Small satellite platform structure carrying large amounts of propellant, point connection separation

Abstract

The application provides a small satellite platform structure which carries a large amount of propellant and is connected and separated in point mode, belongs to the technical field of spacecraft structure, and comprises a frame, a bottom plate, a lower cabin partition plate, a storage tank support rod, a middle layer plate, an upper cabin partition plate, a top plate and a side plate, so that the side plate surrounds the parallelly arranged bottom plate, middle layer plate and top plate into a closed box body, the bottom plate is connected to the frame, the storage tanks are arranged diagonally in the round holes on the bottom plate and the middle layer plate, and the storage tank support rods are uniformly distributed around the round holes; the middle layer plate separates the box body into an upper cabin and a lower cabin, the upper cabin partition plate is connected in the upper cabin, and the lower cabin partition plate is connected in the lower cabin. The application proposes a configuration of "point connection + storage tank sinking", meets the demand of the small satellite platform for carrying a large amount of propellant, effectively reduces the whole satellite center of mass, and improves the satellite dynamic environment; meanwhile, the bottom main load-bearing frame cooperates with a detachable adapter block, can adapt to different mechanical interfaces of launch vehicles, and realizes point connection and separation.

Description

Technical Field

[0001] This invention relates to the field of spacecraft structure technology, specifically to a small satellite platform structure that carries a large amount of propellant and features point-connected and detachable design. Background Technology

[0002] Small satellites are characterized by their small size, light weight, low development and launch costs, short development cycle, and flexible launch methods, and are widely used in fields such as communication, navigation, remote sensing, and reconnaissance.

[0003] Generally, small satellite platforms are small in size and have very limited layout space, so the instruments and equipment on board are mostly miniaturized. In addition, small satellites can be launched either as the primary satellite using a small launch vehicle or as a piggyback satellite using a large launch vehicle.

[0004] According to the mission plan, a certain type of small satellite needs to be compatible with multiple launch vehicles to complete launch and orbit insertion; it also needs to perform multiple orbital maneuvers and conduct on-orbit experiments, requiring the installation of a large-capacity propellant tank. Traditional small satellite platforms are insufficient to meet these space mission requirements. To address this, a novel small satellite platform needs to be developed, particularly focusing on platform configuration and structural design to support the overall satellite design and mission implementation.

[0005] A search of existing technologies revealed Chinese invention patent number CN201810623830.8, entitled "A Trapezoidal Small Satellite Structure Adapted for Launch," characterized by its trapezoidal overall configuration, comprising a honeycomb sandwich panel, an inner frame, and honeycomb embedded components. This microsatellite's unique trapezoidal configuration is specifically designed for launch, resulting in a small size. It is directly mounted in a point-mounted manner on the conical section of the launch vehicle's support module and is generally not used as the primary satellite of the launch vehicle.

[0006] The Chinese invention patent number is CN20201392659.3, and the invention title is "Structure for Small Satellites Applicable to Medium and High Orbits," which consists of six honeycomb panels forming the satellite body. This satellite platform is a small box-type structure with limited internal space and weak load-bearing capacity, making it suitable only for installing small remote sensing and communication payloads.

[0007] The Chinese invention patent number is CN201210104669.6, and the invention title is "A Central Module Truss Satellite Structure," which includes a central module, satellite platform equipment, payload equipment, and truss units. However, this satellite platform is difficult to install large propellant tanks, resulting in a very limited propellant capacity. Spacecraft using this platform are only suitable for near-Earth circular orbit missions.

[0008] A search of existing patent literature revealed Chinese invention patent publication number CN108791953A, which discloses a ladder-shaped small satellite structure suitable for launch, belonging to the field of spacecraft structures. The embedded beams within the structure form a relatively continuous closed configuration, achieving effective mechanical support and force transmission. Simultaneously, the necessary circuit cables for the entire satellite are laid within the embedded beams, resulting in fewer cable runs within the satellite cabin and a more streamlined internal structure. This unique small satellite structure features strong adaptability to launch vehicles, large internal space, light weight, and low manufacturing costs, making it a structural form with significant application value for launching small satellites. It consists of a honeycomb sandwich panel, an embedded frame, and honeycomb embedded parts, and can be directly installed on the conical section of the launch vehicle support cabin using a point-mounted method. The honeycomb sandwich panel adopts an aluminum skin honeycomb sandwich structure. Therefore, this document and the method described in this invention belong to different inventive concepts. Summary of the Invention

[0009] To address the shortcomings of existing technologies, the purpose of this invention is to provide a small satellite platform structure that carries a large amount of propellant and features point-connected and detachable design.

[0010] According to the present invention, a small satellite platform structure carrying a large amount of propellant and with point-connected separation includes a frame, a bottom plate, a lower compartment bulkhead, tank struts, a middle layer plate, an upper compartment bulkhead, a top plate, and side plates. The side plates surround the parallel bottom plate, middle layer plate, and top plate to form a closed box. The bottom of the bottom plate is connected to the frame. The tanks are arranged diagonally in the circular holes on the bottom plate and middle layer plate. The tank struts are evenly distributed around the circular holes.

[0011] The middle layer separates the container into an upper compartment and a lower compartment. The upper compartment bulkhead is connected to the upper compartment, and the upper and lower sides of the upper compartment bulkhead are connected to the top plate and the middle layer, respectively. The lower compartment bulkhead is connected to the lower compartment, and the upper and lower sides of the lower compartment bulkhead are connected to the middle layer and the bottom plate, respectively.

[0012] In some embodiments, the lower and upper bulkheads are cross-shaped, with the lower bulkhead dividing the lower compartment into four compartments and the upper bulkhead dividing the upper compartment into four compartments.

[0013] In some embodiments, the circular holes on the base plate and the middle plate are diagonally distributed.

[0014] In some embodiments, the center line of the circular hole on the base plate and the center line of the circular hole on the middle plate are kept on the same vertical line.

[0015] In some embodiments, the circular holes are connected to the upper and lower flanges in the corresponding storage tanks, respectively.

[0016] In some embodiments, one end of the tank strut is connected to the bottom plate, and the other end is connected to the middle plate; the tank strut transfers the propellant load to the frame, thereby improving the longitudinal stiffness and load-bearing capacity of the frame.

[0017] In some embodiments, the number of tank struts is greater than or equal to 4.

[0018] In some embodiments, the frame is provided with joints around its perimeter, and the joints are connected and separated at four points by explosive bolts.

[0019] In some embodiments, the frame is shaped like a grid, and embedded parts are provided inside the frame.

[0020] In some embodiments, an adapter block is also included, which is connected to the connector.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. In this invention, the bottom plate, middle plate and top plate divide the satellite into upper and lower sections. Each section is equipped with three cross-shaped partitions, which divide the section into four compartments. The two diagonally opposite compartments serve as propulsion compartments, which are used to install two large-volume storage tanks to meet the needs of small satellite platforms to carry a large amount of propellant.

[0023] 2. In this invention, the two large-volume storage tank sections are sunk into the launch vehicle support compartment, which can effectively reduce the satellite's center of gravity;

[0024] 3. In this invention, four struts are designed around each tank to transfer the propellant load to the frame, thereby improving longitudinal stiffness and load-bearing capacity, improving the dynamic environment, and reducing the vibration response during the launch phase.

[0025] 4. In this invention, the frame serves as the main load-bearing component of the entire satellite, and the metal joints at the four corners of the frame provide mechanical interfaces for connection with the launch vehicle. Four-point connection and separation are achieved through explosive bolts.

[0026] 5. The connectors at the four corners of the frame in this invention are equipped with detachable adapter blocks, which can be adapted to different launch vehicle mechanical interfaces, so that the satellite can be launched using different types of launch vehicles. Attached Figure Description

[0027] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0028] Figure 1 This is a schematic diagram of the internal structure of the present invention;

[0029] Figure 2 This is a schematic diagram of the overall structure of the present invention;

[0030] Figure 3 This is a schematic diagram of the framework structure of the present invention;

[0031] Figure 4 This is a schematic diagram showing the connection between the frame and the base plate of the present invention;

[0032] Figure 5 This is a diagram showing the connection relationship between the tank support rod and the circular hole in this invention;

[0033] Figure 6 This is a schematic diagram of the lower compartment structure of the present invention;

[0034] Figure 7 This is a schematic diagram of the upper cabin structure of the present invention;

[0035] Figure 8 This is a schematic diagram of the structure of the adapter block of the present invention;

[0036] Figure 9 This is a schematic diagram of the frame of the satellite platform and the launch vehicle mechanical interface without an adapter block according to the present invention;

[0037] Figure 10 This is a schematic diagram of the frame of the satellite platform and the launch vehicle mechanical interface of the present invention, which has an adapter block;

[0038] Figure 11 This is a schematic diagram of the installation of two 100L storage tanks according to the present invention.

[0039] Numbering on the map:

[0040] 1-Frame, 2-Bottom plate, 3-Lower compartment bulkhead, 4-Storage tank strut, 5-Middle layer plate, 6-Upper compartment bulkhead, 7-Top plate, 8-Side plate, 9-Transfer block. Detailed Implementation

[0041] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0042] Example

[0043] This invention provides a small satellite platform structure that carries a large amount of propellant and features point-connected and detachable configurations, such as... Figure 1 As shown, the system includes a frame 1, a bottom plate 2, a lower compartment bulkhead 3, tank support rods 4, a middle layer plate 5, an upper compartment bulkhead 6, a top plate 7, side plates 8, and connecting blocks 9. The bottom plate 2 is connected to the frame 1 at its bottom. The bottom plate 2, middle layer plate 5, and top plate 7 are arranged in parallel. The side plates 8 surround the bottom plate 2 and top plate 7 to form a closed box. The middle layer plate 5 separates the box into an upper compartment and a lower compartment. The upper compartment has an upper compartment bulkhead 6, which connects to the middle layer plate 5 and the top plate 7. The lower compartment has a lower compartment bulkhead 3, which connects to the bottom plate 2 and the middle layer plate 5. Preferably, the lower compartment bulkhead 3 and the upper compartment bulkhead 6 are divided into four compartments by three cross-shaped bulkheads. The connecting blocks 9 are fixed to the four corners of the frame 1. Figures 2-8 The diagram illustrates the entire platform structure assembly process, with the frame serving as the baseline for the assembly. The assembly sequence of structural components is: "Frame → Bottom Plate → Lower Cabin Bulkhead → Tank Support Rod → Middle Plate → Upper Cabin Bulkhead → Top Plate → Side Plate → Transition Block". Circular holes are provided on both the bottom plate 2 and the middle plate 5, distributed diagonally. These holes correspond one-to-one with the holes on the middle plate 5. The holes connect to the upper and lower flanges in the corresponding tanks. Four tank support rods 4 are evenly distributed around the tanks with the circular holes. One end of each support rod 4 connects to the bottom plate 2, and the other end connects to the middle plate 4. The support rods 4 transfer the propellant load to the frame 1, improving its longitudinal stiffness and load-bearing capacity. The frame 1 includes rods, joints, and reinforcing members. Joints are distributed around the perimeter of the rods, achieving four-point connection and separation via expansion bolts. Reinforcing members are diagonally distributed on the frame 1 and connected to the lower flange on the back of the bottom plate 2, forming a grid-like structure for the frame 1. The joints and rods are equipped with embedded parts, which are fixed to the base plate 2 with screws.

[0044] More specifically, such as Figure 3 As shown, frame 1, serving as the main load-bearing structure of the satellite platform, is formed by bonding joints, rods, and reinforcing members. The rods are made of T700 carbon fiber wound together. The joints at the four corners of frame 1 are machined from 2A14T6 aluminum alloy, while the other joints are molded from T700 carbon fiber. There are two sets of reinforcing members, six in each set, molded from T700 carbon fiber, distributed on a Φ418mm circumference, located on the underside of the base plate 2 at the lower flange of the storage tank to improve the tank's support rigidity.

[0045] The structural panel system includes bottom panel 1, middle panel 5, top panel 7, side panel 8, lower compartment bulkhead 3, and upper compartment bulkhead 6, etc. All structural panels adopt aluminum honeycomb sandwich panel structure. The panel material is aluminum alloy 2A12T4 with a thickness of 0.3mm, and the aluminum honeycomb material is 5A02H with a specification of 5×0.03. The common embedded parts in the sandwich panel are all made of magnesium alloy ZK61MT5.

[0046] The adapter block 9 is machined from 2A14T6 aluminum alloy and is connected to the four corner joints of frame 1 via screws for easy installation and disassembly. When the adapter block 9 is not installed, frame 1 provides a mechanical interface with the launch vehicle, such as... Figure 9 After the adapter block is installed on frame 1, it provides a mechanical interface with the launch vehicle, such as... Figure 10 .

[0047] like Figure 11As shown, the satellite is equipped with two 100L surface tension propellant tanks, symmetrically installed in quadrants I / IV and II / III. Four support rods are installed around each tank to transfer the propellant load to the frame, improving longitudinal stiffness and load-bearing capacity, enhancing the dynamic environment, and reducing vibration response during the launch phase. The support rods are constructed by bonding rods and joints together; the rods are made of T700 carbon fiber, and the joints are machined from 2A14T6 aluminum alloy.

[0048] Satellites weighing 500-1000 kg are generally called small satellites, 100-500 kg are called microsatellites, 10-100 kg are called microsatellites, and those less than 10 kg are called nanosatellites. Based on the ratio of propellant mass to total satellite mass, small satellites typically do not exceed 10%, while the small satellite described in this article has a propellant content of up to 30%. Typical small satellite platforms are too small to accommodate large propellant tanks.

[0049] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0050] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A small satellite platform structure carrying a large amount of propellant and featuring point-connected and detachable configuration, characterized in that: The container includes a frame (1), a bottom plate (2), a lower compartment bulkhead (3), a tank support rod (4), a middle layer plate (5), an upper compartment bulkhead (6), a top plate (7), and side plates (8). The side plates (8) surround the parallel bottom plate (2), the middle layer plate (5), and the top plate (7) to form a closed box. The bottom of the bottom plate (2) is connected to the frame (1). The tanks are arranged diagonally in the circular holes on the bottom plate (2) and the middle layer plate (5). The tank support rods (4) are evenly distributed around the circular holes. The middle layer plate (5) separates the container into an upper compartment and a lower compartment. The upper compartment partition (6) is connected to the upper compartment. The upper and lower sides of the upper compartment partition (6) are respectively connected to the top plate (7) and the middle layer plate (5). The lower compartment partition (3) is connected to the lower compartment. The upper and lower sides of the lower compartment partition (3) are respectively connected to the middle layer plate (5) and the bottom plate (2). The lower compartment bulkhead (3) and the upper compartment bulkhead (6) are cross-shaped. The lower compartment bulkhead (3) divides the lower compartment into four compartments, and the upper compartment bulkhead (6) divides the upper compartment into four compartments. One end of the tank support rod (4) is connected to the bottom plate (2), and the other end of the tank support rod (4) is connected to the middle plate (5). The tank strut (4) transfers the propellant load to the frame (1), thereby improving the longitudinal stiffness and load-bearing capacity of the frame (1).

2. The small satellite platform structure carrying a large amount of propellant and with point-connected separation as described in claim 1, characterized in that, The circular holes on the bottom plate (2) and the middle plate (5) are diagonally distributed.

3. The small satellite platform structure carrying a large amount of propellant and with point-connected separation as described in claim 2, characterized in that, The center line of the circular hole on the bottom plate (2) and the center line of the circular hole on the middle plate (5) are on the same vertical line.

4. The small satellite platform structure carrying a large amount of propellant and with point-connected separation as described in claim 3, characterized in that, The circular holes are respectively connected to the upper and lower flanges in the corresponding storage tanks.

5. The small satellite platform structure carrying a large amount of propellant and with point-connected separation as described in claim 1, characterized in that, The number of the tank support rods (4) is greater than or equal to 4.

6. The small satellite platform structure carrying a large amount of propellant and with point-connected separation as described in claim 1, characterized in that, The frame (1) is provided with a joint around its perimeter, and the joint is connected and separated at four points by an explosion bolt.

7. The small satellite platform structure carrying a large amount of propellant and with point-connected separation as described in claim 6, characterized in that, The frame (1) is in the shape of a grid, and embedded parts are provided inside the frame (1).

8. The small satellite platform structure carrying a large amount of propellant and with point-connected separation as described in claim 6, characterized in that, It also includes an adapter block (9) which is connected to the connector.

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