both ends of each load compartment partition. The two ends of the load compartment partition are connected to the top plate 103 and the middle partition 102 through the load compartment partition mounting ears 1121. Among them, the load compartment +X+Y partition 110 and the load compartment -X+Y partition 113 are aligned with the platform compartment +Y long partition 105 in the upper and lower parts; the load compartment +XY partition 111 and the load compartment -XY partition 112 are aligned with the platform compartment -Y long partition 104 in the upper and lower parts.

[0052] On the basis of the above technical solution, a plurality of metal reinforcing embedded parts are pre-embedded in the middle partition plate 102 , and the optical load 2 is fixedly connected to the position of the middle partition plate 102 where the metal reinforcing embedded parts are provided.

[0053] The metal reinforcing embedded parts increase the structural strength of the connection of the optical load 2, thereby preventing the error of the detection result caused by the change of the installation position of the optical load 2.

[0054] Specifically, the metal reinforcement embedded parts are made of aluminum alloy.

[0055] On the basis of the above technical solution, a mounting plate 1021 is further fixed to the surface of the middle partition plate 102 corresponding to the metal reinforcing embedded part.

[0056] A mounting piece 1021 with high flatness is mounted on the surface of the middle partition plate 102 to ensure the flatness requirement of the mounting surface of the optical load 2, while reducing the precision machining surface and lowering the machining difficulty.

[0057] Specifically, if Figure 6 and Figure 7 As shown, the optical load 2 is mounted on the middle partition 102. The middle partition 102 has a metal reinforcement embedded in the mounting surface of the optical load 2, and a 2mm thick aluminum sheet is attached to the skin as a mounting sheet 1021. The middle partition 102 is produced with a margin, and then combined with the aluminum sheet to ensure the flatness requirement of the mounting surface of the optical load 2.

[0058] On the basis of the above technical solution, a middle portion of the middle partition 102 has a middle partition through hole.

[0059] A middle partition through hole is provided on the middle partition 102 , and the electronic devices in the platform cabin can be connected to the optical payload 2 and receive the signals collected by the optical payload 2 .

[0060] On the basis of the above technical solution, the antenna station includes an antenna mounting plate 118 and an antenna mounting plate 2 121, one end of the antenna mounting plate 118 in the Z direction is fixedly connected to one end of the satellite frame 1 in the Z direction, the other end of the antenna mounting plate 118 in the Z direction is fixedly connected to one end of the antenna mounting plate 2 121 in the Y direction, the antenna mounting plate 2 121 is parallel to the end face of the satellite frame 1, the deployable communication antenna 1 3 is fixedly connected to the antenna mounting plate 118, and the communication antenna 2 4 is fixedly connected to the antenna mounting plate 2 121.

[0061] The deployable communication antenna 1 3 and the communication antenna 2 4 are respectively fixed on the antenna mounting plate 1 18 and the antenna mounting plate 2 121 to provide sufficient installation space for the antennas.

[0062] Specifically, Figure 2 and Figure 3 As shown, the antenna mounting plate 1 118 is a rectangular plate, the antenna mounting plate 2 121 is perpendicular to the antenna mounting plate 1 18 , and one end of the antenna mounting plate 2 121 in the Y direction has an arc-shaped notch for avoiding the side wall of the optical load 2 .

[0063] On the basis of the above technical solution, the antenna station further includes two side trapezoidal plates, the two side trapezoidal plates are arranged in parallel and are respectively fixedly connected to the two ends of the antenna mounting plate 118 in the X direction.

[0064] The two side trapezoidal plates support the antenna mounting plate 1 118 and the antenna mounting plate 2 121 to increase the supporting strength.

[0065] Specifically, the two side trapezoidal plates are respectively the antenna station -X side trapezoidal plate 119 and the antenna station +X side trapezoidal plate 120, and the two side trapezoidal plates are arranged along a direction parallel to the YZ plane.

[0066] On the basis of the above technical solution, a first side support plate of an antenna station parallel to the two side trapezoidal plates is provided at intervals on the opposite sides of the two side trapezoidal plates, and the side trapezoidal plate is fixedly connected to the first side support plate of the antenna station via a second side support plate of the antenna station, and a plurality of antenna station partition plates 124 are also fixed at intervals along the Z direction in the area enclosed by the side trapezoidal plate, the first side support plate of the antenna station, the second side support plate of the antenna station and the antenna mounting plate 118.

[0067] The side trapezoidal plate, the first side support plate of the antenna station and the second side support plate of the antenna station form a prismatic support structure at both ends of the antenna mounting plate 118X, thereby increasing the support strength of the antenna mounting plate 118 and the antenna mounting plate 2 121.

[0068] Specifically, the first side support plates of the two antenna stations are rectangular antenna station +X side support plate 122 and antenna station -X side support plate 123. The first side support plate of the antenna station is arranged parallel to the YZ plane. The second side support plate of the antenna station is Figure 2 The antenna platform-Y side support plate 125 is shown to be arranged parallel to the XZ plane. The antenna platform partition plate 124 is parallel to the XY plane, and the area separated by the antenna platform partition plate 124 can also be used to place electronic devices connected to the antenna.

[0069] Specifically, all two adjacent cabin panels of the satellite frame 1 are directly connected and fixed by screws.

[0070] In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "X", "Y", "Z", "up", "down", etc. are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present invention.

[0071] In addition, the terms "first", "second", "one", and "two" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present utility model, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0072] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0073] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example" or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the utility model. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, unless they are contradictory.

[0074] In the description of the present invention, 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 direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0075] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A satellite configuration with integrated communication and remote sensing, characterized in that: The invention comprises a satellite frame (1), an optical payload (2), a deployable communication antenna 1 (3), a communication antenna 2 (4), a solar wing (5) and a satellite-rocket separation seat (6). The satellite frame (1) is provided with a platform cabin and a payload cabin in sequence. One end of the optical payload (2) is fixed in the payload cabin, and the other end thereof extends out of one end of the satellite frame (1) in the Z direction. An antenna platform is fixed at one end of the satellite frame (1) in the Z direction. The antenna platform is located on one side of the optical payload (2). The deployable communication antenna 1 (3) and the communication antenna 2 (4) are both fixedly connected to the antenna platform. The satellite frame (1) is fixedly connected to the satellite-rocket separation seat (6) at the other end in the Z direction. There are two solar wings (5), and the two solar wings (5) are respectively fixedly connected to two sides of the satellite frame (1) in the Y direction.

2. The satellite configuration of communication and remote sensing according to claim 1, characterized in that: The satellite frame (1) comprises a bottom plate (101), a middle partition plate (102), a top plate (103) and side plates. There are a plurality of side plates, which are connected end to end in sequence to enclose a prismatic cylinder. The bottom plate (101) and the top plate (103) are parallel to each other and are respectively fixedly connected to the two ends of the prismatic cylinder in the Z direction. The middle partition plate (102) is fixed to the middle of the prismatic cylinder and divides the interior of the prismatic cylinder into the platform cabin and the payload cabin. The top plate (103) has a load avoidance hole. One end of the optical load (2) is fixedly connected to the middle partition plate (102), and the other end thereof passes through the load avoidance hole. The antenna station and the satellite-rocket separation seat (6) are respectively fixedly connected to the top plate (103) and the bottom plate (101). The solar wing (5) is fixedly connected to the side plate.

3. The satellite configuration of communication and remote sensing according to claim 2 is characterized in that: The satellite frame (1) further comprises a platform cabin long partition and a platform cabin short partition, both of which are fixed in the platform cabin. There are two platform cabin long partitions, which are parallel to each other and spaced apart, and divide the platform cabin into three platform cabin first areas, wherein at least one platform cabin first area is provided with at least one platform cabin short partition.

4. The satellite configuration of communication and remote sensing according to claim 3 is characterized in that: The satellite frame (1) further comprises a load compartment partition, wherein there are a plurality of load compartment partitions, and the plurality of load compartment partitions are fixed in the load compartment at intervals, the load compartment partition is arranged coplanar with the platform compartment long partition, and the two ends of the load compartment partition are respectively fixedly connected to the top plate (103) and the middle partition plate (102).

5. The satellite configuration of communication and remote sensing according to claim 2, characterized in that: A plurality of metal reinforcing embedded parts are pre-buried in the middle partition (102), and the optical load (2) is fixedly connected to the position of the middle partition (102) where the metal reinforcing embedded parts are provided.

6. The satellite configuration of communication and remote sensing according to claim 5, characterized in that: A mounting plate (1021) is also fixed to the surface of the middle partition (102) corresponding to the metal reinforcing embedded part.

7. The satellite configuration of communication and remote sensing according to claim 2, characterized in that: The middle portion of the middle partition (102) is provided with a middle partition through hole.

8. A satellite configuration for integrated communication and remote sensing according to any one of claims 1 to 7, characterized in that: The antenna station comprises an antenna mounting plate 1 (118) and an antenna mounting plate 2 (121); one end of the antenna mounting plate 1 (118) in the Z direction is fixedly connected to one end of the satellite frame (1) in the Z direction; the other end of the antenna mounting plate 1 (118) in the Z direction is fixedly connected to one end of the antenna mounting plate 2 (121) in the Y direction; the antenna mounting plate 2 (121) is parallel to the end surface of the satellite frame (1); the deployable communication antenna 1 (3) is fixedly connected to the antenna mounting plate 1 (118); and the communication antenna 2 (4) is fixedly connected to the antenna mounting plate 2 (121).

9. The satellite configuration of communication and remote sensing according to claim 8, characterized in that: The antenna station also includes two side trapezoidal plates, which are arranged in parallel and fixedly connected to the two ends of the antenna mounting plate (118) in the X direction.

10. The satellite configuration of communication and remote sensing according to claim 9, characterized in that: An antenna platform first side support plate parallel to the two side trapezoidal plates is provided at intervals on the side facing each other. The side trapezoidal plate is fixedly connected to the antenna platform first side support plate via the antenna platform second side support plate. A plurality of antenna platform partition plates (124) are also fixedly provided at intervals along the Z direction in the area enclosed by the side trapezoidal plate, the antenna platform first side support plate, the antenna platform second side support plate and the antenna mounting plate (118).

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