Satellite support structure and satellite

Abstract

The utility model discloses a satellite support structure and satellite relates to the field of aerospace, is used for fixing on the bottom plate of satellite, including including fixed unit, longitudinal support column and transverse support column, the bottom plate is used for supporting longitudinal support column, fixed unit is fixed on longitudinal support column with transverse support column cooperation fixed, longitudinal support column passes through fixed unit with transverse support column detachable connection, the included angle between longitudinal support column with transverse support column can adjust. The utility model has the advantage that good adaptability.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, specifically to a satellite support structure and a satellite. Background Technology

[0002] The structure of a satellite generally adopts the form of a load-bearing cylinder, frame, aluminum honeycomb sandwich structure, etc. The surface material is mostly made of composite material lay-up or winding. The frame includes circular and square cross sections. Satellites are usually launched into space by rockets in the form of multiple satellites or two satellites.

[0003] However, due to the limited space inside the rocket, existing satellites suffer from poor adaptability. Utility Model Content

[0004] This utility model aims to solve one of the technical problems in related technologies to a certain extent. Therefore, this utility model provides a satellite support structure with the advantage of good adaptability.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A satellite support structure is provided for fixing to a satellite base plate. The support structure includes a fixing unit, a longitudinal support column, and a transverse support column. The base plate supports the longitudinal support column. The fixing unit is fixed to the longitudinal support column and cooperates with the transverse support column for fixation. The longitudinal support column is detachably connected to the transverse support column through the fixing unit. The included angle between the longitudinal support column and the transverse support column is adjustable.

[0007] The satellite is supported by a frame structure composed of longitudinal and transverse support columns, which can improve the structural strength of the satellite. The longitudinal and transverse support columns are fixedly connected by fixing units, and the angle between the longitudinal and transverse support columns can be adjusted so that the longitudinal support column can tilt relative to the base plate, thereby reducing the height requirement of the satellite and accommodating rocket spaces of more sizes.

[0008] Optionally, the fixing unit includes a boss and a fixing member. The boss is located on the side wall of the longitudinal support column and protrudes from the longitudinal support column. A receiving space is formed in the boss. The receiving space has an opening at one end away from the longitudinal support column. The fixing member is disposed in the receiving space. One end of the fixing member communicates with the opening. The extending direction of the fixing member is the same as the extending direction of the transverse support column and is used to cooperate with the transverse support column for fixing.

[0009] The open end of the boss forms a fixing surface for cooperating and fixing with the transverse support column. The fixing surface fits against the end of the transverse support column, and the fixing surface forms an angle with the side wall of the longitudinal support column. The angle can be changed.

[0010] Optionally, the boss is integrally formed with the longitudinal support column. Integrating the boss with the longitudinal support column strengthens the connection between the longitudinal support column and the fixing unit, improving the stability of the satellite support structure.

[0011] Optionally, the transverse support column includes a column body and at least one mounting portion. The mounting portion is disposed at the end of the column body and protrudes from the column body. The mounting portion has mounting holes formed on it. The mounting holes correspond one-to-one with the fixing units and are used to cooperate with the fixing units for fixation.

[0012] The mounting holes on the mounting section cooperate with the fixing units on the longitudinal support column to fix the transverse support column to the longitudinal support column, thereby improving the fixing effect between the transverse support column and the longitudinal support column and improving the stability and safety of the satellite support structure.

[0013] Optionally, the number of mounting parts is two, and the two mounting parts are arranged opposite to each other on both sides of the transverse support column.

[0014] Having two mounting points provides more balanced and uniform support, resulting in greater stability of the entire system or equipment. It also better distributes the load, reducing deformation or damage caused by uneven local stress. The overall structural rigidity can be increased by reinforcing connections or supports, preventing deformation during launch. Especially when the rocket is under high acceleration, adding a second mounting plate effectively prevents problems caused by the bending or detachment of a single mounting plate.

[0015] Optionally, the two mounting portions are arranged along the extension direction of the longitudinal support column. Arranging the two mounting portions along the extension direction of the longitudinal support column typically makes the structure more symmetrical, improving its overall stability and load-bearing capacity. The symmetrical design helps to distribute external forces and reduce unnecessary twisting or deformation.

[0016] Optionally, the longitudinal support column includes two connecting parts that protrude from the surface of the longitudinal support column, and the longitudinal support column can be fixedly connected to the base plate through one of the connecting parts.

[0017] The protruding connecting part provides a larger contact surface, making the connection between the longitudinal support column and the base plate more secure and enhancing the connection strength. This effectively reduces loosening caused by long-term use or external vibration, ensuring long-term stable operation of the equipment. It also optimizes load distribution, preventing concentrated stress at the connection point between the support column and the base plate, thereby improving the overall load-bearing capacity of the system. The protruding connecting part simplifies the connection design between the support column and the base plate, reducing complex connection structures during manufacturing and improving production efficiency and manufacturing precision. Furthermore, it allows the connection between the support column and the base plate to operate stably in various operating environments, such as high loads and frequent vibrations during lift-off, improving the adaptability and service life of the equipment.

[0018] Optionally, a plurality of connection holes are formed on the connection portion away from the base plate, the connection holes being used to support the longitudinal support column during launch.

[0019] By forming multiple connection holes in the joint, the longitudinal support column can be effectively supported, ensuring its stability and preventing wobbling during launch. This reduces damage or instability caused by vibration or impact during launch. The multiple connection holes provide multi-point support, making the longitudinal support column more robust during launch and avoiding the risk of tilting or accidental detachment that might occur with a single support point, thus improving overall launch safety. Furthermore, the design using connection holes for support not only aids in fixation during launch but also facilitates the installation and disassembly of equipment or components after rocket launch. The multiple connection holes can be flexibly adjusted to facilitate installation operations under different conditions.

[0020] Optionally, the longitudinal support column is a polygonal hollow column, with its side edges extending beyond the edges of the transverse support column to which it is fixedly connected. The hollow structure not only reduces the weight of the column but also enhances its resistance to bending and deformation. The polygonal design makes the column structure more stable, especially under heavy loads or external forces, better distributing stress and improving the overall structural rigidity. Furthermore, the hollow structure allows for optimized material usage while maintaining strength and stability, reducing the overall structural weight and providing more space for the equipment. The hollow structure effectively reduces unnecessary material waste.

[0021] Furthermore, this utility model also provides a satellite, which includes a base plate, side plates, a top plate, and the aforementioned satellite support structure. The satellite support structure is fixedly connected to the base plate and is used to support the side plates and the top plate. The reasoning process for the beneficial effects of the satellite provided by this utility model and the aforementioned satellite support structure is similar, and will not be repeated here.

[0022] These features and advantages of this utility model will be disclosed in detail in the following specific embodiments and accompanying drawings. The preferred embodiments or means of this utility model will be shown in detail in conjunction with the accompanying drawings, but are not intended to limit the technical solutions of this utility model. In addition, each of these features, elements and components appearing in the following text and drawings is multiple and is labeled with different symbols or numbers for convenience, but all represent parts with the same or similar structure or function. Attached Figure Description

[0023] The present invention will be further described below with reference to the accompanying drawings:

[0024] Figure 1 This is a schematic diagram of a satellite support structure according to the present invention.

[0025] Figure 2 This is a schematic diagram of a fixed unit structure for a satellite support structure according to the present invention.

[0026] Figure 3 This is a schematic diagram of the installation part of a satellite support structure according to the present invention.

[0027] Figure 4 This is a schematic diagram of the connection part of a satellite support structure according to the present invention.

[0028] Explanation of reference numerals in the attached drawings: 1. Longitudinal support column; 11. Connecting part; 12. Connecting hole; 2. Base plate; 3. Transverse support column; 31. Column body; 32. Mounting part; 33. Mounting hole; 4. Fixing unit; 41. Boss; 42. Fastener; 43. Accommodation space. Detailed Implementation

[0029] The embodiments of this utility model are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described are intended to explain this utility model and should not be construed as limiting it.

[0030] The terms "an embodiment," "example," or "trademark" used in this specification refer to a particular feature, structure, or characteristic described in connection with the embodiment itself that may be included in at least one embodiment disclosed in this utility model. The phrase "in an embodiment" appearing in various places throughout the specification does not necessarily refer to the same embodiment.

[0031] The satellite's structure typically employs forms such as a load-bearing cylinder, frame, or aluminum honeycomb sandwich structure. The surface material is mostly composite material lay-up or winding. The load-bearing cylinder structure, due to its closed shell configuration, has poor openness, hindering the assembly and operation of equipment within. Frames include circular and square cross-sections. Circular cross-section frames have better mechanical properties but cannot provide an installation interface for the base plate 2; connections between base plates 2 require metal corner strips. Square cross-section frames suffer from uneven stress distribution in their joint design. All of these frame structures have drawbacks such as large deformation and low repeatability.

[0032] For satellites that are high in altitude, large in size, heavy in weight, and irregular in shape, if a dual-satellite launch is adopted, the existing satellite support tube, frame, and aluminum honeycomb sandwich structure all need to be designed with docking rings and adapter brackets. This is greatly constrained by the launch vehicle interface and the structural shape of the satellite itself, resulting in poor adaptability and scalability, and failing to solve the problem of limited space for final assembly operations.

[0033] In response, this application proposes a satellite support structure for fixing to the base plate 2 of a satellite. The support structure includes a fixing unit 4, a longitudinal support column 1, and a transverse support column 3. The base plate 2 supports the longitudinal support column 1. The fixing unit 4 is fixed to the longitudinal support column 1 and cooperates with the transverse support column 3 for fixation. The longitudinal support column 1 is detachably connected to the transverse support column 3 through the fixing unit 4. The included angle between the longitudinal support column 1 and the transverse support column 3 can be adjusted.

[0034] The satellite is supported by a frame structure composed of longitudinal support columns 1 and transverse support columns 3, which can improve the structural strength of the satellite. The longitudinal support columns 1 and transverse support columns 3 are fixedly connected by fixing units 4. The angle between the longitudinal support columns 1 and the transverse support columns 3 can be adjusted so that the longitudinal support column 1 can tilt relative to the base plate 2, thereby reducing the height requirement of the satellite and accommodating rocket spaces of more sizes.

[0035] In this embodiment, the transverse support column 3 is made of high-strength aluminum alloy, with a cross-sectional dimension that is half that of the load-bearing column and a wall thickness of 2mm.

[0036] The fixing unit 4 includes a boss 41 and a fixing member 42. The boss 41 is located on the side wall of the longitudinal support column 1 and protrudes from the longitudinal support column 1. A receiving space 43 is formed in the boss 41. The receiving space 43 has an opening at one end away from the longitudinal support column 1. The fixing member 42 is disposed in the receiving space 43. One end of the fixing member 42 communicates with the opening. The extending direction of the fixing member 42 is the same as the extending direction of the transverse support column 3, and it is used to cooperate with the transverse support column 3 for fixing. The extending direction of the fixing member 42 is the same as that of the transverse support column 3.

[0037] The side interface of the longitudinal support column 1 adopts a φ10mm×10mm boss with an embedded M5 steel wire thread sleeve. The direction can be tilted at a certain angle to the normal of the side of the longitudinal support column 1 and is perpendicular to the corresponding base plate 2 and transverse support column 3.

[0038] The open end of the boss 41 forms a fixing surface for cooperating and fixing with the transverse support column 3. The fixing surface is in contact with the end of the transverse support column 3, and the fixing surface forms an angle with the side wall of the longitudinal support column 1. The angle can be changed.

[0039] In actual production, the top surface of the boss 41 can be processed so that the top surface of the boss 41 forms an angle with the side of the longitudinal support column 1 on which it is installed, and the opening and extension direction of the internal fastener 42 can be changed to meet the matching and fixing with the transverse support column 3 with different extension directions. That is, by changing the opening direction of the fastener 42 during manufacturing, the fixing of the transverse support column 3 with different angles and the longitudinal support column 1 can be met.

[0040] The boss 41 is integrally formed with the longitudinal support column 1. The integral formation of the boss 41 with the longitudinal support column 1 can strengthen the connection between the longitudinal support column 1 and the fixing unit 4, and improve the stability of the satellite support structure.

[0041] In this embodiment, all six sides have mounting interfaces, and the components are integrally formed using 2A12 steel with good forging properties.

[0042] The transverse support column 3 includes a column body 31 and at least one mounting part 32. The mounting part 32 is disposed at the end of the column body 31 and protrudes from the column body 31. The mounting part 32 has mounting holes 33 formed thereon. The mounting holes 33 correspond one-to-one with the fixing unit 4 and are used to cooperate with the fixing unit 4 for fixing.

[0043] The mounting holes 33 on the mounting section 32 and the fixing unit 4 on the longitudinal support column 1 cooperate to fix the transverse support column 3 and the longitudinal support column 1, thereby improving the fixing effect between the transverse support column 3 and the longitudinal support column 1 and improving the stability and safety of the satellite support structure.

[0044] The number of mounting parts 32 is two, and the two mounting parts 32 are arranged opposite to each other on both sides of the transverse support column 3.

[0045] Setting up two mounting sections 32 provides more balanced and uniform support, resulting in greater stability of the entire system or equipment. This allows for better load distribution and reduces deformation or damage caused by uneven local stress. The overall structural rigidity can be improved by reinforcing connections or supports, preventing deformation during launch. Especially when the rocket is under high acceleration, adding a second mounting plate effectively prevents problems caused by the bending or detachment of a single mounting plate.

[0046] The two mounting portions 32 are arranged along the extending direction of the longitudinal support column 1. Arranging the two mounting portions 32 along the extending direction of the longitudinal support column 1 generally makes the structure more symmetrical, improving the overall stability and load-bearing capacity of the structure. The symmetrical design helps to distribute external forces and reduce unnecessary twisting or deformation.

[0047] The longitudinal support column 1 includes two connecting parts 11, which protrude from the surface of the longitudinal support column 1. The longitudinal support column 1 can be fixedly connected to the base plate 2 through one of the connecting parts 11.

[0048] The protruding connecting part 11 provides a larger contact surface, making the connection between the longitudinal support column 1 and the base plate 2 more secure and enhancing the connection strength. This effectively reduces loosening caused by long-term use or external vibration, ensuring long-term stable operation of the equipment, optimizing load distribution, and preventing concentrated stress at the connection between the support column and the base plate 2, thereby improving the overall load-bearing capacity of the system. The protruding connecting part 11 simplifies the connection design between the support column and the base plate 2, reducing complex connection structures during manufacturing and improving production efficiency and manufacturing precision. Furthermore, it enables the connection between the support column and the base plate 2 to operate stably in various operating environments, such as high loads and frequent vibrations during lift-off, improving the adaptability and service life of the equipment.

[0049] A plurality of connection holes 12 are formed on the connection portion 11 away from the base plate 2, and the connection holes 12 are used to support the longitudinal support column 1 during launch.

[0050] In this embodiment, the connecting part 11 away from the base plate 2 is in the form of a connecting flange, which facilitates handling.

[0051] By forming multiple connecting holes 12 on the connecting part 11, the longitudinal support column 1 can be effectively supported, ensuring that the support column is stable and does not wobble during launch, thereby reducing damage or instability caused by vibration or impact during launch. The design of multiple connecting holes 12 provides multi-point support, making the longitudinal support column 1 more secure during launch and avoiding the risk of tilting or accidental detachment that may occur with a single support point, thus improving the overall safety of the launch process. Furthermore, the design using connecting holes 12 for support not only helps with fixation during launch but also facilitates the installation and disassembly of equipment or components after rocket launch. The multiple connecting holes 12 can be flexibly adjusted to facilitate installation operations under different conditions.

[0052] The longitudinal support column 1 is a polygonal hollow column, with its side edges extending beyond the edge of the transverse support column 3 to which it is fixedly connected. The hollow structure not only reduces the weight of the column 31 but also enhances its resistance to bending and deformation. The polygonal design makes the column 31 more stable, especially under heavy loads or external forces, better distributing stress and improving the overall structural rigidity. Furthermore, the hollow structure optimizes material usage, reduces the overall structural weight, and provides more space for the equipment while maintaining strength and stability. The hollow structure effectively reduces unnecessary material waste.

[0053] In this embodiment, the longitudinal support column 1 has a size of 40mm to 60mm and a wall thickness of 3mm to 5mm.

[0054] In addition, this application also discloses a satellite, which includes a base plate 2, a side plate, a top plate and the above-mentioned satellite support structure. The satellite support structure is fixedly connected to the base plate 2 and is used to support the side plate and the top plate.

[0055] The base plate 2, side plates, and top plate are all structural plates used for installation on the satellite support structure. Each structural plate consists of two layers of skin covering a reinforcing core, resulting in better structural strength and support stability. The reinforcing core is an aluminum honeycomb core sandwich structure, and the skin is made of aluminum alloy or carbon fiber composite material. It is used to install equipment and is connected to the longitudinal support column 1 and the transverse support column 3. Preferably, when the skin is made of aluminum alloy, its thickness is 0.3 mm; when the skin is made of carbon fiber composite material, its thickness is 0.5 mm. The thickness of the reinforcing core is 20 mm to 30 mm.

[0056] The above are merely specific embodiments of this utility model, but the scope of protection of this utility model is not limited thereto. Those skilled in the art should understand that this utility model includes, but is not limited to, the contents described in the accompanying drawings and the specific embodiments above. Any modifications that do not depart from the functional and structural principles of this utility model will be included within the scope of the claims.

Claims

1. A satellite support structure for fixing to the base plate (2) of a satellite, characterized in that, The support structure includes a fixing unit (4), a longitudinal support column (1), and a transverse support column (3). The base plate (2) is used to support the longitudinal support column (1). The fixing unit (4) is fixed on the longitudinal support column (1) and cooperates with the transverse support column (3) for fixation. The longitudinal support column (1) is detachably connected to the transverse support column (3) through the fixing unit (4). The included angle between the longitudinal support column (1) and the transverse support column (3) can be adjusted.

2. The satellite support structure according to claim 1, characterized in that, The fixing unit (4) includes a boss (41) and a fixing member (42). The boss (41) is located on the side wall of the longitudinal support column (1) and protrudes from the longitudinal support column (1). The boss (41) has a receiving space (43) formed inside. The receiving space (43) has an opening at one end away from the longitudinal support column (1). The fastener (42) is disposed in the receiving space (43). One end of the fastener (42) is connected to the opening. The extension direction of the fastener (42) is the same as the extension direction of the transverse support column (3) and is used to cooperate with the transverse support column (3) for fixation.

3. The satellite support structure according to claim 2, characterized in that, The open end of the boss (41) forms a fixing surface for cooperating and fixing with the transverse support column (3). The fixing surface is in contact with the end of the transverse support column (3). The fixing surface forms an angle with the side wall of the longitudinal support column (1). The angle can be changed.

4. The satellite support structure according to claim 2, characterized in that, The transverse support column (3) includes a column body (31) and at least one mounting part (32). The mounting part (32) is disposed at the end of the column body (31) and protrudes from the column body (31). The mounting part (32) has mounting holes (33) formed on it. The mounting holes (33) correspond one-to-one with the fixing unit (4) and are used to cooperate with the fixing unit (4) for fixing.

5. The satellite support structure according to claim 4, characterized in that, The number of mounting parts (32) is two, and the two mounting parts (32) are arranged opposite to each other on both sides of the transverse support column (3).

6. The satellite support structure according to claim 5, characterized in that, The two mounting portions (32) are arranged along the extension direction of the longitudinal support column (1).

7. The satellite support structure according to claim 1, characterized in that, The longitudinal support column (1) includes two connecting parts (11), which protrude from the surface of the longitudinal support column (1). The longitudinal support column (1) can be fixedly connected to the base plate (2) through one of the connecting parts (11).

8. The satellite support structure according to claim 7, characterized in that, A plurality of connection holes (12) are formed on the connection portion (11) away from the base plate (2), the connection holes (12) being used to support the longitudinal support column (1) during launch.

9. The satellite support structure according to any one of claims 1-8, characterized in that, The longitudinal support column (1) is a polygonal hollow column, and the side edge of the longitudinal support column (1) extends beyond the edge of the transverse support column (3) to which it is fixedly connected.

10. A satellite, characterized in that, The satellite includes a base plate (2), a side plate, a top plate, and a satellite support structure as described in any one of claims 1 to 9. The satellite support structure is fixedly connected to the base plate (2) and is used to support the side plate and the top plate.

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