Vibration reduction and energy absorption lightweight satellite case structure applicable to multiple working conditions

Abstract

The invention belongs to the technical field of satellite case structure design, and relates to a vibration reduction and energy absorption lightweight satellite case structure suitable for multiple working conditions. A main shell of the rib-like case is of a hollow box body structure with an opening in one side; the grid skin panel is fixedly connected with an opening of the rib-like case main shell, and a plurality of diagonal grid structures are arranged in the grid skin panel; a plurality of similar-nest-shaped supporting structures are arranged in the similar-rib type case main shell, the similar-nest-shaped supporting structures are fixedly connected, the similar-nest-shaped supporting structures are fixedly connected with a grid skin panel, a plurality of grid skin supports are arranged on the similar-nest-shaped supporting structures, and the grid skin supports are used for installing components in the satellite case; the nesting-like supporting structure is an irregular rod-shaped connecting structure obtained through topological optimization. The space utilization rate of the satellite case is remarkably improved, the vibration and impact resistance of the supporting structure is improved, light weight of the satellite case is facilitated, and the positioning precision of an assembled optical component is guaranteed.

Description

Technical Field

[0001] The present invention belongs to the technical field of satellite chassis structure design, and relates to a vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions. Background Art

[0002] In tests for evaluating and verifying the performance and reliability of equipment or systems under specific environmental conditions, vibration tests and shock tests are often carried out to simulate extreme environments such as bumps during transportation and use. The components in a satellite chassis are often relatively complex, with many designed parts, interfaces, and structural form changes. Under complex working conditions, high-precision, stable, and all-round support is required to provide a stable working environment and necessary protection measures.

[0003] The existing satellite chassis outer shell is relatively heavy, which is not conducive to installation, transportation, and use in special environments. The support structures in the satellite chassis are divided into two types: simple single brackets and integral epoxy pouring. The support structure of the simple single bracket has poor structural space utilization rate and cannot play a good role in resisting vibration and shock, resulting in poor protection of the precision devices in the chassis and only being suitable for a small number of device layout schemes; the support structure of integral epoxy pouring also has many problems, such as large weight and inconvenient carrying, etc. Both types of brackets have problems with poor positioning accuracy of multiple optical components after assembly. Summary of the Invention

[0004] The purpose of the present invention is to provide a vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions, so as to solve the technical problems of poor space utilization rate, poor vibration and shock resistance, large weight, and poor positioning accuracy of optical components after assembly in the existing satellite chassis. The present invention significantly improves the space utilization rate of the satellite chassis, improves the vibration and shock resistance of the support structure, is conducive to the lightweight of the satellite chassis, and ensures the positioning accuracy of optical components after assembly.

[0005] In order to achieve the above purpose, the present invention adopts the following technical solutions: The present invention discloses a vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions, including: A rib-like chassis main shell, which is a hollow box structure with an opening on one side; A grid skin panel, which is fixedly connected to the opening of the rib-like chassis main shell, and several body diagonal grid structures are arranged inside the grid skin panel; A nest-like support structure, several nest-like support structures are arranged inside the rib-like chassis main shell, the nest-like support structures are fixedly connected to each other, the nest-like support structures are fixedly connected to the grid skin panel, and several grid skin supports are arranged on the nest-like support structures, and the grid skin supports are used for installing the components inside the satellite chassis; The nest-like support structure is an irregular rod-shaped connection structure obtained by topological optimization according to the force conditions and the optical path inside the satellite chassis.

[0006] Furthermore, the main shell of the rib-like chassis is provided with special-shaped weight-reducing and heat-dissipating grooves and polygonal weight-reducing grooves.

[0007] Furthermore, the main shell of the rib-like chassis is provided with a number of semi-elliptical mounting bosses. The semi-elliptical mounting bosses are located at the opening of the main shell of the rib-like chassis, and the grid skin panel is connected to the semi-elliptical mounting bosses by bolts.

[0008] Furthermore, the grid skin panel is provided with a nest-like support structure mounting hole, a main shell mounting hole of the rib-like chassis, and an external interface. The nest-like support structure mounting hole is used to connect the nest-like support structure. The main shell mounting hole of the rib-like chassis is used to connect the opening of the main shell of the rib-like chassis. The external interface is used for light source input.

[0009] Furthermore, a skin is covered on the grid skin panel. The thickness of the skin is 1 mm to 5 mm, and the skin is located on the side away from the main shell of the rib-like chassis.

[0010] Furthermore, the nest-like support structure includes a base panel, a tree-branch-shaped bracket, an intermediate connector, and a mounting interface; The base panel is fixedly connected to the tree-branch-shaped bracket; The tree-branch-shaped brackets are connected by an intermediate connector; The tree-branch-shaped bracket is connected to the grid skin panel through a mounting interface, and the mounting interface is connected to the grid skin panel by bolts; The tree-branch-shaped bracket is provided with a grid skin support.

[0011] Furthermore, the tree-branch-shaped bracket is specifically as follows: A multi-branch curved rod-shaped connection structure with an irregular cross-section obtained by topological optimization according to the force conditions of the tree-branch-shaped bracket and the optical path inside the satellite chassis. The number of branches of the tree-branch-shaped bracket is 1 to 8. There is a fillet at the connection of the branches, and the fillet radius is 3 mm to 15 mm. The grid skin support is connected to three to eight branches.

[0012] Furthermore, the grid skin support is a special-shaped box-like structure with one side open. The shell of the grid skin support is filled with a body diagonal grid structure, and the outer surface of the grid skin support is covered with a skin; The grid skin support is provided with one to four external interfaces, and the external interfaces are used for light source input.

[0013] Furthermore, the body diagonal grid structure is a hexahedron structure, with the interior and six faces of the hexahedron structure being hollowed out. The vertices of the hexahedron structure are connected by rods, and the porosity of the body diagonal grid structure is 30% - 40%.

[0014] Furthermore, the spacing between the body diagonal grid structures is 7 mm - 20 mm.

[0015] Compared with the prior art, the present invention has the following beneficial effects: 1. The main shell of the rib - like chassis of the present invention is a hollow box structure with an opening on one side. The interior of the main shell of the rib - like chassis is used to arrange the nest - like support structure. The grid skin panel is fixedly connected to the opening of the main shell of the rib - like chassis. That is, the grid skin panel and the main shell of the rib - like chassis together form a closed space, which helps to protect the internal components. When an external force acts, the internal pores of the body diagonal grid structure will deform, which can absorb and disperse vibration energy, reduce the impact of vibration and shock on the equipment, and improve the anti - vibration and shock performance of the chassis. Compared with the traditional solid structure, the body diagonal grid structure has a lower mass while maintaining the structural strength. The grid skin support is used to install the components inside the satellite chassis. The nest - like support structure is integrally formed, avoiding errors caused by multiple component assemblies or tooling, and ensuring the position accuracy of the components. Secondly, the nest - like support structure is an irregular rod - shaped connection structure obtained by topological optimization according to the force conditions and the optical path conditions inside the satellite chassis. The nest - like support structure is set according to the structural force conditions, making full use of materials and ensuring the structural stiffness and strength. This structure not only facilitates the arrangement of components, can make full use of the internal space of the chassis, reduce the use of redundant materials, and better achieve the weight reduction effect. That is, the present invention significantly improves the poor space utilization rate of the satellite chassis, improves the anti - vibration and shock performance of the support structure, is conducive to the lightweight of the satellite chassis, and ensures the positioning accuracy of the optical components after assembly.

[0016] 2. The main shell of the rib - like chassis of the present invention is provided with special - shaped weight - reducing and heat - dissipating grooves and polygonal weight - reducing grooves, which achieve the effects of weight reduction and enhanced heat dissipation while ensuring the structural strength.

[0017] 3. The body diagonal grid structure of the present invention is a hexahedron structure, with the interior and six faces of the hexahedron structure being hollowed out. The vertices of the hexahedron structure are connected by rods, which improves the anti - vibration and shock performance of the support structure and is conducive to the lightweight of the satellite chassis. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 Schematic diagram of the main shell of the rib - like chassis of the present invention; Figure 2 Assembly drawing of the satellite chassis of the present invention; Figure 3Schematic diagram of the satellite chassis assembly after hiding the main chassis housing of the present invention; Figure 4 Cross-sectional view of the grid skin panel of the present invention; Figure 5 Partial cross-sectional schematic diagram of the grid skin panel of the present invention; Figure 6 Schematic diagram of a single body diagonal grid structure of the present invention; Figure 7 Top view of the satellite chassis assembly after hiding the main chassis housing of the present invention; Figure 8 Schematic diagram of the third type of nest-shaped support structure of an embodiment of the present invention; Figure 9 Schematic diagram of the second type of nest-shaped support structure of an embodiment of the present invention; Figure 10 Schematic diagram of the first type of nest-shaped support structure of an embodiment of the present invention.

[0019] Wherein: 1. Rib-like main chassis housing; 2. Grid skin panel; 3. Nest-shaped support structure; 1-1. Special-shaped weight-reducing and heat-dissipating groove; 1-2. Polygonal weight-reducing groove; 1-3. Semi-waist-shaped mounting boss; 2-1. Body diagonal grid structure; 2-2. Nest-shaped support structure mounting hole; 2-3. Rib-like main chassis housing mounting hole; 2-4. External interface; 3-1. Base panel; 3-2. Fork-shaped bracket; 3-3. Grid skin support; 3-4. Intermediate connecting piece; 3-5. Mounting interface; 3-6. First type of nest-shaped support structure; 3-7. Second type of nest-shaped support structure; 3-8. Third type of nest-shaped support structure. Detailed implementation manners

[0020] In order to enable those skilled in the art to better understand the solution of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present invention.

[0021] It should be noted that the terms "first", "second", etc. in the specification of the present invention and the above-mentioned drawings are used to distinguish similar objects, and do not necessarily have to be used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged under appropriate circumstances, so that the embodiments of the present invention described here can be implemented in an order other than those illustrated or described here. In addition, the terms "comprising" and "having" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product or device comprising a series of steps or units does not necessarily have to be limited to those steps or units clearly listed, but may include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0022] The present invention will be further described in detail below with reference to the accompanying drawings: See Figure 1 , the present invention discloses a vibration damping, energy absorption and lightweight satellite chassis structure applicable to multiple working conditions, including: a rib-like chassis main body 1, a grid skin panel 2 and a nest-like support structure 3; The rib-like chassis main body 1 is a hollow box structure with an opening on one side, and the inside of the rib-like chassis main body 1 is used to arrange the nest-like support structure 3.

[0023] The grid skin panel 2 is fixedly connected to the opening of the rib-like chassis main body 1, that is, the grid skin panel 2 and the rib-like chassis main body 1 together form a closed space, which helps to protect the internal components. The inside of the grid skin panel 2 is provided with a number of body diagonal grid structures 2-1. When the internal pores of the body diagonal grid structure 2-1 are subjected to external forces, they will deform, which can absorb and disperse vibration energy, reduce the impact of vibration and impact on the equipment, improve the anti-vibration and impact performance of the chassis. Compared with the traditional solid structure, the body diagonal grid structure 2-1 has a lower mass while maintaining the structural strength.

[0024] The nest-like support structures 3 are fixedly connected to each other, the nest-like support structures 3 are fixedly connected to the grid skin panel 2, and a number of grid skin supports 3-3 are provided on the nest-like support structures 3. The grid skin supports 3-3 are used to install the components inside the satellite chassis. The nest-like support structure 3 is integrally formed, avoiding errors caused by multiple component assemblies or toolings, and ensuring the position accuracy of the components.

[0025] The nest-like support structure 3 is an irregular rod-shaped connection structure obtained by topology optimization according to the force conditions and the optical path conditions inside the satellite chassis. The nest-like support structure 3 is set according to the structural force conditions, making full use of the material and ensuring the structural stiffness and strength. This structure not only facilitates the arrangement of components, can make full use of the internal space of the chassis, reduce the use of redundant materials, and better achieve the weight reduction effect.

[0026] Example 1: Referring to Figure 1 , this embodiment discloses a vibration damping, energy absorption and lightweight satellite chassis structure applicable to multiple working conditions, including: a rib-like chassis main body 1, a grid skin panel 2 and a nest-like support structure 3; Referring to Figure 1 , the rib-like chassis main body 1 is a hollow box structure with an opening on one side; The rib-like chassis main body 1 is provided with special-shaped weight-reducing and heat-dissipating grooves 1-1 and polygonal weight-reducing grooves 1-2, which can reduce weight and enhance heat dissipation while ensuring structural strength.

[0027] The rib-like chassis main body 1 is provided with a number of semi-elliptical mounting bosses 1-3. The semi-elliptical mounting bosses 1-3 are located at the opening of the rib-like chassis main body 1, and the grid skin panel 2 is connected to the semi-elliptical mounting bosses 1-3 by bolts.

[0028] Referring to Figure 2 and Figure 3 , the grid skin panel 2 is fixedly connected to the opening of the rib-like chassis main body 1; Referring to Figure 4 , the grid skin panel 2 is provided with nest-like support structure mounting holes 2-2, rib-like chassis main body mounting holes 2-3 and external interfaces 2-4. The nest-like support structure mounting holes 2-2 are used to connect the nest-like support structure 3, the rib-like chassis main body mounting holes 2-3 are used to connect the opening of the rib-like chassis main body 1, and the external interfaces 2-4 are used for light source input.

[0029] Preferably, the external interface 2-4 is rectangular, there is one external interface 2-4, the external interface 2-4 is located at the geometric center of the grid skin panel 2, both the nest-like support structure mounting holes 2-2 and the rib-like chassis main body mounting holes 2-3 are four, and the four nest-like support structure mounting holes 2-2 and the four rib-like chassis main body mounting holes 2-3 are symmetrically arranged about the center of the external interface 2-4.

[0030] The grid skin panel 2 is covered with a skin, and the thickness of the skin is 1 mm to 5 mm. The skin is located on the side away from the rib-like chassis main body 1.

[0031] Referring to Figure 5 , the inside of the grid skin panel 2 is provided with a number of body diagonal grid structures 2-1; Referring to Figure 6, the body diagonal grid structure 2-1 is a hexahedron structure, and the interior and six faces of the hexahedron structure are hollowed out. The vertices of the hexahedron structure are connected by rods. The porosity of the body diagonal grid structure 2-1 is 30% - 40%, which improves the anti-vibration and impact performance of the support structure and is beneficial to the lightweight of the satellite chassis.

[0032] The spacing between the body diagonal grid structures 2-1 is 7 mm - 20 mm, which improves the poor anti-vibration and impact performance of the support structure while ensuring the structural strength.

[0033] See Figure 2 and Figure 7 , several nest-like support structures 3 are arranged inside the rib-like chassis main shell 1. The nest-like support structures 3 are fixedly connected to each other. The nest-like support structures 3 are fixedly connected to the grid skin panel 2. Several grid skin supports 3-3 are provided on the nest-like support structures 3, and the grid skin supports 3-3 are used to install the components inside the satellite chassis.

[0034] See Figure 8 and Figure 9 , the nest-like support structure 3 includes a base panel 3-1, a tree-like bracket 3-2, an intermediate connector 3-4 and a mounting interface 3-5; The base panel 3-1 is fixedly connected to the tree-like bracket 3-2; The tree-like brackets 3-2 are connected by an intermediate connector 3-4; The tree-like bracket 3-2 is connected to the grid skin panel 2 through the mounting interface 3-5, and the mounting interface 3-5 and the grid skin panel 2 are connected by bolts.

[0035] The nest-like support structure 3 is an irregular rod-shaped connection structure obtained by topological optimization according to the force condition and the optical path condition inside the satellite chassis. Specifically, it is an irregular cross-section multi-branch curved rod-shaped connection structure obtained by topological optimization according to the force condition of the tree-like bracket 3-2 and the optical path condition inside the satellite chassis. The branches of the tree-like bracket 3-2 are 1 to 8, and fillets are provided at the joints of the branches, and the fillet radius is 3 mm - 15 mm.

[0036] See Figure 10 , the tree-like bracket 3-2 is provided with a grid skin support 3-3, and the grid skin support 3-3 is connected to three to eight branches; The grid skin support 3-3 is a special-shaped box-like structure with an opening on one side. The shell of the grid skin support 3-3 is filled with the body diagonal grid structure 2-1, and the outer surface of the grid skin support 3-3 is covered with skin; One to four external interfaces 2-4 are provided on the grid skin support 3-3, and the external interfaces 2-4 are used for light source input.

[0037] Example Two: Refer to Figure 1 , this example discloses a vibration damping, energy absorption and lightweight satellite chassis structure applicable to multiple working conditions, including a rib-like chassis main body, a grid skin panel and a plurality of nest-like support structures.

[0038] After the rib-like chassis main body 1 and the grid skin panel 2 are assembled, they form the satellite chassis outer shell; after fixing the components to a single nest-like support structure 3, all the nest-like support structures 3 are assembled into a whole using bolts and then installed into the satellite rib-like chassis main body 1.

[0039] The rib-like chassis main body 1 is an irregular hollow box structure with an opening on one side. The outer wall surfaces of the upper and lower surfaces are provided with special-shaped weight-reducing and heat-dissipating grooves 1-1, the outer wall surfaces of the left and right surfaces and the bottom surface are provided with polygonal weight-reducing grooves, and a semi-waist-shaped mounting boss 1-3 with threaded holes is provided at the opening.

[0040] The grid skin panel 2 is a box cover plate, with a variable-spacing body diagonal grid structure 2-1 inside and a skin covered outside. The grid skin panel 2 is provided with round holes, and the round holes are external interfaces 2-4.

[0041] The nest-like support structure 3 is integrally formed based on additive manufacturing and is a three-dimensional wrapping support structure composed of a base panel 3-1, a plurality of tree-branch-shaped brackets 3-2, a plurality of grid skin supports 3-3, a plurality of intermediate connectors 3-4 and a plurality of mounting interfaces 3-5; the base panel 3-1 is a basic support structure connecting the tree-branch-shaped brackets 3-2; the tree-branch-shaped brackets 3-2 are obtained through topology optimization calculation according to the force conditions of the tree-branch-shaped brackets 3-2 and the optical paths inside the satellite chassis. The tree-branch-shaped brackets 3-2 are multi-branch curved rod-shaped connection structures with irregular cross-sections and are used to connect the grid skin supports 3-3, the intermediate connectors 3-4 and the mounting interfaces 3-5; the grid skin supports 3-3 are special-shaped box structures with an opening on one side, filled with a body diagonal grid structure 2-1 inside and covered with a skin outside, and the grid skin supports 3-3 are used to fix the components inside the chassis; the intermediate connectors 3-4 are boss structures with threaded holes or through holes and are used for connecting between multiple nest-like support structures; the external mounting interface 3-5 is a round boss with threaded holes, and the whole nest-like support structure is installed on the grid skin panel 2.

[0042] The number of the above-mentioned nest-like support structures 3 is 2 to 4.

[0043] The shape of the polygonal weight-reducing groove 1-2 can be a random combination of square, rectangle, pentagon or hexagon.

[0044] The spacing of the body diagonal grid structure 2-1 of the grid skin panel 2 is 7 mm to 20 mm, and the skin thickness is 1 mm to 5 mm.

[0045] The above-mentioned body diagonal grid structure 2-1 is a cube where the diagonal rods intersect. The side length of the cube is 2 mm to 8 mm. The porosity of the body diagonal grid structure 2-1 is 30% to 40%. There are corners inside the body diagonal grid structure 2-1, and the fillets at the corners are 0.2 mm to 0.5 mm.

[0046] The branches of the tree-shaped bracket 3-2 generally have 1 to 8. The curved rod is a variable cross-section curved rod structure. The shape of the curved rod is adjusted according to the load-bearing conditions and external working conditions. The cross-sectional shape of the curved rod is nearly circular or nearly elliptical. The long side dimension of the cross-section is 1.5 mm to 20 mm. The mating surface between the two nest-like support structures 3 is treated by flattening. Fillet transitions are provided at the branch joints, and the fillet radius is 3 mm to 15 mm.

[0047] The grid skin support 3-3 is in the shape of an element envelope with a certain thickness. The thickness is 3 mm to 5 mm and is fixed by 3 to 8 branches. There are external interfaces 2-4 opened on one to four sides.

[0048] The number of the intermediate connectors 3-4 of the nest-like support structure 3 is 4 to 8.

[0049] The number of the external mounting interfaces 3-5 of the nest-like support structure 3 is 4 to 8.

[0050] Compared with the prior art, the present invention has the following beneficial effects: The present invention provides a vibration damping, energy absorption and lightweight satellite chassis structure applicable to multiple working conditions. Combining the characteristics of the additive manufacturing process and the use environment of the satellite chassis, a nest-like support structure 3 is designed. The grid skin support 3-3 for fixing components is built on the tree-shaped bracket 3-2 like a bird's nest and suspended in the entire space structure. The distribution of the tree-shaped bracket 3-2 is set according to the structural stress conditions, making full use of materials and ensuring the structural stiffness and strength. This structure not only facilitates the arrangement of components, can make full use of the internal space of the chassis, but also reduces the use of redundant materials and better achieves the weight reduction effect.

[0051] The nest-like support structure 3 can be produced by the additive manufacturing process. The base panel 3-1, the tree-shaped bracket 3-2, the grid skin support 3-3, the intermediate connector 3-4 and the external mounting interface 3-5 are integrally formed, avoiding errors caused by multiple component assemblies or toolings and ensuring the position accuracy of the components.

[0052] Grooves of different forms are provided on each outer wall surface of the rib-like chassis main shell 1 of the satellite chassis, which not only ensures the structural strength but also plays the roles of weight reduction and enhanced heat dissipation.

[0053] The body diagonal grid structure 2-1 adopted in the grid skin panel 2 and the grid skin support 3-3 has pores inside. When the body diagonal grid structure 2-1 is subjected to external forces, it will deform, thereby absorbing energy and reducing the impact or damage of vibration and impact on the equipment. Compared with the traditional solid structure, the grid structure has a lower mass while maintaining the structural strength.

[0054] The grid skin panel 2 and multiple nest-like support structures 3 are manufactured by 3D printing.

[0055] The present invention has great engineering application value in the fields of aerospace and other occasions where weight reduction, strength improvement and stability enhancement are required.

[0056] Embodiment III: The design solution of this embodiment is as Figures 1 to 10 shown, and the components mentioned therein are optical lenses, beam splitters, photodetectors, etc. The components are installed in the rib-like chassis main housing 1 through the nest-like support structure 3.

[0057] The satellite chassis of this embodiment includes a rib-like chassis main housing 1, a grid skin panel 2 and several nest-like support structures 3. The several nest-like support structures 3 are respectively a first type of nest-like support structure 3-6, a second type of nest-like support structure 3-7 and a third type of nest-like support structure 3-8. See Figure 8 for the schematic diagram of the third type of nest-like support structure of an embodiment of the present invention; see Figure 9 for the schematic diagram of the second type of nest-like support structure of an embodiment of the present invention; see Figure 10 for the schematic diagram of the first type of nest-like support structure of an embodiment of the present invention.

[0058] After the rib-like chassis main housing 1 and the grid skin panel 2 are assembled, they form the outer shell of the satellite chassis; after fixing the components to a single nest-like support structure 3, the first type of nest-like support structure 3-6, the second type of nest-like support structure 3-7 and the third type of nest-like support structure 3-8 are assembled into a whole using bolts and then installed on the satellite chassis outer shell.

[0059] The rib-like chassis main housing 1 is a trapezoidal box body with an opening on one side. The outer wall surfaces of the upper and lower surfaces are provided with special-shaped weight-reducing and heat-dissipating grooves 1-1 in combination with circles and mountain shapes. The outer wall surfaces of the left and right surfaces and the bottom surface are provided with polygonal weight-reducing grooves 1-2. Four semi-waist-shaped mounting bosses 1-3 with threaded holes are provided at the opening.

[0060] The grid skin panel 2 described above is a box cover plate, with a variable-spacing body diagonal grid structure 2-1 inside, covered with skin on the outside, and there are 4 nest-like support structure mounting holes 2-2, 4 rib-like chassis main housing mounting holes 2-3 and external interfaces 2-4 in the center of the panel.

[0061] The first type of nest-like support structure 3-6, the second type of nest-like support structure 3-7 and the third type of nest-like support structure 3-8 are the internal support main bodies of the satellite chassis. Taking the third type of nest-like support structure 3-8 as an example for detailed description, the third type of nest-like support structure 3-8 is composed of a base panel 3-1, multiple tree-branch-shaped brackets 3-2, six grid skin supports 3-3, 6 intermediate connectors 3-4 and 2 mounting interfaces 3-5; the base panel 3-1 is a basic supporting structure with undulations for connecting other components; the tree-branch-shaped brackets 3-2 are multi-branch curved rod-shaped connecting structures with irregular cross-sections that avoid the optical path and are obtained through topology optimization calculation, and are used to connect the grid skin supports 3-3, the intermediate connectors 3-4 and the mounting interfaces 3-5; the grid skin supports 3-3 are special-shaped box-like structures with an open side on one side, filled with a body diagonal grid structure 2-1 inside and covered with skin on the outer surface, and the grid skin supports 3-3 are used to fix the internal components of the chassis; the intermediate connectors 3-4 are boss structures with threaded holes or through holes, and are used for connecting between multiple nest-like support structures; the mounting interfaces 3-5 are round bosses with threaded holes, and are used to mount the entire nest-like support structure onto the grid skin panel 2.

[0062] There are three kinds of spacing dimensions of the body diagonal grid structure 2-1 of the above-mentioned grid skin panel 2, which are 7mm, 12mm and 20mm respectively, and the skin thickness is 2mm.

[0063] The above-mentioned body diagonal grid structure 2-1 is a cube where the diagonal rods intersect, the grid size of the grid skin panel 2 is 4mm, and the porosity is 35%.

[0064] The number of branches of the tree-branch-shaped brackets in the above-mentioned nest-like support structure is from 1 to 8, the curved rod is a variable cross-section curved rod-shaped structure, the shape of the rod is adjusted according to the loading conditions and external working conditions, the cross-sectional shape is nearly circular or nearly elliptical, the long side dimension of the cross-section is 1.5mm to 20mm, and fillet transitions are provided at the branch points, and the fillet radius is 3mm to 15mm.

[0065] The number of external mounting interfaces of the above-mentioned entire nest-like support structure is 4.

[0066] Assembly and fitting: Install all components from the open side of the grid skin support 3-3. After all components are assembled, connect the first type of nest-shaped support structure 3-6, the second type of nest-shaped support structure 3-7, and the third type of nest-shaped support structure 3-8 respectively through 24 intermediate connectors 3-4. The assembled nest-shaped support structure 3 is fixed to the grid skin panel 2 through 4 mounting interfaces 3-5 and four nest-shaped support structure mounting holes 2-2, and then the grid skin panel 2 is installed on the semi-waist-shaped mounting boss 1-3 of the ribbed chassis main housing 1. During installation, the four ribbed chassis main housing mounting holes 2-3 correspond to the four semi-waist-shaped mounting bosses 1-3 and are fixedly connected by bolts.

[0067] The above content is only to illustrate the technical idea of the present invention and cannot be used to limit the protection scope of the present invention. Any modification made on the basis of the technical solution according to the technical idea proposed by the present invention falls within the protection scope of the present invention.

Claims

1. A vibration-reducing and energy-absorbing lightweight satellite chassis structure suitable for multiple working conditions, characterized in that: include: A rib-like chassis main shell (1), wherein the rib-like chassis main shell (1) is a hollow box structure with an opening on one side; A grid skin panel (2), the grid skin panel (2) being fixedly connected to the opening of the rib-type chassis main shell (1), and a plurality of body diagonal grid structures (2-1) being arranged inside the grid skin panel (2); A nest-like support structure (3), wherein a plurality of nest-like support structures (3) are arranged in the rib-like chassis main shell (1), the nest-like support structures (3) are fixedly connected to each other, the nest-like support structure (3) is fixedly connected to the grid skin panel (2), and a plurality of grid skin supports (3-3) are provided on the nest-like support structure (3), and the grid skin supports (3-3) are used to install components inside the satellite chassis; The nest-like support structure (3) is an irregular rod-shaped connection structure obtained by topological optimization according to the stress conditions and the optical path conditions inside the satellite chassis.

2. The vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions according to claim 1 is characterized in that: The rib-like chassis main shell (1) is provided with a special-shaped weight-reducing and heat-dissipating groove (1-1) and a polygonal weight-reducing groove (1-2).

3. The vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions according to claim 1 is characterized in that: A plurality of semi-waist-shaped mounting bosses (1-3) are provided on the rib-like chassis main shell (1), the semi-waist-shaped mounting bosses (1-3) are located at the opening of the rib-like chassis main shell (1), and the grid skin panel (2) is connected to the semi-waist-shaped mounting bosses (1-3) by bolts.

4. The vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions according to claim 1 is characterized in that: The grid skin panel (2) is provided with a nest-like support structure mounting hole (2-2), a rib-like chassis main shell mounting hole (2-3) and an external interface (2-4); the nest-like support structure mounting hole (2-2) is used to connect the nest-like support structure (3); the rib-like chassis main shell mounting hole (2-3) is used to connect the opening of the rib-like chassis main shell (1); and the external interface (2-4) is used for light source input.

5. The vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions according to claim 1 is characterized in that: The grid skin panel (2) is covered with a skin having a thickness of 1 mm to 5 mm, and the skin is located on a side away from the rib-type chassis main shell (1).

6. The vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions according to claim 1 is characterized in that: The nest-like support structure (3) comprises a base panel (3-1), a tree-branch-shaped support (3-2), an intermediate connecting piece (3-4) and a mounting interface (3-5); The base panel (3-1) is fixedly connected to the tree-branch-shaped bracket (3-2); The tree-branch-shaped supports (3-2) are connected by intermediate connecting pieces (3-4); The tree-branch-shaped bracket (3-2) is connected to the grid skin panel (2) via a mounting interface (3-5), and the mounting interface (3-5) is connected to the grid skin panel (2) via bolts; A grid skin support (3-3) is provided on the tree-branch-shaped support (3-2).

7. The vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions according to claim 6 is characterized in that: The tree-branch-shaped support (3-2) is specifically as follows: A multi-branch curved rod-shaped connection structure with an irregular cross-section is obtained through topological optimization according to the stress conditions of the tree-branch-shaped support (3-2) and the optical path conditions inside the satellite chassis. The tree-branch-shaped support (3-2) has 1 to 8 branches, and the connection between the branches is provided with fillets with a radius of 3mm to 15mm. The grid skin support (3-3) is connected to three to eight branches.

8. The vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions according to claim 8 is characterized in that: The grid skin support (3-3) is a special-shaped box-shaped structure with one side open; the shell of the grid skin support (3-3) is filled with a body diagonal grid structure (2-1); and the outer surface of the grid skin support (3-3) is covered with skin; One to four external interfaces (2-4) are provided on the grid skin support (3-3), and the external interfaces (2-4) are used for light source input.

9. The vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions according to claim 1 is characterized in that: The body diagonal lattice structure (2-1) is a hexahedral structure, the interior and six faces of the hexahedral structure are hollowed out, the apex angles of the hexahedral structure are connected by rods, and the porosity of the body diagonal lattice structure (2-1) is 30% to 40%.

10. The vibration-damping, energy-absorbing and lightweight satellite chassis structure applicable to multiple working conditions according to claim 1 is characterized in that: The spacing between the body diagonal grid structures (2-1) is 7 mm to 20 mm.

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