Thin-walled multi-rib structure aluminum alloy satellite propulsion module

Abstract

The present application relates to the field of aerospace technology, and in particular to a thin-walled multi-ribbed aluminum alloy satellite propulsion module, comprising a main bearing cylinder, an upper end frame, a lower end frame, a flange, and a skin; the upper end frame and the lower end frame are respectively located at both ends of the main bearing cylinder, the flange is located on the side wall of the main bearing cylinder, and the skin is arranged outside the outer wall of the main bearing cylinder; wherein the main bearing cylinder, the upper end frame, the lower end frame, the flange and the skin are integrally formed. The present application has the effect of effectively reducing the manufacturing difficulty of complex parts of special-shaped structures, reducing the number of formed parts, improving the mechanical properties of the structure, shortening the production cycle, and lightweighting the satellite structure.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a thin-walled multi-ribbed aluminum alloy satellite propulsion cabin. Background Art

[0002] The satellite propulsion module is a direct embodiment of the satellite propulsion system, which is used for satellite orbit control, orbit correction, orbit maintenance and position maintenance, rendezvous and docking, attitude control, etc. The complex structural configuration of the satellite propulsion module components leads to a relatively increased complexity of its processing technology, especially the connecting parts, which have high requirements for riveting and welding processes and have some hidden dangers. The main processing method used for the components of the traditional satellite propulsion module is the material removal method, which is easy to waste materials and increase production costs. The formulation of the traditional processing technology plan and the actual production process both take a long time, making the manufacturing efficiency very low and increasing the time cost. At the same time, there are many irregularly shaped parts in the satellite propulsion module. It is difficult to guarantee the functional requirements of the product using traditional subtractive processing technology, and sometimes it is even impossible to process. Summary of the invention

[0003] In order to effectively reduce the manufacturing difficulty of complex parts with special-shaped structures, reduce the number of formed parts, improve the mechanical properties of the structure, shorten the production cycle, and lightweight the satellite structure, the present application provides a thin-walled multi-rib structure aluminum alloy satellite propulsion cabin.

[0004] The thin-walled multi-ribbed aluminum alloy satellite propulsion cabin provided in this application adopts the following technical solution:

[0005] A thin-walled multi-ribbed aluminum alloy satellite propulsion module, including a main bearing cylinder, an upper end frame, a lower end frame, a flange, and a skin;

[0006] The upper end frame and the lower end frame are respectively located at two ends of the main bearing cylinder, the flange is located on the main bearing cylinder, and the skin is arranged outside the outer wall of the main bearing cylinder;

[0007] Wherein, the main bearing cylinder, the upper end frame, the lower end frame, the flange and the skin are integrally formed.

[0008] By adopting the above technical solution, in the traditional splicing structure, the connection parts may experience stress concentration due to problems such as loose bolts and welding defects. The one-piece molding design eliminates connection gaps or weak connection links between the components, and can evenly distribute the external load on the entire structure. When subjected to axial tension or pressure, the force can be smoothly transmitted from the main load-bearing cylinder to the upper and lower end frames, and no stress mutation will occur at the joint of the components, thereby effectively improving the overall bearing capacity of the structure, and being able to withstand greater external forces without being easily damaged; compared with the structure assembled from multiple parts, the one-piece molding technology can avoid the extra weight caused by connecting components (such as bolts, nuts and other connectors), and the one-piece molding process can optimize the distribution of materials according to the actual stress conditions; since there are no connection gaps, the one-piece molded structure can effectively prevent the leakage of gas or liquid.

[0009] Preferably, the flange is used to install a fuel tank, and at least one flange is provided on the main bearing cylinder.

[0010] By adopting the above technical solution, at least one flange is provided to flexibly install the fuel tank according to the specific needs of the satellite propulsion system. For satellites with different mission requirements, the number and size of their fuel tanks may be different. If it is a satellite performing a short-term mission, it may only need to install a relatively small fuel tank. At this time, one flange can meet the installation requirements; for large satellites that are in orbit for a long time and require multiple orbital maneuvers, multiple fuel tanks can be installed through multiple flanges, thereby increasing the fuel storage capacity to meet complex orbital control and attitude adjustment tasks. The flange can effectively transfer loads such as the weight of the fuel tank and the inertial force generated during the flight to the main bearing cylinder.

[0011] Preferably, the flanges are passed through the side walls of the main bearing cylinder and the skin, and the sizes of the multiple flanges are the same.

[0012] By adopting the above technical solution, multiple flanges of the same size means that the same mold can be used to produce the flanges during the manufacturing process. For components such as satellite propulsion modules that require extremely high precision, reducing the number of molds can reduce production costs and manufacturing difficulty. During the casting or forging process of aluminum alloys, there is no need to design multiple complex molds for flanges of different sizes, thereby shortening the production cycle and improving production efficiency.

[0013] Preferably, the center of the flange is located at the midline of the main bearing cylinder in the height direction, and a plurality of the flanges are evenly distributed along the circumference of the outer wall of the main bearing cylinder.

[0014] By adopting the above technical solution, multiple flanges are evenly distributed along the circumference of the outer wall of the main bearing cylinder, which can ensure that the force generated by external equipment such as fuel tanks is evenly distributed in the circumferential direction of the main bearing cylinder, avoiding deformation such as twisting of the main bearing cylinder, thereby improving the stability of the structure.

[0015] Preferably, four flanges are evenly and symmetrically arranged along the circumferential direction of the outer wall of the main bearing cylinder, and the connection between the flange and the main bearing cylinder is evenly transitioned according to the curvature of the main bearing cylinder.

[0016] By adopting the above technical solution and setting four uniformly symmetrical flanges, the force generated by the equipment installed thereon (such as a fuel tank) can be evenly distributed in the circumferential direction of the main bearing cylinder, thus avoiding excessive local stress due to force concentration, effectively improving the circumferential bearing capacity of the main bearing cylinder, and ensuring that the structure remains stable in a complex mechanical environment.

[0017] Preferably, the flange is located on the inner wall of the main bearing cylinder.

[0018] By adopting the above technical solution, in the space environment, the satellite may be affected by external factors such as the impact of micrometeorites, collision of space debris or solar radiation. The outer wall of the main load-bearing cylinder directly bears these potential threats, while the flange located on the inner wall and the equipment connected to it can be protected from direct interference from these external factors, thereby reducing the risk of equipment damage and improving the safety and reliability of the satellite propulsion system. During the assembly and testing process before the satellite launch, or during orbital service and maintenance operations, the internal flange layout can reduce the possibility of damage to the flange and connected equipment due to human operating errors or accidental collision of tools.

[0019] Preferably, at least four mounting holes are provided on the flange, and the plurality of mounting holes are evenly arranged with the center of the flange as the axis.

[0020] By adopting the above technical solution, during the satellite launch process, the fuel tank will be subjected to huge axial overload and lateral force generated by vibration. When the flange is used to install equipment such as the fuel tank, at least 4 evenly arranged mounting holes can evenly disperse the connection force on the flange. The fuel tank is fixed to the flange using bolts and other connectors to ensure that these forces can be evenly transmitted to the flange through the mounting holes, and then to the main bearing cylinder. This uniform force transmission method can avoid excessive local stress caused by too few connection points or uneven distribution, and effectively enhance the stability of the connection.

[0021] Preferably, the center line of the flange in the thickness direction coincides with the center line of the main bearing cylinder in the height direction.

[0022] By adopting the above technical solution, when the center line of the flange in the thickness direction coincides with the center line of the main bearing cylinder in the height direction, the axial force generated by the equipment installed on the flange (such as a fuel tank) can be evenly transmitted through the main bearing cylinder. These axial forces will be symmetrically distributed in the upper and lower parts of the main bearing cylinder, avoiding additional bending moments caused by eccentric force, ensuring that the main bearing cylinder can stably bear the load when subjected to axial force, and effectively improving the stability of the structure in the axial direction.

[0023] Preferably, the height of the skin is the same as the height of the main bearing cylinder, the upper end frame connects the skin and the main bearing cylinder, and the lower end frame connects the skin and the main bearing cylinder.

[0024] By adopting the above technical solutions, in the space environment, the impact of micrometeoroids, solar radiation and high-energy particle bombardment may cause damage to the internal equipment of the satellite. The complete skin structure is like a solid shield to block these external threats and ensure the safety of the internal equipment. The upper and lower end frames connect the skin and the main bearing cylinder, which helps to achieve good sealing.

[0025] Preferably, the upper end frame and the lower end frame have the same size, and the circumferential length of the skin determines the width of the upper end frame and the lower end frame.

[0026] By adopting the above technical solution, the upper end frame and the lower end frame have the same size. This symmetrical design allows the force to be evenly distributed at the upper and lower ends when subjected to axial loads (such as the force generated by acceleration during satellite launch). The axial force borne by the main load-bearing cylinder can be symmetrically transmitted to the skin through the upper end frame and the lower end frame of the same size, avoiding structural deformation or local stress concentration caused by uneven force at the upper and lower ends.

[0027] In summary, the present application includes at least one of the following beneficial technical effects:

[0028] 1. In traditional splicing structures, stress concentration may occur at the connection parts due to problems such as loose bolts and welding defects. The one-piece design eliminates connection gaps or weak connection links between the components, and can evenly distribute the external load on the entire structure. When subjected to axial tension or pressure, the force can be smoothly transmitted from the main load-bearing cylinder to the upper and lower end frames, and no stress mutation will occur at the joint of the components, thereby effectively improving the overall bearing capacity of the structure, and being able to withstand greater external forces without being easily damaged; compared with structures assembled from multiple parts, the one-piece molding technology can avoid the extra weight caused by connecting components (such as bolts, nuts and other connectors), and the one-piece molding process can optimize the distribution of materials according to actual stress conditions; since there are no connection gaps, the one-piece molded structure can effectively prevent gas or liquid leakage. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This is a schematic diagram of the structure of Example 1 in the embodiments of the present application;

[0030] Figure 2 It is a structural schematic diagram of Example 2 in the embodiments of the present application.

[0031] Explanation of the accompanying reference numerals: 1. upper end frame; 2. main load-bearing cylinder; 3. flange; 4. skin; 5. lower end frame. DETAILED DESCRIPTION

[0032] The following is combined with Figure 1-2 This application is described in further detail.

[0033] The embodiment of the present application discloses a thin-walled multi-ribbed aluminum alloy satellite propulsion cabin. The thin-walled multi-ribbed aluminum alloy satellite propulsion cabin includes a main bearing cylinder 2, an upper end frame 1, a lower end frame 5, a flange 3, and a skin 4; the upper end frame 1 and the lower end frame 5 are respectively located at both ends of the main bearing cylinder 2, the flange 3 is located on the main bearing cylinder 2, and the skin 4 is arranged on the outer wall of the main bearing cylinder 2; wherein, the main bearing cylinder 2, the upper end frame 1, the lower end frame 5, the flange 3 and the skin 4 are integrally formed. In the traditional splicing structure, the connection part may have stress concentration due to problems such as loose bolts and welding defects. The integrally formed design makes it possible to have no connection gaps or weak connection links between the various components, and can evenly distribute the external load on the entire structure. When subjected to axial tension or pressure, the force can be smoothly transmitted from the main bearing cylinder 2 to the upper and lower end frames 5, and no stress mutation will occur at the joint of the components, thereby effectively improving the bearing capacity of the entire structure, and being able to withstand greater external forces without being easily damaged.

[0034] The flange 3 is used to install the fuel tank, and at least one flange 3 is provided on the main bearing cylinder 2. The provision of at least one flange 3 allows the fuel tank to be flexibly installed according to the specific needs of the satellite propulsion system. For satellites with different mission requirements, the number and size of their fuel tanks may be different. If it is a satellite performing a short-term mission, it may only need to install a relatively small fuel tank, and at this time, one flange 3 can meet the installation requirements; and for large satellites that are in orbit for a long time and require multiple orbital maneuvers, multiple fuel tanks can be installed through multiple flanges 3, thereby increasing the fuel storage capacity and meeting complex orbital control and attitude adjustment tasks. The flange 3 can effectively transfer the weight of the fuel tank and the inertial force generated during the flight and other loads to the main bearing cylinder 2.

[0035] The height of the skin 4 is the same as that of the main bearing cylinder 2. The upper frame 1 connects the skin 4 and the main bearing cylinder 2, and the lower frame 5 connects the skin 4 and the main bearing cylinder 2. In the space environment, the impact of micrometeoroids, solar radiation, and high-energy particle bombardment may cause damage to the internal equipment of the satellite. The complete skin 4 structure is like a solid shield, blocking these external threats and ensuring the safety of the internal equipment. The upper and lower frames 5 connect the skin 4 and the main bearing cylinder 2, which helps to achieve good sealing.

[0036] Preferably, the upper end frame 1 and the lower end frame 5 are of the same size, and the circumferential length of the skin 4 determines the width of the upper end frame 1 and the lower end frame 5. The upper end frame 1 and the lower end frame 5 are of the same size. This symmetrical design allows the force to be evenly distributed at the upper and lower ends when bearing axial loads (such as the force generated by acceleration during satellite launch). The axial force borne by the main bearing cylinder 2 can be symmetrically transmitted to the skin 4 through the upper end frame 1 and the lower end frame 5 of the same size, avoiding structural deformation or local stress concentration caused by uneven force at the upper and lower ends; when facing torsional forces (such as torque generated during satellite attitude adjustment), the upper end frame 1 and the lower end frame 5 of the same size can also provide balanced resistance, and can work together when resisting torsional forces, effectively reducing torsional deformation of the structure.

[0037] Example 1

[0038] Reference Figure 1 The flange 3 is inserted through the side wall of the main bearing cylinder 2 and the skin 4, and the sizes of the multiple flanges 3 are the same. The same size of the multiple flanges 3 means that the same mold can be used to produce the flanges 3 during the manufacturing process. For components such as satellite propulsion modules that require extremely high precision, reducing the number of molds can reduce production costs and manufacturing difficulties. In the casting or forging process of aluminum alloys, there is no need to design multiple complex molds for flanges 3 of different sizes, thereby shortening the production cycle and improving production efficiency.

[0039] In the satellite assembly workshop, workers can use the same tools and installation processes to install multiple flanges 3, reducing assembly errors that may be caused by size differences; when multiple flanges 3 are of the same size and are inserted through the side walls of the main load-bearing cylinder 2 and the skin 4, they can evenly share the weight and force of external equipment such as fuel tanks, and when subjected to complex external forces (such as thrust during orbit adjustment, small impacts in the space environment, etc.), multiple flanges 3 of the same size can work together.

[0040] Optionally, the center of the flange 3 is located at the midline of the main bearing cylinder 2 in the height direction, and multiple flanges 3 are evenly distributed along the circumference of the outer wall of the main bearing cylinder 2. Multiple flanges 3 are evenly distributed along the circumference of the outer wall of the main bearing cylinder 2, which can ensure that the force generated by external equipment such as the fuel tank is evenly distributed in the circumferential direction of the main bearing cylinder 2. When the fuel tank is installed on the flange 3 and stores fuel, the weight of the fuel will exert a downward pulling force on the flange 3. If the circumferential distribution of the flange 3 is uneven, it will cause the main bearing cylinder 2 to be subjected to uneven forces in the circumferential direction, which may cause structural deformation or excessive local stress. The evenly distributed flanges 3 can balance these forces with each other in the circumferential direction, avoid deformation such as distortion of the main bearing cylinder 2, and thus improve the stability of the structure.

[0041] Optionally, four flanges 3 are evenly and symmetrically arranged along the circumferential direction of the outer wall of the main bearing cylinder 2, and the connection between the flange 3 and the main bearing cylinder 2 is evenly transitioned according to the curvature of the main bearing cylinder 2. The arrangement of four evenly and symmetrical flanges 3 can evenly distribute the force generated by the equipment (such as a fuel tank) installed thereon in the circumferential direction of the main bearing cylinder 2, avoiding excessive local stress caused by force concentration, effectively improving the circumferential bearing capacity of the main bearing cylinder 2, and ensuring that the structure remains stable in a complex mechanical environment. At the same time, due to the symmetrical positions of the four flanges 3, when the weight of the fuel tank or the thrust generated during the propulsion process acts on the flange 3, these axial forces can be evenly transmitted through the main bearing cylinder 2. Compared with the asymmetric arrangement, this symmetrical structure will not generate additional bending moment, ensuring the balance and stability of the main bearing cylinder 2 when subjected to axial force, so that the main bearing cylinder 2 can better withstand the axial load of the satellite during launch and orbital operation.

[0042] Example 2

[0043] Reference Figure 2 , flange 3 is located on the inner wall of the main bearing cylinder 2. In the space environment, the satellite may be affected by external factors such as the impact of micrometeoroids, collision of space debris or solar radiation. The outer wall of the main bearing cylinder 2 directly bears these potential threats, while the flange 3 located on the inner wall and the equipment connected thereto can be protected from direct interference from these external factors, reducing the risk of equipment damage and improving the safety and reliability of the satellite propulsion system; during the assembly and testing process before the satellite launch, or during orbital service and maintenance operations, the internal flange 3 layout can reduce the possibility of damage to the flange 3 and the connected equipment due to human operating errors or accidental collisions with tools.

[0044] The center line of the flange 3 in the thickness direction coincides with the center line of the main bearing cylinder 2 in the height direction. The axial overload generated by acceleration will act on the fuel tank, and then be transmitted to the main bearing cylinder 2 through the flange 3. When the center line of the flange 3 in the thickness direction coincides with the center line of the main bearing cylinder 2 in the height direction, the axial force generated by the equipment installed on the flange 3 (such as the fuel tank) can be evenly transmitted through the main bearing cylinder 2. These axial forces will be symmetrically distributed in the upper and lower parts of the main bearing cylinder 2, avoiding additional bending moments caused by eccentric force, ensuring that the main bearing cylinder 2 can stably bear the load when subjected to axial force, and effectively improving the stability of the structure in the axial direction.

[0045] Optionally, when the fuel tank generates circumferential force due to its own weight, internal fuel sloshing or external interference, the flange 3, as a connecting structure, can evenly transfer these forces to the main bearing cylinder 2 in the circumferential direction. Because the design of the coincidence of the center lines makes the installation position of the flange 3 on the main bearing cylinder 2 more symmetrical, the transmission of force in the circumferential direction is also more balanced, which will not cause the main bearing cylinder 2 to be subjected to excessive local force in the circumferential direction, thereby enhancing the circumferential stability of the entire structure.

[0046] Optionally, at least four mounting holes are provided on the flange 3, and the multiple mounting holes are evenly arranged with the center of the flange 3 as the axis. During the satellite launch process, the fuel tank will be subjected to huge axial overload and lateral force generated by vibration. When the flange 3 is used to install equipment such as the fuel tank, at least four evenly arranged mounting holes can evenly disperse the connection force on the flange 3. The fuel tank is fixed to the flange 3 using bolts and other connectors, which can ensure that these forces can be evenly transmitted to the flange 3 through the mounting holes, and then transmitted to the main bearing cylinder 2. This uniform force transmission method can avoid excessive local stress caused by too few connection points or uneven distribution, and effectively enhance the stability of the connection.

[0047] The implementation principle of the embodiment of the present application is as follows: in a traditional splicing structure, stress concentration may occur at the connection part due to problems such as loose bolts and welding defects. The one-piece design eliminates connection gaps or weak connection links between the components, and can evenly distribute the external load on the entire structure. When subjected to axial tension or pressure, the force can be smoothly transmitted from the main load-bearing cylinder 2 to the upper and lower end frames 5, and no stress mutation will occur at the joint of the components, thereby effectively improving the overall bearing capacity of the structure, and being able to withstand greater external forces without being easily damaged; compared with a structure assembled from multiple parts, the one-piece molding technology can avoid the extra weight caused by connecting components (such as bolts, nuts and other connectors), and the one-piece molding process can optimize the distribution of materials according to actual stress conditions; since there are no connection gaps, the one-piece molded structure can effectively prevent the leakage of gas or liquid.

[0048] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. Thin-walled multi-ribbed aluminum alloy satellite propulsion cabin, characterized in that: include: A main bearing cylinder (2), an upper end frame (1), a lower end frame (5), a flange (3), and a skin (4); The upper end frame (1) and the lower end frame (5) are respectively located at two ends of the main bearing cylinder (2), the flange (3) is located on the main bearing cylinder (2), and the skin (4) is arranged outside the outer wall of the main bearing cylinder (2); Wherein, the main bearing cylinder (2), the upper end frame (1), the lower end frame (5), the flange (3) and the skin (4) are integrally formed.

2. The thin-walled multi-ribbed aluminum alloy satellite propulsion module according to claim 1 is characterized in that: The flange (3) is used to install the fuel storage tank, and at least one flange (3) is provided on the main bearing cylinder (2).

3. The thin-walled multi-ribbed aluminum alloy satellite propulsion module according to claim 2 is characterized in that: The flange (3) is inserted through the side walls of the main bearing cylinder (2) and the skin (4), and the sizes of the plurality of flanges (3) are the same.

4. The thin-walled multi-ribbed aluminum alloy satellite propulsion module according to claim 3 is characterized by: The center of the flange (3) is located at the midline of the main bearing cylinder (2) in the height direction, and a plurality of flanges (3) are evenly distributed along the circumference of the outer wall of the main bearing cylinder (2).

5. The thin-walled multi-ribbed aluminum alloy satellite propulsion module according to claim 3 is characterized by: Four flanges (3) are evenly and symmetrically arranged along the circumferential direction of the outer wall of the main bearing cylinder (2); the connection between the flange (3) and the main bearing cylinder (2) is evenly transitioned according to the curvature of the main bearing cylinder (2).

6. The thin-walled multi-ribbed aluminum alloy satellite propulsion module according to claim 2 is characterized by: The flange (3) is located on the inner wall of the main bearing cylinder (2).

7. The thin-walled multi-ribbed aluminum alloy satellite propulsion module according to claim 6 is characterized by: At least four mounting holes are provided on the flange (3), and the plurality of mounting holes are evenly arranged with the center of the flange (3) as the axis.

8. The thin-walled multi-ribbed aluminum alloy satellite propulsion module according to claim 6 is characterized by: The center line of the flange (3) in the thickness direction coincides with the center line of the main bearing cylinder (2) in the height direction.

9. The thin-walled multi-rib structure aluminum alloy satellite propulsion module according to claim 1, characterized in that: The height of the skin (4) is the same as the height of the main bearing cylinder (2); the upper end frame (1) connects the skin (4) and the main bearing cylinder (2); and the lower end frame (5) connects the skin (4) and the main bearing cylinder (2).

10. The thin-walled multi-ribbed aluminum alloy satellite propulsion module according to claim 9, characterized in that: The upper end frame (1) and the lower end frame (5) have the same size, and the circumferential length of the skin (4) determines the width of the upper end frame (1) and the lower end frame (5).

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