CN219305247U - Power supply controller structure for satellite - Google Patents
Power supply controller structure for satellite Download PDFInfo
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- CN219305247U CN219305247U CN202223130971.7U CN202223130971U CN219305247U CN 219305247 U CN219305247 U CN 219305247U CN 202223130971 U CN202223130971 U CN 202223130971U CN 219305247 U CN219305247 U CN 219305247U
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Abstract
The utility model relates to the field of power control, in particular to a power controller structure for a satellite, which comprises a circuit board, a power element, a mounting rack, a functional module and a flying lead. The mounting bracket includes the mounting panel, and the body coupling of mounting panel and satellite, circuit board set up on the mounting bracket, and power component sets up in the front of mounting panel, and the reverse side of mounting panel is used for installing other functional module. Flying leads are used to electrically connect the circuit board and the power element. The power supply controller structure for the satellite can enable heat generated by the power element to be directly transferred to the mounting frame, and further be emitted to the satellite body, so that the heat dissipation effect is remarkably improved. In addition, the side of the mounting frame, which is away from the circuit board, can be used for mounting other single-machine functional modules of the satellite, so that the structure of the mounting frame is fully utilized, the integration level between the power supply controller and the other single-machine functional modules of the satellite is higher, and the space is saved to a great extent.
Description
Technical Field
The utility model relates to the field of power control, in particular to a power controller structure for satellites.
Background
The power supply controller can send RS-232 and RS-485 codes, and controls equipment by using a computer and a central control, such as equipment switch, lifting control of an electric screen, an electric curtain and an electric hanger, delayed shutdown of a projector and the like. The power supply controller can be matched with a conference central control system to realize centralized intelligent control of the power supply. The device can be controlled by PC software, and the open software platform has a device state feedback display function.
In the prior art, a power supply controller for a satellite is of an independent single-machine structure and mainly comprises a power element, a circuit board and an external frame, wherein the power element is arranged on the circuit board, the external frame is of a box structure, the circumferential edge of the circuit board is connected with the side wall of the external frame, the external frame is arranged inside the satellite, the bottom plate of the external frame is connected with the satellite body, and heat generated by the power element is transferred to the satellite body to realize heat dissipation. The heat generated by the power element of the power supply controller is firstly transmitted to the side wall of the external frame from the circuit board and then transmitted to the bottom plate of the external frame, and finally transmitted to the satellite body from the bottom plate, so that the heat dissipation effect of the heat dissipation mode is poor. In addition, the existing power supply controller has a large overall structure, occupies a large space and has a large weight, and is not suitable for small satellites with very strict space and weight requirements.
Accordingly, there is a need for a power controller architecture for satellites that addresses the above-described issues.
Disclosure of Invention
The utility model aims to provide a power supply controller structure for a satellite, which solves the problems of large volume, occupied space, heavy weight and poor heat dissipation of the existing power supply controller on the premise of ensuring the rigidity and strength of a whole machine.
In order to achieve the above object, the following technical scheme is provided:
a power controller architecture for a satellite comprising a circuit board and a power element, the power controller architecture for a satellite further comprising:
the mounting frame comprises a mounting plate, the mounting plate is connected with the body of the satellite, the circuit board is arranged on the mounting frame, and the power element is arranged on the front surface of the mounting plate;
the functional module is arranged on the back surface of the mounting plate;
and the flying lead is electrically connected with the circuit board and the power element.
Optionally, the mounting frame further comprises at least two support columns, one ends of the support columns are connected with the front surface of the mounting plate, and the other ends of the support columns are connected with the circuit board.
Optionally, the circuit board is disposed parallel to the mounting plate, a distance between the circuit board and the mounting plate is greater than a height of the power element, the power element is disposed in plurality, and at least a portion of the power element is disposed between the circuit board and the mounting plate.
Optionally, the power supply controller structure for satellite further comprises an external plug-in unit, wherein the external plug-in unit is arranged on the circuit board, and the external plug-in unit is electrically connected with the circuit board.
Optionally, the external connector is disposed at a peripheral edge of the circuit board, the external connector is perpendicular to the circuit board, and the external connector extends toward the mounting board.
Optionally, the power element further comprises an insulating heat-conducting gasket, and the insulating heat-conducting gasket is arranged between the power element and the mounting frame.
Optionally, the insulating thermal pad is a Bei Gesi thermal pad.
Optionally, the power element comprises a pin, a node is arranged on the circuit board, one end of the flying lead is connected with the pin, and the other end of the flying lead is connected with the node.
Optionally, a mounting hole is formed in a side surface of the mounting plate, and the mounting hole is connected with the body of the satellite.
Optionally, the mounting is made of an aluminum alloy.
Compared with the prior art, the utility model has the beneficial effects that:
according to the power supply controller structure for the satellite, an original external frame of the power supply controller is omitted, the circuit board and the power element are detached, the circuit board is arranged on the mounting frame, the power element is arranged on the front surface of the mounting plate of the mounting frame, and the mounting plate is connected with the body of the satellite. The heat generated by the power element is directly transferred to the mounting frame and then is emitted to the satellite body, so that the heat transfer process is reduced, and the heat dissipation effect is obviously improved. In addition, the reverse side of the mounting plate can be used for mounting other single-machine functional modules, such as a magnetic torquer, a lithium battery pack and the like. The power supply controller and other functional modules on the single machine are integrated on the mounting frame, so that the structure of the mounting frame is fully utilized, the space is saved to a great extent, and the weight of the whole satellite structure is reduced.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the following description will briefly explain the drawings needed in the description of the embodiments of the present utility model, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to the contents of the embodiments of the present utility model and these drawings without inventive effort for those skilled in the art.
Fig. 1 is a schematic structural diagram of a power controller structure for a satellite according to the present utility model;
fig. 2 is a schematic structural diagram of another view angle of the power controller structure for satellites according to the present utility model.
Reference numerals: 1. a circuit board; 11. a node; 2. a power element; 21. pins; 3. a mounting frame; 31. a mounting plate; 32. a support column; 4. an external plug-in unit; 5. and (5) mounting holes.
Detailed Description
In order to make the technical problems solved, the technical scheme adopted and the technical effects achieved by the utility model more clear, the technical scheme of the utility model is further described below by a specific embodiment in combination with the attached drawings.
In the description of the present utility model, unless explicitly stated and limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.
In the present utility model, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
In the description of the present utility model, the terms "upper," "lower," "left," "right," and the like are used for convenience of description and simplicity of operation based on the orientation or positional relationship shown in the drawings, and do not denote or imply that the apparatus or element in question must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the utility model. Furthermore, the terms "first," "second," and the like, are used merely for distinguishing between descriptions and not for distinguishing between them.
As shown in fig. 1 and 2, the present utility model provides a power controller structure for a satellite, including a circuit board 1, a power element 2, a mounting frame 3, a functional module, and a flying lead, the mounting frame 3 including a mounting plate 31. The mounting panel 31 is connected with the body of satellite, and circuit board 1 sets up on mounting bracket 3, and power component 2 sets up in the front of mounting panel 31, and the reverse side of mounting panel 31 is used for installing other functional module. The circuit board 1 and the power element 2 are electrically connected by a flying lead.
According to the structure of the power supply controller for the satellite, provided by the utility model, an external frame of an original power supply controller is omitted, the circuit board 1 and the power element 2 are detached, the circuit board 1 is arranged on the mounting frame 3, the power element 2 is arranged on the front surface of the mounting plate 31, and the mounting plate 31 is connected with a body in the satellite. The heat generated by the power element 2 is directly transferred to the mounting frame 3 and then is emitted to the satellite body, so that the heat transfer process is reduced, and the heat dissipation effect is obviously improved. In addition, in order to make full use of the structure of the mounting frame 3, the opposite side of the mounting plate 31 may be used for mounting other stand-alone functional modules, such as a magnetic torquer, a lithium battery pack, etc., and the mounting structure of the other stand-alone functional modules is not specifically described in this embodiment, and may be adjusted according to practical situations. The power supply controller and other functional modules on the single machine are integrated on the installation frame 3, so that the structure of the installation frame 3 is fully utilized, the space is saved to a great extent, and the weight of the whole satellite structure is reduced.
Alternatively, the functional module may be attached to the opposite side of the mounting plate 31 by fasteners such as screws.
Further, the side of the mounting plate 31 is provided with mounting holes 5, and the mounting holes 5 are connected with the body of the satellite. The mounting plate 31 is directly connected with the body of the satellite, so that heat generated by the power element 2 is directly conducted to the body of the satellite through the mounting plate 31, the heat dissipation effect is better, the mounting holes 5 are formed in the side face of the mounting plate 31, and the mounting plate 31 cannot interfere with other parts when being connected with the body of the satellite. Alternatively, the mounting plate 31 may be attached to the body of the satellite by fasteners such as screws.
Further, the mounting frame 3 further comprises at least two support columns 32. One end of the support column 32 is connected to the front surface of the mounting board 31, and the other end is connected to the circuit board 1. This scheme all sets up support column 32 and circuit board 1 in the front of mounting panel 31, and the another side of mounting panel 31 is used for installing other functional module on the satellite, and circuit board 1 passes through support column 32 to be set up on mounting panel 31, makes the area of mounting panel 31 that circuit board 1 occupy less, and this scheme make full use of the space of mounting panel 31.
Further, the circuit board 1 is disposed parallel to the mounting board 31, the distance between the circuit board 1 and the mounting board 31 is larger than the height of the power element 2, the power element 2 is provided in plurality, and at least part of the power element 2 is located between the circuit board 1 and the mounting board 31. According to the scheme, the circuit board 1 is arranged above the power element 2, the occupied area of the mounting plate 31 is further reduced in a space stacking mode, and the size of the mounting plate 31 is further reduced, so that the weight is reduced, and the occupied space is reduced.
Further, the power supply controller structure for the satellite further comprises an external plug-in unit 4, the external plug-in unit 4 is arranged on the circuit board 1, and the external plug-in unit 4 is electrically connected with the circuit board 1. Because the power component 2 is detached from the circuit board 1 and mounted on the mounting plate 31, the circuit board 1 has more vacant structures, and in order to fully utilize the vacant structures, the external plug-in unit 4 is arranged on the circuit board 1, so that the space utilization rate is higher.
Further, the external connector 4 is disposed at the peripheral edge of the circuit board 1, the external connector 4 is perpendicular to the circuit board 1, and the external connector 4 extends toward the mounting board 31. The position of the external connector 4 of this solution can further reduce the space occupied by the external connector 4.
Further, the power supply controller structure for the satellite further includes an insulating and heat conducting spacer disposed between the power element 2 and the mounting frame 3. The insulating heat conduction gasket of this scheme can further make the heat conduction effect better.
Preferably, the insulating thermal pad is a Bei Gesi thermal pad. Bei Gesi heat-conducting gasket is a high-performance heat-conducting insulator, has excellent heat-conducting property and insulating property, and is safe and reliable.
Further, the power element 2 includes a pin 21, the circuit board 1 is provided with a node 11, one end of the flying lead is connected with the pin 21, and the other end is connected with the node 11. The pin 21 of the scheme can facilitate and ensure the connection between the flying lead and the power element 2.
Further, the mount 3 is made of an aluminum alloy. The aluminum alloy has high strength, light weight, good heat conduction performance, good corrosion resistance and weldability.
Note that in the description of this specification, a description referring to terms "some embodiments", "other embodiments", and the like, means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the utility model. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing description is only of the preferred embodiments of the utility model and the technical principles employed. It will be understood by those skilled in the art that the present utility model is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the utility model. Therefore, while the utility model has been described in connection with the above embodiments, the utility model is not limited to the embodiments, but may be embodied in many other equivalent forms without departing from the spirit or scope of the utility model, which is set forth in the following claims.
Claims (10)
1. A power supply controller structure for a satellite, comprising a circuit board (1) and a power element (2), characterized in that the power supply controller structure for a satellite further comprises:
the installation frame (3), the installation frame (3) comprises an installation plate (31), the installation plate (31) is connected with the body of the satellite, the circuit board (1) is arranged on the installation frame (3), and the power element (2) is arranged on the front surface of the installation plate (31);
a functional module provided on the back surface of the mounting plate (31);
and a flying wire electrically connecting the circuit board (1) and the power element (2).
2. The power supply controller structure for satellites according to claim 1, characterized in that the mounting frame (3) further comprises:
and one end of each support column (32) is connected with the front surface of the mounting plate (31), and the other end of each support column (32) is connected with the circuit board (1).
3. The power supply controller structure for satellites according to claim 2, characterized in that the circuit board (1) is disposed parallel to the mounting board (31), a distance between the circuit board (1) and the mounting board (31) is larger than a height of the power element (2), the power element (2) is provided in plurality, and at least part of the power element (2) is located between the circuit board (1) and the mounting board (31).
4. A power controller structure for a satellite according to claim 3, further comprising an external connector (4), the external connector (4) being arranged on the circuit board (1), the external connector (4) being electrically connected to the circuit board (1).
5. The power controller structure for satellites according to claim 4, wherein the external connector (4) is provided at a peripheral edge of the circuit board (1), the external connector (4) being perpendicular to the circuit board (1), the external connector (4) extending toward the mounting board (31).
6. The power controller structure for satellites according to any one of claims 1 to 5, further comprising an insulating and thermally conductive gasket arranged between the power element (2) and the mounting frame (3).
7. The power controller architecture for a satellite of claim 6, wherein the insulating thermally conductive gasket is a Bei Gesi thermally conductive gasket.
8. A power supply controller structure for satellites according to any one of claims 1-5, characterized in that the power element (2) comprises a pin (21), a node (11) is provided on the circuit board (1), one end of the flying wire is connected to the pin (21), and the other end is connected to the node (11).
9. The power controller structure for a satellite according to any one of claims 1 to 5, wherein a mounting hole (5) is provided at a side of the mounting plate (31), and the mounting hole (5) is connected to a body of the satellite.
10. Power supply controller structure for satellites according to any one of claims 1 to 5, characterized in that the mounting frame (3) is made of aluminium alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223130971.7U CN219305247U (en) | 2022-11-24 | 2022-11-24 | Power supply controller structure for satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223130971.7U CN219305247U (en) | 2022-11-24 | 2022-11-24 | Power supply controller structure for satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219305247U true CN219305247U (en) | 2023-07-04 |
Family
ID=86953379
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223130971.7U Active CN219305247U (en) | 2022-11-24 | 2022-11-24 | Power supply controller structure for satellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219305247U (en) |
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2022
- 2022-11-24 CN CN202223130971.7U patent/CN219305247U/en active Active
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