Lightweight substructure suitable for moonlet multi-view-field constraint and multi-device installation

Abstract

The invention relates to a lightweight substructure suitable for moonlet multi-view-field constraint and multi-device installation, which is arranged in a moonlet docking ring, and comprises a device installation panel provided with a device installation position; the upper end of the supporting frame is detachably connected with the bottom surface of the equipment mounting panel, and the lower end of the supporting frame is fixedly connected with the sunward surface of the small satellite; a hollow avoiding space is defined by the equipment mounting panel and the supporting frame; and the height of the lightweight secondary structure is smaller than that of the small satellite docking ring. The multi-view-field and multi-device compact type small satellite has the advantages of being convenient and fast to machine, easy to assemble, high in space utilization rate, convenient to operate and safe, and the problem that the multi-view-field and multi-device configuration layout design difficulty of an existing compact type small satellite is large can be solved.

Description

Technical Field

[0001] The present invention relates to the field of satellite technology, and in particular to a lightweight substructure suitable for multi-field-of-view constraints and multi-device installation of small satellites. Background Art

[0002] With the development of small satellite applications, the configuration of small satellites is becoming more and more compact. With the improvement of technical indicators, the equipment on small satellites that requires field of view has not decreased but increased. At the same time, users have also put forward high requirements on the total weight of satellites. This makes the design difficulty of small satellite configuration more and more difficult.

[0003] At present, the substructures of small satellites are mostly designed around a single device. When a satellite has multiple satellite catalog devices, multiple substructures are often designed to meet the field of view requirements. This not only brings difficulty in the design of the configuration layout, but also may cause various unexpected interference situations during the satellite AIT process, increasing the difficulty of satellite assembly.

[0004] Therefore, it is necessary to design a lightweight substructure suitable for multi-field-of-view constraints and multi-device installation in the compact space of small satellites to meet the requirements of small satellites for operational convenience and safety in arranging multi-field-of-view constraints and multi-device installation on the sky. Summary of the invention

[0005] In order to solve the technical problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a lightweight substructure suitable for multi-field-of-view constraints and multi-device installation of small satellites, which has the characteristics of easy operation, high safety and strong adaptability.

[0006] To achieve the above-mentioned purpose, the present invention provides a lightweight substructure suitable for multi-field-of-view constraint and multi-device installation of a small satellite, which is arranged in a small satellite docking ring. The lightweight substructure includes:

[0007] An equipment installation panel, on which equipment installation positions are provided;

[0008] A support frame, the upper end of which is detachably connected to the bottom surface of the device installation panel, and the lower end of which is fixedly connected to the small satellite's sky surface; the device installation panel and the support frame form a hollow avoidance space;

[0009] The height of the lightweight secondary structure is less than the height of the small satellite docking ring.

[0010] According to a technical solution of the present invention, the equipment installation panel includes:

[0011] The panel body is circular; the device installation position is arranged on the panel body;

[0012] The circumferential reinforcing rib is annular and is arranged on the bottom surface of the panel body; the circumferential reinforcing rib and the panel body are provided with a plurality of support frame mounting interfaces;

[0013] The equipment installation reinforcement rib is arranged on the bottom surface of the panel body, and the two ends of the equipment installation reinforcement rib are respectively connected to the inner wall of the circumferential reinforcement rib.

[0014] According to a technical solution of the present invention, the support frame includes:

[0015] A plurality of support rods are distributed along the circumferential reinforcement ribs, and an upper support rod mounting seat and a lower support rod mounting seat are respectively provided at the upper end and the lower end of the support rod; a support beam mounting interface is provided at the middle of the support rod;

[0016] A plurality of support beams are arranged between two adjacent support rods, and a first support beam mounting seat and a second support beam mounting seat are respectively arranged at two ends of the support beam.

[0017] According to a technical solution of the present invention, the upper support rod mounting seat and the support frame mounting interface, the lower support rod mounting seat and the small satellite facing the sky, and the first support beam mounting seat and the second support beam mounting seat and the support beam mounting interface are connected and fixed by means of screw nuts.

[0018] According to a technical solution of the present invention, the support rod is provided with an upper support rod weight reduction groove and a lower support rod weight reduction groove arranged along the length direction of the support rod, and the support beam mounting interface is arranged between the upper support rod weight reduction groove and the lower support rod weight reduction groove.

[0019] According to a technical solution of the present invention, the support beam is provided with a support beam weight reducing groove arranged along the length direction of the support beam.

[0020] According to a technical solution of the present invention, the width of the support frame is smaller than the width of the equipment installation panel, and the width of the equipment installation panel is smaller than the width of the small satellite docking ring.

[0021] According to a technical solution of the present invention, the support rod is in the shape of a parallelogram, and the support beam is in the shape of a trapezoid.

[0022] According to a technical solution of the present invention, the equipment installation panel and the support frame are both made of aluminum alloy 2A12.

[0023] Compared with the prior art, the present invention has the following beneficial effects:

[0024] The present invention proposes a lightweight substructure suitable for multi-field-of-view constraints and multi-equipment installation of small satellites, which is arranged in a docking ring of the small satellite facing the sky. At the same time, the equipment installation panel and the support frame form a hollow cavity, which meets the installation requirements of equipment such as satellite hydrazine bottles on the small satellite facing the sky, and can achieve efficient utilization of the equipment layout space of the small satellite facing the sky; equipment installation positions are arranged on the equipment installation panel, which can meet the centralized installation of multiple equipment with field-of-view requirements, greatly improving the utilization rate of the equipment layout space of the satellite facing the sky; the equipment installation panel can adapt to different equipment layout requirements of different equipment, and has good adaptability.

[0025] The present invention has a simple structure, is easy to process and assemble, and has a short construction period. The equipment installation panel can be adaptively adjusted according to the installation equipment to design interfaces and equipment installation reinforcement ribs, and has multi-equipment adaptability. At the same time, the individual parts can be easily processed, and the whole can be easily assembled and disassembled, which is convenient for satellite assembly and the plugging and unplugging of high-frequency electrical connectors on antennas during wireless testing in the AIT stage.

[0026] In the present invention, a plurality of weight-reducing grooves are arranged on the support frame, which can reduce the weight of the support frame structure and also serve as binding and fixing points for cable binding and thermal control multi-layer implementation, thus providing convenience for satellite installation and satellite wireless test operations. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0028] Figure 1 A three-dimensional diagram schematically showing a lightweight substructure suitable for multi-field-of-view constraints and multi-equipment installation of a small satellite provided in an embodiment of the present invention;

[0029] Figure 2 A schematic front view of a lightweight secondary structure suitable for multi-field-of-view constraints and multi-equipment installation of a small satellite according to an embodiment of the present invention is shown;

[0030] Figure 3 A schematic top view of a lightweight secondary structure suitable for multi-field-of-view constraints and multi-device installation of a small satellite according to an embodiment of the present invention is shown;

[0031] Figure 4 Schematically showing a schematic diagram of the structure of a device installation panel according to an embodiment of the present invention;

[0032] Figure 5 A schematic diagram of the structure of a support rod according to an embodiment of the present invention is shown;

[0033] Figure 6 The schematic diagram of the structure of the support beam according to the embodiment of the present invention is shown schematically.

[0034] The corresponding relationship between the component names and the reference numerals is as follows:

[0035] 1. Equipment installation panel; 2. Support frame;

[0036] 11. Panel body; 12. Circumferential reinforcement ribs; 13. Equipment installation reinforcement ribs; 14. Equipment installation position; 15. Support frame installation interface;

[0037] 21. Support rod; 22. Support beam;

[0038] 211, upper support rod mounting seat; 212, lower support rod mounting seat; 213, support beam mounting interface; 214, upper support rod weight reduction groove; 215, lower support rod weight reduction groove;

[0039] 221. First support beam mounting seat; 222. Second support beam mounting seat; 223. Support beam weight reduction groove. DETAILED DESCRIPTION

[0040] The description of the embodiments of this specification should be combined with the corresponding drawings, which should be considered as part of the complete specification. In the drawings, the shape or thickness of the embodiments may be enlarged and indicated for simplification or convenience. Furthermore, the parts of each structure in the drawings will be described separately. It is worth noting that the elements not shown in the drawings or not described in words are in a form known to ordinary technicians in the relevant technical field.

[0041] The description of the embodiments herein and any reference to directions and orientations are only for the convenience of description and are not to be construed as any limitation on the scope of protection of the present invention. The following description of the preferred embodiments may involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0042] like Figures 1 to 6 As shown, a lightweight substructure suitable for multi-field-of-view constraint and multi-device installation of a small satellite is provided in a small satellite docking ring. The lightweight substructure includes:

[0043] An equipment installation panel 1, on which an equipment installation position 14 is provided;

[0044] The support frame 2 has an upper end detachably connected to the bottom surface of the equipment installation panel 1, and a lower end fixedly connected to the small satellite's sky surface; the equipment installation panel 1 and the support frame 2 form a hollow avoidance space;

[0045] The height of the lightweight secondary structure is less than the height of the small satellite docking ring.

[0046] In order to efficiently utilize the equipment layout space of the small satellite on the sky surface and ensure that the equipment field of view is not affected by the docking ring, thrusters and other structures and other equipment on the satellite, while leaving installation space for the satellite hydrazine bottle, the lightweight secondary structure design in the present invention is hollow inside as a whole, and its height is less than the height of the satellite docking ring.

[0047] In some embodiments of the present invention, the device mounting panel 1 comprises:

[0048] The panel body 11 is circular; the device installation position 14 is arranged on the panel body 11;

[0049] The circumferential reinforcing rib 12 is annular and is disposed on the bottom surface of the panel body 11; a plurality of support frame mounting interfaces 15 are disposed on the circumferential reinforcing rib 12 and the panel body 11;

[0050] The equipment installation reinforcement rib 13 is arranged on the bottom surface of the panel body 11, and the two ends of the equipment installation reinforcement rib 13 are respectively connected to the inner wall of the circumferential reinforcement rib 12. The equipment installation reinforcement rib 13 includes a plurality of transverse reinforcement ribs and longitudinal reinforcement ribs connected to the transverse reinforcement ribs. The number and installation position of the transverse reinforcement ribs are determined according to the installation equipment. In some embodiments of the present invention, such as Figure 4 As shown, the number of transverse reinforcing ribs is 4 and the number of longitudinal reinforcing ribs is 5.

[0051] The equipment installation panel 1 is circular and has circumferential reinforcement ribs designed on the edge of the panel, on which six groups of installation interfaces with the support rod 2 are evenly distributed. The installation panel is connected to the circumferential reinforcement ribs 12 through four horizontal and one vertical equipment installation reinforcement ribs 13, which strengthens the overall strength of the installation panel and ensures that the secondary structure can meet the mechanical conditions of transportation after the equipment is installed. Equipment with field of view requirements such as GNSS antennas, solar sensors and measurement and control antennas can be arranged on the equipment installation panel 1. The equipment installation panel 1 can adjust the specific positions of the equipment installation position 14 and the equipment installation reinforcement ribs 13 according to the equipment to be installed.

[0052] In some embodiments of the present invention, the support frame 2 comprises:

[0053] A plurality of support rods 21 are distributed along the circumferential reinforcement rib 12. An upper support rod mounting seat 211 and a lower support rod mounting seat 212 are respectively provided at the upper end and the lower end of the support rod 21; a support beam mounting interface 213 is provided at the middle of the support rod 21;

[0054] A plurality of support beams 22 are arranged between two adjacent support rods 21 , and a first support beam mounting seat 221 and a second support beam mounting seat 222 are respectively arranged at two ends of the support beam 22 .

[0055] In some embodiments of the present invention, the upper support rod mounting seat 211 and the support frame mounting interface 15, the lower support rod mounting seat 212 and the small satellite facing the sky, and the first support beam mounting seat 221 and the second support beam mounting seat 222 and the support beam mounting interface 213 are connected and fixed by means of screw nuts.

[0056] The equipment installation panel 1 and the support rod 21 of the secondary structure, as well as the support rod 21 and the support beam 22 are connected and fixed by means of screw nuts, which can achieve the effect of easy processing of individual parts and easy assembly and disassembly of the whole, and is convenient for satellite assembly and plugging and unplugging of high-frequency electrical connectors on the antenna during wireless testing in the AIT stage.

[0057] In some embodiments of the present invention, the support rod 21 is provided with an upper support rod weight reduction groove 214 and a lower support rod weight reduction groove 215 arranged along the length direction of the support rod 21, and the support beam mounting interface 213 is arranged between the upper support rod weight reduction groove 214 and the lower support rod weight reduction groove 215. The support beam 22 is provided with a support beam weight reduction groove 223 arranged along the length direction of the support beam 22. The weight reduction grooves of the support rod 21 and the support beam 22 effectively reduce the weight of the structure while ensuring the strength, and can also be used as binding points for equipment cables and fixing points when the thermal control is implemented in multiple layers.

[0058] In some embodiments of the present invention, the width of the support frame 2 is smaller than the width of the equipment installation panel 1, and the width of the equipment installation panel 1 is smaller than the width of the small satellite docking ring. The support rod 21 is parallelogram-shaped, and the support beam 22 is trapezoidal.

[0059] By setting the width of the equipment installation panel 1 to be smaller than the width of the small satellite docking ring, interference between the equipment installed on the equipment installation panel 1 and the small satellite docking ring can be avoided. By setting the shapes of the support rod 21 and the support beam 22, it can be ensured that the equipment installation panel 1 remains parallel to the small satellite's sky surface during installation, thereby improving the stability of the installed equipment.

[0060] In some embodiments of the present invention, the equipment installation panel 1 and the support frame 2 are both made of aluminum alloy 2A12. There are no special requirements for the processing of the equipment installation panel 1 and the support frame 2, the roughness is 3.2, the dimensional tolerance is implemented according to GB / T 1184, and the sharp angles are blunted.

[0061] The installation order of the lightweight substructure suitable for multi-field-of-view constraints and multi-device installation of small satellites provided by the present invention on the satellite is as follows: first, fix the panel body 11 and the support rod 21 by two M4 screws and M4 nuts, a total of six groups. Then fix the support rod 21 and the support beam 22 by two M4 screws and M4 nuts, a total of six groups. According to the design status, the substructure is fixed to the satellite's sky surface structure plate by twelve M4 screws, and then the equipment to be installed is installed on the equipment installation panel 1, and the cable connector is plugged in. The cable can be tied and fixed by the support rod 21 and the support beam 22. When the thermal control is implemented in multiple layers, it can also be tied and fixed by the support rod 21 and the support beam 22.

[0062] It should be noted that the above is a preferred embodiment of the present invention. It should be pointed out that although the preferred embodiment of the present invention has been described, once the basic creative concept of the present invention is known, a number of improvements and modifications can be made by a person skilled in the art without departing from the principles of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. Therefore, the attached claims are intended to be interpreted as including the preferred embodiment and all changes and modifications that fall within the scope of the embodiments of the present invention.

Claims

1. A lightweight substructure suitable for multi-field-of-view constraints and multi-device installation of small satellites, characterized in that: Arranged in the small satellite docking ring, the lightweight substructure includes: An equipment installation panel (1) having an equipment installation position (14) disposed thereon; A support frame (2), the upper end of which is detachably connected to the bottom surface of the device installation panel (1), and the lower end of which is fixedly connected to the small satellite's sky surface; the device installation panel (1) and the support frame (2) enclose a hollow avoidance space; The height of the lightweight secondary structure is less than the height of the small satellite docking ring.

2. The lightweight substructure according to claim 1, characterized in that: The device installation panel (1) comprises: The panel body (11) is circular; the device installation position (14) is arranged on the panel body (11); The circumferential reinforcing rib (12) is annular and is arranged on the bottom surface of the panel body (11); a plurality of support frame mounting interfaces (15) are arranged on the circumferential reinforcing rib (12) and the panel body (11); The equipment installation reinforcement rib (13) is arranged on the bottom surface of the panel body (11), and the two ends of the equipment installation reinforcement rib (13) are respectively connected to the inner wall of the circumferential reinforcement rib (12).

3. The lightweight substructure according to claim 2, characterized in that: The support frame (2) comprises: A plurality of support rods (21) are distributed along the circumferential reinforcing ribs (12); an upper support rod mounting seat (211) and a lower support rod mounting seat (212) are respectively provided at the upper end and the lower end of the support rod (21); and a support beam mounting interface (213) is provided at the middle of the support rod (21); A plurality of support beams (22) are arranged between two adjacent support rods (21), and a first support beam mounting seat (221) and a second support beam mounting seat (222) are respectively arranged at two ends of the support beam (22).

4. The lightweight substructure according to claim 3, characterized in that: The upper support rod mounting seat (211) and the support frame mounting interface (15), the lower support rod mounting seat (212) and the small satellite facing the sky, and the first support beam mounting seat (221) and the second support beam mounting seat (222) and the support beam mounting interface (213) are connected and fixed by means of screw nuts.

5. The lightweight substructure according to claim 4, characterized in that: The support rod (21) is provided with an upper support rod weight reduction groove (214) and a lower support rod weight reduction groove (215) arranged along the length direction of the support rod (21), and the support beam mounting interface (213) is arranged between the upper support rod weight reduction groove (214) and the lower support rod weight reduction groove (215).

6. The lightweight substructure according to claim 3, characterized in that: The support beam (22) is provided with a support beam weight-reducing groove (223) arranged along the length direction of the support beam (22).

7. The lightweight substructure according to claim 1, characterized in that: The width of the support frame (2) is smaller than the width of the equipment installation panel (1), and the width of the equipment installation panel (1) is smaller than the width of the small satellite docking ring.

8. The lightweight substructure according to claim 3, characterized in that: The support rod (21) is in the shape of a parallelogram, and the support beam (22) is in the shape of a trapezoid.

9. The lightweight substructure according to claim 1, characterized in that: The equipment installation panel (1) and the support frame (2) are both made of aluminum alloy 2A12.

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