Satellite electric control electric box and flywheel integrated structure

Abstract

The invention relates to the technical field of satellite single machines, and particularly discloses a satellite electric control electric box and flywheel integrated structure which comprises a shell, a supporting structure, a plurality of working modules and a flywheel assembly. The shell is provided with eight side faces, and four flywheels in the flywheel assembly are connected with the four rectangular side faces on the outer side of the shell respectively. A plurality of working modules are sequentially arranged in the shell from top to bottom, the working modules are matched with the inner space of the shell and are fixed in the shell through a supporting structure, and the heat dissipation device is directly installed on the shell. The structure integrates a flywheel support structure and an electric control electric box structure shell, and has the advantages of being high in integration degree, high in lightweight degree and excellent in mechanical property.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite stand-alone machines, and in particular to an integrated structure of a satellite electric control box and a flywheel. Background Art

[0002] With the continuous advancement of aerospace technology, the space and weight restrictions on satellites by carriers are becoming increasingly stringent, prompting satellite structural design to move towards high space utilization and lightweight structure. Structural optimization design has become an important trend in satellite design. The traditional satellite electrical box structure is composed of multiple layers of series components. For example, in a Chinese patent with publication number CN216581107U, a satellite electrical unit structure that is easy to separate and disassemble is used: each layer is equipped with a circuit board, and finally fixed by screws passing through the corresponding connection holes of each layer. Due to the lack of effective support for the center of the circuit board and the square layout restriction, this type of structure has a significant decrease in dynamic stiffness as the size of the circuit board increases, and increasing stiffness often requires increasing mass, which is contrary to the goal of lightweighting.

[0003] Compared with the orthogonal flywheel installation scheme, the four-slant flywheel installation scheme provides higher reliability and performance in satellite attitude control due to its redundant design, control flexibility and dynamic optimization. Therefore, the use of the four-slant flywheel installation scheme has become a new trend in attitude control of high-resolution remote sensing satellites. However, the traditional four-slant flywheel bracket adopts a pyramid design, and the internal space of the pyramid is wasted, resulting in its structural redundancy, such as the Chinese patent with publication number CN202010699479.8.

[0004] In addition, the existing high-resolution remote sensing satellite flywheel bracket design lacks attention to the relationship between the fundamental frequency of the flywheel bracket and the frequency of the flywheel disturbance force, resulting in the coupling of the flywheel disturbance force frequency, which leads to the amplification of the disturbance force, thereby affecting the imaging quality. At the same time, the traditional satellite stand-alone design scheme is not integrated enough, resulting in a complex layout of connector cables, difficult disassembly and assembly, and cable redundancy increases the overall quality, which does not meet the modern satellite design requirements of high integration and lightweight.

[0005] Based on this, the technical personnel in this field urgently need to provide a new structure that integrates the satellite electronic control box and the flywheel to solve the technical problems existing in the above-mentioned prior art. Summary of the invention

[0006] Therefore, the technical problem to be solved by the present invention is to overcome the defects existing in the above-mentioned prior art, thereby providing a satellite electric control box and flywheel integrated structure that can be mass-produced.

[0007] A satellite electric control box and flywheel integrated structure, comprising: a housing, a circuit board support structure, a plurality of working modules, a flywheel assembly and a heat dissipation device; The housing has eight side surfaces in total, and the four flywheels in the flywheel assembly are respectively connected to the four rectangular side surfaces on the outside of the housing; Inside the shell: a plurality of working modules are arranged in sequence from top to bottom, and the plurality of working modules are adapted to the inner space of the shell and fixed inside the shell through the circuit board support structure; The heat dissipation device is installed on the shell.

[0008] Preferably, the housing is composed of a structural shell and a top cover plate; The structural shell is composed of eight staggered rectangular sides and triangular sides; the side lengths of the rectangular sides are equal to the side lengths of the triangular sides and are butt-jointed; The top cover plate is connected to the top edges of the four rectangular side surfaces.

[0009] Preferably, it also includes a rubber vibration damper; The four flywheels are symmetrically mounted on the four rectangular sides of the structural shell through vibration dampers.

[0010] Preferably, the angle between the rectangular side surface of the structural shell and the bottom surface of the structural shell is 54.74°.

[0011] Preferably, the heat dissipation device includes: a power discharge MOS tube and a power discharge resistor; The power discharge MOS tube is installed on the inner wall of the structural shell; The power discharge resistor is installed on the outer wall of the structural shell.

[0012] Preferably, a plurality of circuit boards are integrated with a plurality of devices required for the functions of the working modules, and the devices are interconnected through wiring on the plurality of circuit boards to form a complete functional unit; Multiple circuit boards are installed inside the structural shell from top to bottom, and data transmission is achieved between the circuit boards through flexible circuit boards; The electrical connectors of the multiple circuit boards are evenly arranged at the edges of the corresponding circuit boards.

[0013] Preferably, the circuit board is fixed in the structural housing via a circuit board support structure; The circuit board support structure is provided with a heat dissipation structure, and the heat dissipation surface of the heat dissipation structure is fitted with the components on the circuit board to achieve heat conduction.

[0014] The technical solution of the present invention has the following advantages: The present invention proposes a four-slant flywheel bracket and satellite electric box integrated design structure for spacecraft. The design integrates the flywheel bracket and the structural shell, and integrates vibration reduction and isolation, device heat dissipation, connector installation and other functions. It breaks the physical boundary between the flywheel assembly and the electric control box in the traditional satellite design, and achieves high integration, high space utilization and lightweight structure. The highly integrated design of the present invention also greatly simplifies the cable network layout inside the satellite, reduces the labor intensity during the assembly process, and significantly improves the satellite assembly, integration and testing efficiency, laying the foundation for the mass production of satellites.

[0015] The pyramid structure of the present invention has excellent structural rigidity. On the one hand, the high structural rigidity avoids the coupling between the structural fundamental frequency and the flywheel disturbance vibration frequency, reducing the negative impact of the flywheel disturbance force on the camera imaging quality. On the other hand, it significantly strengthens the rigid support of the circuit board, effectively reduces the mechanical response of the circuit board caused by the complex mechanical environment of the launch section, and improves the environmental adaptability of the circuit board. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 The final assembly structure diagram of the present invention is Figure 2 A cross-sectional schematic diagram of the present invention Figure 3 This is a partial enlarged view of the device heat dissipation surface of the point-type support structure of the upper circuit board in Example 2 of the present invention.

[0018] Description of reference numerals: 1 structural shell, 10 top cover plate, 3 upper circuit board point support structure, 2 upper circuit board support structure transfer, 4 lower circuit board point support structure, 5 flywheel, 11 shock absorber, 6 upper circuit board, 7 lower circuit board, 8 power discharge MOS tube, 9 power discharge resistor. DETAILED DESCRIPTION

[0019] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0020] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the structure or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0021] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0022] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0023] Example 1 A satellite electric control box and flywheel integrated structure, comprising: a housing, a circuit board support structure, a plurality of working modules, a flywheel assembly and a heat dissipation device; The housing has eight sides in total, and the four flywheels 5 in the flywheel assembly are respectively connected to the four rectangular sides outside the housing; Inside the shell: a plurality of working modules are arranged in sequence from top to bottom, and the plurality of working modules are adapted to the inner space of the shell and fixed inside the shell through the circuit board support structure; The heat dissipation device is installed on the shell.

[0024] Specifically: The housing is composed of a structural shell 1 and a top cover plate 10; The structural shell 1 is in a pyramid configuration, consisting of eight staggered rectangular sides and triangular sides; the side length of the rectangular side is equal to the side length of the triangular side, and the two are butted; the angle between the rectangular side of the structural shell 1 and the bottom of the structural shell 1 is 54.74°. The top cover plate 10 is connected to the top edges of the four rectangular sides. The material of the structural shell 1 and the top cover plate 10 is magnesium alloy, and the wall thickness of the structural shell is set to 3mm; The heat dissipation device comprises: a power discharge MOS tube (8) and a power discharge resistor (9); The power discharge MOS tube (8) is mounted on the inner wall of the structural housing (1); The power discharge resistor (9) is mounted on the outer wall of the structural housing (1).

[0025] Specifically: the power discharge MOS tube 8 uses the general military-grade product LYPM4905T, the gate and source of the power discharge MOS tube 8 are respectively led out through wires, connected to the bus power supply and the power discharge resistor 9 on the flywheel connector, and the power discharge MOS tube 8 is installed on the inner wall of the structural housing 1 through the mounting holes on the structural housing 1 to facilitate heat conduction; The power discharge resistor 9 uses RIG5-25W-35Ω, and the two ends are connected to the drain of the power discharge MOS tube 8 and the ground signal on the flywheel connector through wires. The power discharge resistor 9 is installed on the outer wall of the structural shell 1 through the mounting hole on the structural shell 1 to facilitate heat conduction. The power discharge MOS tube 8 and the power discharge resistor 9 are connected by wires to form a discharge circuit.

[0026] At the same time, a weight-reducing groove is provided on the outer wall of the structural shell 1, and reinforcing ribs are provided at the installation points of the flywheel 5 and the circuit board. The design scheme of this embodiment has a compact structure, and the structure is lightweight by optimizing the thickness of the structural shell 1 and the top cover plate 10 and the geometric parameters of the supporting structure reinforcing ribs.

[0027] In addition, in this embodiment, a plurality of circuit boards are integrated with a plurality of devices required for the functions of the working modules, and the devices are interconnected through wiring on the plurality of circuit boards to form a complete functional unit; Multiple circuit boards are installed inside the structural housing 1 from top to bottom, and data transmission is achieved between the circuit boards through flexible circuit boards; The electrical connectors of the multiple circuit boards are evenly arranged at the edges of the corresponding circuit boards.

[0028] In the embodiment, the circuit board is fixed in the structural housing 1 via a circuit board supporting structure.

[0029] Example 2 Based on Example 1, this example further discloses the following contents: In this embodiment, a shock absorber 11 is also included; The four flywheels 5 are symmetrically mounted on the four rectangular sides through the shock absorbers 11. In this embodiment, the shock absorbers 11 are made of rubber; on the one hand, the rubber shock absorbers isolate the disturbance force of the flywheel when it is working, attenuate the high-frequency disturbance force of the flywheel, and avoid the influence of the disturbance force of the flywheel on the imaging quality; on the other hand, during the rocket launch phase, the random vibration input of the flywheel is reduced to ensure the stable operation of the flywheel.

[0030] Example 3 Based on Example 1, this example further discloses the following contents: In this embodiment, several working modules include but are not limited to: a driving module, a collection module, a satellite service processing module, a signal module and a power distribution module; In this embodiment, two circuit boards are used, and several components required for the functions of the working modules are integrated on the two circuit boards. The components are interconnected through wiring on the two circuit boards to form a complete functional unit; the two circuit boards are: an upper circuit board 6 and a lower circuit board 7; At the same time, the inner side of the structural housing 1 is provided with mounting surfaces for two circuit boards; Specifically: In this embodiment, the circuit board support structure includes: an upper circuit board support structure adapter 2, an upper circuit board point support structure 3 and a lower circuit board point support structure 4; The upper circuit board 6 and the lower circuit board 7 are installed inside the structural housing 1 from top to bottom. To adapt to the structural form of the structural housing, the electronic part of the electrical box is composed of two octagonal circuit boards, so that the upper circuit board 6 is smaller than the lower circuit board 7. The upper circuit board 6 and the lower circuit board 7 realize data transmission through a flexible circuit board. The upper circuit board 6 and the lower circuit board 7 are both provided with notches in the flexible circuit boards to avoid interference with the structural housing 1 when the flexible circuit boards are bent back. The electrical connectors of the upper circuit board 6 and the lower circuit board 7 are evenly arranged at the edges of the respective circuit boards. The position layout of the electrical connectors takes into account the spatial positions of different working modules in the satellite relative to the electrical box, so that the electrical connectors face the connected working modules to save the length of the connection line. Several working modules are connected to the circuit board through the above-mentioned electrical connectors; Eleven mounting points are evenly arranged on the edge of the upper circuit board 6 and fixed to the structural housing 1 by screws; Nine mounting points are evenly arranged at the center of the upper circuit board 6 and fixed to the upper circuit board point support structure 3 and the lower circuit board point support structure 4 by screws. The screws pass through the upper circuit board 6 from the upper circuit board point support structure 3 and are fixed to the lower circuit board point support structure 4. The upper circuit board point support structure 3 is fixed to the structural shell 1 through the upper circuit board support structure adapter 2 bracket; Fifteen mounting points are evenly arranged on the edge of the lower circuit board 7 and fixed to the structural housing 1 by screws; Nine mounting points are evenly arranged at the center of the lower circuit board 7 and fixed to the lower circuit board point support structure 4 by screws, and the positions of the nine mounting holes at the center of the upper circuit board 6 correspond to the positions of the nine mounting holes at the center of the lower circuit board 7; The eight outer connection points of the lower circuit board point support structure 4 are fixed to the side surface of the structural shell 1 by screws.

[0031] Example 4 Based on Example 3, this example further discloses the following contents: A heat dissipation structure is provided on the circuit board support structure; The heat dissipation structure achieves heat conduction by fitting the heat dissipation surface of the heat dissipation structure with the device on the circuit board through a thermal pad. The thickness of the thermal pad is 0.51mm. The thermal pad is used to provide compression to avoid assembly stress or poor contact of the thermal surface caused by processing errors.

[0032] Compared with the prior art, Examples 1-4 propose an integrated structural design of four obliquely mounted flywheels and an electric control box for high-resolution remote sensing satellites, in which the electric control box integrates the integrated electronics, power supply, X-measurement and control, and some attitude control functions of traditional satellite models. The integrated structure has multiple functions such as vibration reduction and isolation, device heat dissipation, and connector installation, replacing the traditional independent flywheel brackets and electric box housings. The four flywheels are installed on the outside of the structural housing through rubber shock absorbers, and the integrated circuit board is connected to the structural housing 1 using a point support structure. The structural design scheme has a high degree of integration, greatly improves space utilization, and greatly reduces the proportion of structural mass. At the same time, the structure simplifies the cable network of the entire satellite, reduces the intensity of manual labor, improves the efficiency of satellite assembly, integration and testing, and adapts to the needs of satellite mass production. In view of the problem of high power density of the electric box caused by the highly integrated design, the integrated structure solves the problem by directly installing the devices with high power consumption on the structural housing 1 to facilitate heat conduction, and designs a heat dissipation structure for some devices with high heat consumption on the circuit board. The pyramid structure adopted in this design scheme has multiple advantages due to its excellent structural stiffness characteristics. First, the structure effectively avoids the coupling phenomenon between the structural fundamental frequency and the vibration frequency generated by the disturbance of the flywheel 5, thereby significantly reducing the potential impact of the flywheel disturbance force on the camera imaging quality and ensuring the stability of the imaging; secondly, the pyramid structure significantly enhances the support stiffness of the circuit board and reduces the mechanical response of the circuit board under the conditions of the carrying mechanical environment.

[0033] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. A satellite electric control box and flywheel integrated structure, characterized in that: include: Housing, circuit board support structure, several working modules, flywheel assembly and heat dissipation device; The housing has eight side surfaces in total, and the four flywheels (5) in the flywheel assembly are respectively connected to the four rectangular side surfaces on the outer side of the housing; Inside the shell: a plurality of working modules are arranged in sequence from top to bottom, and the plurality of working modules are adapted to the inner space of the shell and fixed inside the shell through the circuit board support structure; The heat dissipation device is installed on the shell.

2. The satellite electric control box and flywheel integrated structure according to claim 1 is characterized in that: The housing is composed of a structural shell (1) and a top cover plate (10); The structural shell (1) is composed of eight staggered rectangular sides and triangular sides; the side lengths of the rectangular sides are equal to the side lengths of the triangular sides and are butt-jointed; The top cover plate (10) is connected to the top edges of the four rectangular side surfaces.

3. The satellite electric control box and flywheel integrated structure according to claim 1 is characterized in that: Also includes a rubber shock absorber (11); The four flywheels (5) are symmetrically mounted on the four rectangular sides via vibration dampers (11).

4. The satellite electric control box and flywheel integrated structure according to claim 2 is characterized in that: The included angle between the rectangular side surface of the structural shell (1) and the bottom surface of the structural shell (1) is 54.74°.

5. The satellite electric control box and flywheel integrated structure according to claim 2 is characterized in that The heat dissipation device comprises: a power discharge MOS tube (8) and a power discharge resistor (9); The power discharge MOS tube (8) is mounted on the inner wall of the structural housing (1); The power discharge resistor (9) is mounted on the outer wall of the structural housing (1).

6. The satellite electric control box and flywheel integrated structure according to claim 1 is characterized in that: Several components required for the functions of the working modules are integrated on multiple circuit boards, and the components are interconnected through wiring on multiple circuit boards to form a complete functional unit; A plurality of circuit boards are installed inside the structural housing (1) from top to bottom, and data transmission is achieved between the circuit boards via a flexible circuit board; The electrical connectors of the multiple circuit boards are evenly arranged at the edges of the corresponding circuit boards.

7. The satellite electric control box and flywheel integrated structure according to claim 6 is characterized in that: The circuit board is fixed in the structural housing (1) via a circuit board support structure; The circuit board support structure is provided with a heat dissipation structure, and heat conduction is achieved by fitting the heat dissipation surface of the heat dissipation structure to the components on the circuit board through a thermal pad.

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