Satellite platform configuration for hosted services

Abstract

The application discloses a satellite platform configuration for carrying business and belongs to the technical field of satellite structures, and aims to solve the problems of the existing technology, such as the inability to meet the installation requirements of multiple types of loads, low carrying efficiency, long research and development period, and high research and development cost. The application comprises a carbon fiber force bearing cylinder located in the middle, a camera mounting plate arranged at one end of the carbon fiber force bearing cylinder, an optical load mounted on the camera mounting plate and located in the carbon fiber force bearing cylinder, a carrying plate arranged on the upper side of the carbon fiber force bearing cylinder, two solar wing panels symmetrically arranged on the left side and the right side of the carbon fiber force bearing cylinder relative to the center of mass of the satellite platform configuration, a platform single machine mounted on the left cabin plate and the carbon fiber force bearing cylinder, multiple carrying single machines mounted on the carrying area of the carrying plate, a high-power consumption single machine mounted on the right side of the carbon fiber force bearing cylinder, a separation mechanism mounted on the lower side of the carbon fiber force bearing cylinder, and a propeller mounted on the lower side of the carbon fiber force bearing cylinder.

Description

Technical Field

[0001] This invention belongs to the field of satellite structure technology, and specifically relates to a satellite platform configuration for onboard services. Background Technology

[0002] In recent years, the demand for on-orbit verification of new payloads has been increasing, but traditional methods have many drawbacks, such as: 1. New payloads are launched with the satellite as backups or as carry-on payloads, which is coupled with the satellite development process and has a long cycle; 2. New payloads are launched with the satellite as main payloads, which is costly and risky. If the new payload fails, it will lead to a significant reduction in satellite performance or even scrapping. On the other hand, payloads come in various forms and types, which puts forward a variety of requirements for the platform, including: installation orientation, field of view avoidance, stray light avoidance, micro-vibration / vibration isolation, and ensuring the range of motion of mechanical units.

[0003] Therefore, it is necessary to design a satellite platform configuration that is oriented towards payload services, with the characteristics of being universal and off-the-shelf, in order to reduce the cost of on-orbit verification of new payloads and shorten the development cycle.

[0004] Currently, satellite platform configurations are designed based on overall mission requirements, focusing on the main payload and key operational functions. However, no specific installation space is designed for payloads, making it impossible to meet the installation needs of diverse payload types. This results in low payload efficiency, long development cycles, and high development costs. Summary of the Invention

[0005] The purpose of this invention is to propose a satellite platform configuration for payload-carrying services, which solves the problems of existing technologies such as inability to meet the installation requirements of multiple types of payloads, low payload-carrying efficiency, long development cycle and high development cost.

[0006] To achieve the above objectives, a satellite platform configuration for payload services according to the present invention includes:

[0007] The carbon fiber load-bearing cylinder is located in the middle, and its four sides are defined as the upper side, lower side, left side and right side, respectively; the left side of the carbon fiber load-bearing cylinder is the left compartment and the right side is the right compartment.

[0008] A camera mounting plate is disposed at one end of the carbon fiber support cylinder, and an optical load is mounted on the camera mounting plate and located inside the carbon fiber support cylinder.

[0009] A mounting plate is provided on the upper side of the carbon fiber load-bearing cylinder. One side of the mounting plate is connected to the carbon fiber load-bearing cylinder, and the other side serves as a mounting area.

[0010] Regarding the two solar panels symmetrically positioned on the left and right sides of the carbon fiber support tube in the satellite platform configuration, the solar panel on the left side is connected to the carbon fiber support tube via a left cabin plate, and is supported on the side by a solar panel bracket; the solar panel on the right side is connected to the carbon fiber support tube via a support plate, and is supported on the side by a solar panel mount.

[0011] Platform units are installed on the left and right compartments and the left compartment panel;

[0012] Multiple mounting units installed in the mounting area of ​​the mounting plate;

[0013] A high-power unit is installed on the right side of the carbon fiber load-bearing cylinder;

[0014] A separation mechanism is installed on the lower side of the carbon fiber load-bearing cylinder, and the separation mechanism is symmetrical with respect to the centroid of the satellite platform configuration.

[0015] And a thruster installed on the lower side of the carbon fiber support cylinder, the thruster being symmetrical about the centroid of the satellite platform configuration.

[0016] The satellite platform configuration also includes reinforcing ribs, which are located at the corner where the lower surface of the mounting plate connects to the left side of the carbon fiber support cylinder and at the corner where the lower surface of the mounting plate connects to the right side of the carbon fiber support cylinder.

[0017] A protruding adapter bracket, corresponding to the shape of the separation mechanism, is provided on the side of the carbon fiber support cylinder near the separation mechanism. The separation mechanism, the carbon fiber support cylinder, and the adapter bracket are fixedly connected.

[0018] The left cabin plate is located on the left side of the carbon fiber support tube. One side along the vertical direction is fixed to the left side of the carbon fiber support tube, and one side along the horizontal direction is fixed to the bottom surface of the mounting plate. The other side along the vertical direction is connected to the corresponding solar panel via a hinge or via a solar panel drive mechanism.

[0019] The solar panel support system includes a first solar panel support, a second solar panel support, a third solar panel support, and a fourth solar panel support. The first and second solar panel supports are located on the upper left side, with one end fixedly connected to the left side of the carbon fiber support cylinder and the other end contacting and supporting the solar panel. Their upper parts are fixedly connected to the mounting plate. The third and fourth solar panel supports are located on the lower left side of the carbon fiber support cylinder, with one end fixedly connected to the left side of the carbon fiber support cylinder and the other end contacting and supporting the solar panel.

[0020] The support plate includes a first support plate, a second support plate, a third support plate, and a fourth support plate. The third and second support plates are located on the lower right side, with one end fixedly connected to the carbon fiber support cylinder. The fourth support plate is located on the right side away from the camera mounting plate, with one side fixedly connected to the carbon fiber support cylinder, and its lower and upper ends fixedly connected to the third support plate and the mounting plate, respectively. The first support plate is located on the right side near the camera mounting plate, with one side fixedly connected to the carbon fiber support cylinder, and its lower and upper ends fixedly connected to the second support plate and the mounting plate, respectively. The side of the first support plate away from the carbon fiber support cylinder is connected to the corresponding solar panel via a hinge or via a solar panel drive mechanism.

[0021] The outer surfaces of the first and second support plates are coated with a heat dissipation coating.

[0022] The satellite platform configuration also includes a heat sink, with the first support plate and the heat sink located on opposite sides of the high-power unit; one end of the heat sink is fixedly connected to a carbon fiber support cylinder, and the lower end is fixedly connected to a second support plate; the heat sink is provided with holes that allow cables to pass through.

[0023] The high-power unit is bonded to the heat sink and the first support plate with thermal grease in between.

[0024] The solar panel mount includes a first solar panel mount, a second solar panel mount, and a third solar panel mount; the first and second solar panel mounts are located on the right side of the carbon fiber support cylinder and fixed to one side of the mounting plate; the third solar panel mount is fixedly mounted on the second support plate; the unconnected sides of the first, second, and third solar panel mounts are located on the same plane, supporting the corresponding solar panels.

[0025] The beneficial effects of this invention are as follows: This invention provides a satellite platform configuration for payload services, with a carbon fiber load-bearing cylinder in the middle, supported by appropriately configured brackets on both sides for load-bearing function, and a single load-bearing plate at the top connecting the load-bearing cylinder to the side brackets. This forms an open structure, with a large payload space above the load-bearing plate, capable of accommodating multiple small payloads or a single large payload. The interior of the load-bearing cylinder provides a suitable mounting environment for optical payloads requiring stray light avoidance, such as optical cameras with networking needs. Depending on the interface of different payload units, only the load-bearing plate and camera mounting plate need to be redesigned, while other structures remain unchanged. The load-bearing plate can be expanded according to the number and volume of payload units, with the dimensions of other components appropriately expanded accordingly. After expansion, the relative positional relationships of the components remain unchanged, and the overall configuration remains the same. This improves development efficiency and reduces R&D costs. Attached Figure Description

[0026] Figure 1 This is a frontal view schematic diagram of the overall structure of a satellite platform configuration for onboard services according to the present invention;

[0027] Figure 2 This is a rear view schematic diagram of the overall structure of a satellite platform configuration for onboard services according to the present invention;

[0028] Figure 3 This is a schematic diagram of the front-view structure of a satellite platform configuration for onboard services according to the present invention with the solar panels hidden.

[0029] Figure 4 This is a rear-down view structural diagram of a satellite platform configuration for onboard services according to the present invention with the solar panels hidden.

[0030] Figure 5 This is an exploded view of a partial structure of a satellite platform configuration for onboard services according to the present invention;

[0031] Figure 6 This is a schematic diagram of the high-power single unit position from the lower right front view in a satellite platform configuration oriented towards onboard services according to the present invention;

[0032] Figure 7 This is a schematic diagram of the position of a high-power single unit in a satellite platform configuration for onboard services according to the present invention, viewed from the lower right rear.

[0033] The components include: 1. Separation mechanism, 2. Solar panel, 3. Thruster, 4. High-power unit, 5. Platform unit, 6. Mounted unit, 7. Optical payload, 8. Mounting plate, 9. Camera mounting plate, 10. Carbon fiber support tube, 11. First solar panel support, 12. Second solar panel support, 13. Third solar panel support, 14. Fourth solar panel support, 15. Left cabin plate, 16. First support plate, 17. Second support plate, 18. Third support plate, 19. Fourth support plate, 20. Heat sink, 21. First solar panel mount, 22. Second solar panel mount, 23. Third solar panel mount, 24. Adapter bracket, 25. Reinforcing rib. Detailed Implementation

[0034] The embodiments of the present invention will be further described below with reference to the accompanying drawings.

[0035] See Figures 1-7 The present invention provides a satellite platform configuration for payload services, comprising:

[0036] The carbon fiber load-bearing cylinder 10 located in the middle has four sides defined as the upper side, lower side, left side and right side respectively;

[0037] The camera mounting plate 9 is disposed at one end of the carbon fiber support cylinder 10, and the optical load 7 is mounted on the camera mounting plate 9 and located inside the carbon fiber support cylinder 10.

[0038] The mounting plate 8 is disposed on the upper side of the carbon fiber support cylinder 10. One side of the mounting plate 8 is connected to the carbon fiber support cylinder 10, and the other side serves as a mounting area.

[0039] Regarding the two solar panels 2 symmetrically arranged on the left and right sides of the carbon fiber support cylinder 10 with the center of mass of the satellite platform, the solar panel 2 on the left side is connected to the carbon fiber support cylinder 10 on one side via the left cabin plate 15, and is supported on the side by the solar panel bracket; the solar panel 2 on the right side is connected to the carbon fiber support cylinder 10 on one side via the support plate, and is supported on the side by the solar panel seat.

[0040] Platform units 5 are installed on the left compartment, right compartment and left compartment plate 15; in this embodiment, one of the three platform units 5 is installed on the left compartment plate 15 and the other two are installed on the right side of the carbon fiber load-bearing cylinder 10.

[0041] Multiple mounting units 6 are installed in the mounting area of ​​the mounting plate 8;

[0042] High-power single unit 4 is installed on the right side of the carbon fiber load-bearing cylinder 10;

[0043] The separation mechanism 1 is installed on the lower side of the carbon fiber support cylinder 10, and the separation mechanism 1 is symmetrical with respect to the centroid of the satellite platform configuration.

[0044] And a thruster 3 installed on the lower side of the carbon fiber support cylinder 10, the thruster 3 being symmetrical about the centroid of the satellite platform configuration.

[0045] The mounting plate 8 can be expanded according to the size and quantity of the mounted single unit 6. The size of related components such as the carbon fiber load-bearing cylinder 10 also needs to be expanded appropriately. After expansion, the relative positional relationship between the mounting plate 8 and related components such as the carbon fiber load-bearing cylinder 10 remains unchanged.

[0046] In addition to mounting the optical payload 7, the camera mounting plate 9 can also mount a stand-alone unit 6.

[0047] The solar panel 2 is installed symmetrically relative to the platform's center of mass, and is not limited to single-fold or multi-fold installations.

[0048] The separation mechanism 1 and the thruster 3 are symmetrically installed below the platform's center of gravity, opposite to the mounting unit 6. The thruster 3 is cylindrical, and different sizes of thrusters 3 can be adapted to fit the weight of the mounting unit 6.

[0049] The satellite platform configuration also includes reinforcing ribs 25, which are located at the corners where the lower surface of the mounting plate 8 connects to the left side of the carbon fiber support cylinder 10 and at the corners where the lower surface of the mounting plate 8 connects to the right side of the carbon fiber support cylinder 10. The arrangement of multiple reinforcing ribs 25 is perpendicular to the camera mounting plate 9, and the number and position of the reinforcing ribs 25 can be determined according to the layout of the mounted unit 6. Specifically, it is determined based on the results of mechanical simulation, with reinforcing ribs 25 placed at locations of high stress on the mounting plate 8. The layout of the mounted unit 6 affects the stress distribution on the mounting plate 8.

[0050] A transition bracket 24, which protrudes and corresponds to the shape of the separation mechanism 1, is provided on the side of the carbon fiber support cylinder 10 near the separation mechanism 1. The separation mechanism 1, the carbon fiber support cylinder 10, and the transition bracket 24 are fixedly connected.

[0051] The left cabin plate 15 is located on the left side of the carbon fiber support cylinder 10. One side along the vertical direction is fixed to the left side of the carbon fiber support cylinder 10, and one side along the horizontal direction is fixed to the bottom surface of the mounting plate 8. The other side along the vertical direction is connected to the corresponding solar panel 2 by a hinge or by a solar drive mechanism.

[0052] The solar panel support system includes a first solar panel support 11, a second solar panel support 12, a third solar panel support 13, and a fourth solar panel support 14. The first solar panel support 11 and the second solar panel support 12 are located on the upper left side, with one end fixedly connected to the left side of the carbon fiber support cylinder 10 and the other end contacting and supporting the solar panel 2. Their upper parts are fixedly connected to the mounting plate 8. The third solar panel support 13 and the fourth solar panel support 14 are located on the lower left side of the carbon fiber support cylinder 10, with one end fixedly connected to the left side of the carbon fiber support cylinder 10 and the other end contacting and supporting the solar panel 2.

[0053] The support plate includes a first support plate 16, a second support plate 17, a third support plate 18, and a fourth support plate 19. The third support plate 18 and the second support plate 17 are located on the lower right side, with one end fixedly connected to the carbon fiber support cylinder 10. The fourth support plate 19 is located on the right side away from the camera mounting plate 9, with one side fixedly connected to the carbon fiber support cylinder 10, and its lower and upper ends fixedly connected to the third support plate 18 and the mounting plate 8, respectively. The first support plate 16 is located on the right side near the camera mounting plate 9, with one side fixedly connected to the carbon fiber support cylinder 10, and its lower and upper ends fixedly connected to the second support plate 17 and the mounting plate 8, respectively. The side of the first support plate 16 away from the carbon fiber support cylinder 10 is connected to the corresponding solar panel 2 via a hinge or via a solar panel drive mechanism.

[0054] The outer surfaces of the first support plate 16 and the second support plate 17 are coated with a heat dissipation coating.

[0055] The satellite platform configuration also includes a heat sink 20. The first support plate 16 and the heat sink 20 are located on opposite sides of the high-power unit 4. One end of the heat sink 20 is fixedly connected to the carbon fiber support cylinder 10, and the lower end is fixedly connected to the second support plate 17. The heat sink 20 is provided with holes that allow cables to pass through.

[0056] The high-power stand-alone unit 4 is bonded to the heat sink 20 and the first support plate 16 with thermal grease in between.

[0057] The solar panel mount includes a first solar panel mount 21, a second solar panel mount 22, and a third solar panel mount 23. The first solar panel mount 21 and the second solar panel mount 22 are located on the right side of the carbon fiber support cylinder 10 and fixed to one side of the mounting plate 8. The third solar panel mount 23 is fixedly mounted on the second support plate 17. The unconnected sides of the first solar panel mount 21, the second solar panel mount 22, and the third solar panel mount 23 are located on the same plane, supporting the corresponding solar panels 2.

Claims

1. A satellite platform configuration for payload services, characterized in that, include: The carbon fiber support cylinder (10) located in the middle has four sides defined as the upper side, lower side, left side and right side respectively. The left side of the carbon fiber support cylinder (10) is the left compartment and the right side is the right compartment. The camera mounting plate (9) is set at one end of the carbon fiber support cylinder (10), and the optical load (7) is mounted on the camera mounting plate (9) and located inside the carbon fiber support cylinder (10). A mounting plate (8) is provided on the upper side of the carbon fiber support cylinder (10). One side of the mounting plate (8) is connected to the carbon fiber support cylinder (10), and the other side serves as the mounting area. Regarding the satellite platform configuration, the two solar panels (2) are symmetrically arranged on the left and right sides of the carbon fiber support cylinder (10). The solar panel (2) on the left side is connected to the carbon fiber support cylinder (10) on one side via the left cabin plate (15), and is supported by the solar panel bracket on the side. The solar panel (2) on the right side is connected to the carbon fiber support cylinder (10) on one side via the support plate, and is supported by the solar panel seat on the side. Platform units (5) are installed on the left and right compartments and the left compartment panel (15); Multiple mounting units (6) are installed in the mounting area of ​​the mounting plate (8); A high-power single unit (4) is installed on the right side of the carbon fiber load-bearing cylinder (10); A separation mechanism (1) is installed on the lower side of the carbon fiber support cylinder (10), and the separation mechanism (1) is symmetrical with respect to the centroid of the satellite platform configuration; And a thruster (3) installed on the lower side of the carbon fiber support cylinder (10), the thruster (3) being symmetrical about the centroid of the satellite platform configuration.

2. The satellite platform configuration for payload services according to claim 1, characterized in that, The satellite platform configuration also includes reinforcing ribs (25), which are located at the corner where the lower surface of the mounting plate (8) connects to the left side of the carbon fiber support cylinder (10) and at the corner where the lower surface of the mounting plate (8) connects to the right side of the carbon fiber support cylinder (10).

3. The satellite platform configuration for payload services according to claim 1, characterized in that, A transition bracket (24) protruding and corresponding to the shape of the separation mechanism (1) is provided on the side of the carbon fiber support cylinder (10) near the separation mechanism (1). The separation mechanism (1), the carbon fiber support cylinder (10), and the transition bracket (24) are fixedly connected.

4. The satellite platform configuration for onboard services according to claim 1, characterized in that, The left cabin plate (15) is located on the left side of the carbon fiber support tube (10). One side along the vertical direction is fixed to the left side of the carbon fiber support tube (10), and one side along the horizontal direction is fixed to the bottom surface of the mounting plate (8). The other side along the vertical direction is connected to the corresponding solar panel (2) by a hinge or by a solar drive mechanism.

5. The satellite platform configuration for payload services according to claim 1, characterized in that, The sail support includes a first sail support (11), a second sail support (12), a third sail support (13), and a fourth sail support (14). The first sail support (11) and the second sail support (12) are located on the upper left side, with one end fixedly connected to the left side of the carbon fiber support cylinder (10) and the other end contacting and supporting the solar panel (2). The upper part is fixedly connected to the mounting plate (8). The third sail support (13) and the fourth sail support (14) are located on the lower left side of the carbon fiber support cylinder (10), with one end fixedly connected to the left side of the carbon fiber support cylinder (10) and the other end contacting and supporting the solar panel (2).

6. The satellite platform configuration for payload services according to claim 1, characterized in that, The support plate includes a first support plate (16), a second support plate (17), a third support plate (18), and a fourth support plate (19); the third support plate (18) and the second support plate (17) are located on the lower right side, and one end is fixedly connected to the carbon fiber support cylinder (10); the fourth support plate (19) is located on the right side away from the camera mounting plate (9), one side is fixedly connected to the carbon fiber support cylinder (10), and the lower and upper ends are fixedly connected to the third support plate (18) and the mounting plate (8), respectively; the first support plate (16) is located on the right side near the camera mounting plate (9), one side is fixedly connected to the carbon fiber support cylinder (10), and the lower and upper ends are fixedly connected to the second support plate (17) and the mounting plate (8), respectively; the side of the first support plate (16) away from the carbon fiber support cylinder (10) and the corresponding solar panel (2) are connected by a hinge or by a solar drive mechanism.

7. A satellite platform configuration for payload services according to claim 6, characterized in that, The outer surfaces of the first support plate (16) and the second support plate (17) are coated with a heat dissipation coating.

8. The satellite platform configuration for payload services according to claim 6, characterized in that, The satellite platform configuration also includes a heat sink (20), the first support plate (16) and the heat sink (20) are located on opposite sides of the high power unit (4); one end of the heat sink (20) is fixedly connected to the carbon fiber support cylinder (10), and the lower end is fixedly connected to the second support plate (17); the heat sink (20) is provided with holes that allow cables to pass through.

9. A satellite platform configuration for payload services according to claim 8, characterized in that, The high-power unit (4) is bonded to the heat sink (20) and the first support plate (16) with thermal grease in between.

10. A satellite platform configuration for payload services according to claim 6, characterized in that, The solar panel mount includes a first solar panel mount (21), a second solar panel mount (22), and a third solar panel mount (23); the first solar panel mount (21) and the second solar panel mount (22) are located on the right side of the carbon fiber support tube (10) and fixed to one side of the mounting plate (8); the third solar panel mount (23) is fixedly mounted on the second support plate (17); the unconnected sides of the first solar panel mount (21), the second solar panel mount (22), and the third solar panel mount (23) are located on the same plane, supporting the corresponding solar panels (2).

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