Control module suitable for space environment

Abstract

The invention provides a control module suitable for a space environment. The control module comprises a main control computer board, an isolator and an electronic fuse. The main control computer board is provided with a processor, a transmission interface and a power interface. The isolator is connected between the processor and the transmission interface and is used for blocking and isolating the damage of the external environment to the system. The electronic fuse is connected between the processor and the power interface and used for detecting the abnormal state of the system and generating a detection result according to the abnormal state of the system. Wherein the electronic fuse selectively cuts off the electrical connection between the processor and the power interface according to the detection result, and the isolator selectively stops the transmission interface from transmitting the data signal according to the detection result.

Description

Technical Field

[0001] The present application relates to a control module, and in particular to a control module suitable for a space environment. Background Art

[0002] Because the space environment differs from the surface environment, conventional computers are generally not suitable for operation in space. For example, satellite computers designed for use in space environments are often composed of simple control modules. Due to the limited space and power supply on spacecraft or space stations, control modules must be extremely small while also being highly efficient and low-power. However, the control modules currently used in satellite computers are insufficiently efficient and lack protection against interference from the space environment, making them incapable of supporting new satellite applications. Consequently, the industry needs a new control module suitable for space environments that can improve satellite performance and adaptability in space environments. Summary of the Invention

[0003] The technical problem to be solved by this application is to provide a control module suitable for space environment, which has the ability to resist anomalies such as overcurrent and overvoltage in space environment, and can provide electrostatic protection in space environment.

[0004] This application proposes a control module suitable for use in a space environment, comprising a main control computer board, an isolator, and an electronic fuse. The main control computer board includes a processor, a transmission interface, and a power interface. The isolator is connected between the processor and the transmission interface to transmit data signals. The electronic fuse is connected between the processor and the power interface to detect system abnormalities and generate a detection result based on the abnormality. The electronic fuse selectively disconnects the electrical connection between the processor and the power interface based on the detection result, and the isolator selectively stops the transmission interface from transmitting data signals based on the detection result.

[0005] In one embodiment, the electronic fuse dynamically adjusts detection conditions based on a set command, and the detection conditions are used to determine whether a system abnormality exists. Furthermore, after the electronic fuse disconnects the electrical connection between the processor and the power interface, it restores the electrical connection between the processor and the power interface based on a reset command. Furthermore, the isolator is further configured to process data signals to reduce data signal distortion. Furthermore, the isolator selectively disconnects the electrical connection between the processor and the transmission interface when the main control computer board is shut down.

[0006] To sum up, the control module suitable for space environment provided in this application is equipped with an isolator and an electronic fuse, so that it can resist abnormalities such as overcurrent and overvoltage in the space environment, and can provide electrostatic protection in the space environment.

[0007] The details of other functions and embodiments of the present application are described below with reference to the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments recorded in this application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0009] Figure 1 This is a functional diagram of a control module suitable for a space environment according to an embodiment of the present application.

[0010] Explanation of symbols

[0011] 1: Control module suitable for space environment

[0012] 10: Main control computer board 100: Processor

[0013] 102: Transmission interface 104: Power interface

[0014] 106: Isolator 108: Electronic fuse DETAILED DESCRIPTION

[0015] The positional relationships described in the following embodiments include up, down, left, and right. Unless otherwise specified, they are based on the directions of the components shown in the drawings.

[0016] See also Figure 1 , Figure 1 This is a functional diagram of a control module suitable for a space environment according to an embodiment of the present application. Figure 1 As shown, the control module 1 demonstrated in this embodiment can be applied to a space environment, for example, it can be used alone or assembled in a satellite computer to assist the operation of a satellite or a space station. In addition, the control module 1 can also be connected to external devices, such as other control modules, computing cards, or devices with various functions, which are not limited in this embodiment. In practice, there are many factors in the space environment that can easily cause abnormalities in satellite computers, such as space dust and particles, cosmic radiation, solar wind, and drastic temperature changes. In order to prevent the above-mentioned undesirable factors from affecting the operation of a satellite or a space station, the control module 1 demonstrated in this embodiment includes, in addition to a main control computer board 10 with computing capabilities, an isolator 12 and an electronic fuse 14. The following describes the specific functions of the control module 1 of this embodiment.

[0017] The main control computer board 10 includes a processor 100, a transmission interface 102, and a power interface 104. In practice, the processor 100 is used to perform various operations. For example, the processor 100 can be a microprocessor chip such as a Cortex-M7. The transmission interface 102 can be used to electrically connect to other control modules, computing cards, or devices with various functions, allowing data signals to be sent or received between these devices and the processor 100 of the main control computer board 10. The power interface 104 is an interface for receiving power supplied to the main control computer board 10. In one example, the main control computer board 10 is part of a satellite computer, and the transmission interface 102 is connected to other circuits. In this case, data signals are susceptible to interference from other circuits or space noise. Furthermore, the transmission interface 102 could be damaged by various space environmental anomalies, such as overvoltage surges, overcurrent surges, space radiation heat, space dust and particles, and other factors, potentially damaging the internal components of the main control computer board 10. Accordingly, the main control computer board 10 is provided with an isolator 106 between the processor 100 and the transmission interface 102. The isolator 106 can electrically connect the processor 100 and the transmission interface 102 to ensure that the data signal can be transmitted correctly and block the damage to the system from the external environment (space environment).

[0018] In practice, the isolator 106 is an isolation switch used to isolate the main control computer board 10 from other circuits, reducing the impact of signal interference between different circuits. Furthermore, the isolator 106 can also process data signals to reduce the degree of distortion (or the possibility of signal distortion) when subject to external interference such as space noise, thereby improving the reliability and stability of the data signals. Furthermore, the isolator 106 can selectively cut off the electrical connection between the processor 100 and the transmission interface 102 when the main control computer board 10 is shut down, preventing current or voltage surges from damaging the processor 100. In one example, space dust and particles may rub against each other and generate static electricity. The isolator 106 can also isolate the static electricity caused by space dust and particles from impacting the transmission interface 102 and damaging the processor 100.

[0019] Similarly, the power interface 104 may also receive abnormal inputs such as current or voltage surges. Accordingly, the main control computer board 10 is provided with an isolator 106 between the processor 100 and the power interface 104. The electronic fuse 108 can detect abnormal system conditions and generate corresponding detection results. For example, the electronic fuse 108 can detect abnormal overcurrent and overvoltage surges. In practice, when the electronic fuse 108 detects an overcurrent or overvoltage surge, it can be determined as an abnormal system condition and the electrical connection between the processor 100 and the power interface 104 can be cut off to prevent the overcurrent or overvoltage surge from attacking the processor 100 or other internal components. In one example, the electronic fuse 108 can dynamically adjust the criteria for determining overcurrent and overvoltage surges. For example, the electronic fuse 108 can dynamically adjust the standard ranges (detection conditions) of current and voltage based on set instructions, thereby subsequently determining whether the current or voltage exceeds the new standard ranges.

[0020] For another example, the electronic fuse 108 can also detect whether the main control computer board 10 is abnormally overheating. When the main control computer board 10 is overheated, the electronic fuse 108 can cut off the electrical connection between the processor 100 and the power interface 104 to prevent the processor 100 or other internal components from continuing to heat up and causing damage. When the system abnormal state is resolved (or the main control computer board 100 is restored to the default state), the electronic fuse 108 can reconnect the processor 100 and the power interface 104 according to the reset instruction. This embodiment does not limit the source of the setting instruction and the reset instruction. For example, the setting instruction and the reset instruction can be issued by the satellite computer itself or by other external devices. It is worth mentioning that the detection result generated by the electronic fuse 108 when detecting the system abnormal state can also be provided to the isolator 106, so that the isolator 106 can decide whether to cut off the electrical connection between the processor 100 and the transmission interface 102 based on the detection result and stop transmitting the data signal.

[0021] To sum up, the control module suitable for space environment provided in this application is equipped with an isolator and an electronic fuse, so that it can resist abnormalities such as overcurrent and overvoltage in the space environment, and can provide electrostatic protection in the space environment.

[0022] The embodiments and / or implementation methods described above are only used to illustrate the preferred embodiments and / or implementation methods for realizing the technology of the present application, and do not impose any form of limitation on the implementation methods of the technology of the present application. Any person skilled in the art may make slight changes or modifications to other equivalent embodiments without departing from the scope of the technical means disclosed in the content of the present application, but they should still be regarded as technologies or embodiments that are essentially the same as those of the present application.

Claims

1. A control module suitable for a space environment, characterized in that: The control module includes: A main control computer board having a processor, a transmission interface and a power interface; an isolator connected between the processor and the transmission interface for transmitting a data signal; and an electronic fuse connected between the processor and the power interface, for detecting a system abnormality and generating a detection result according to the system abnormality; The electronic fuse selectively cuts off the electrical connection between the processor and the power interface according to the detection result, and the isolator selectively stops the transmission interface from transmitting the data signal according to the detection result.

2. The control module suitable for space environment according to claim 1, characterized in that: The electronic fuse dynamically adjusts a detection condition according to a setting instruction, and the detection condition is used to determine whether the system is in an abnormal state.

3. The control module suitable for a space environment according to claim 1, characterized in that: After the electronic fuse cuts off the electrical connection between the processor and the power interface, the electronic fuse further restores the electrical connection between the processor and the power interface according to a reset instruction.

4. The control module suitable for a space environment according to claim 1, characterized in that: The isolator is further used for signal processing the data signal to reduce the distortion of the data signal.

5. The control module suitable for space environment according to claim 1, characterized in that: The isolator selectively cuts off the electrical connection between the processor and the transmission interface when the main control computer board is shut down.

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