Satellite operating system cold start load shedding method and device, equipment and storage medium

Abstract

The invention discloses a cold start load shedding method for a satellite operating system, which is suitable for solving the problem of operation stability recovery after abnormal power failure and restart due to overlarge power load during in-orbit operation of a spaceborne computer. The method comprises a cold start judgment process and a load shedding process. The cold start judgment mode is star time judgment, the start mode of the computer is judged according to the counting state of a 48-bit clock on the FPGA, if the judgment result is cold start, a load shedding instruction is sent, the high-power-consumption single machine is closed, and the whole process is completed before an operating system is started. According to the invention, after the on-board computer is powered off and restarted, the system load shedding can be completed in the shortest time, the satellite energy safety is ensured, and the operation stability of the satellite system is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace electronics, and in particular relates to a method, device, equipment and storage medium for cold start load reduction of a satellite operating system. Background Art

[0002] The onboard computer is a crucial component of the satellite platform, responsible for core tasks such as satellite operations management, telemetry and remote control, attitude and orbit control, and energy management. Its reliability directly impacts the operational reliability of the entire satellite system. Due to the unique characteristics of satellite operating spaces, onboard computers have limited maintainability and must operate continuously under normal circumstances. If the computer loses power, ground control cannot be achieved through commands or by obtaining information about the satellite system's status. If power cannot be restored, the entire satellite system may fail, resulting in significant economic losses.

[0003] As the complexity of aerospace engineering continues to increase, satellite systems are becoming increasingly large. Furthermore, the harsh operating environment of satellites in space can cause damage to power subsystems. As a result, excessive power consumption in these subsystems occasionally causes computer power outages during satellite in-orbit operations. A search has revealed no effective measures to restore satellite system stability. If no special actions are taken after power is restored to the computer, the power outage is likely to recur. Summary of the Invention

[0004] The purpose of the present invention is to provide a satellite operating system cold start load reduction method, which can reduce the power consumption load of the satellite system in the shortest time when the onboard computer is powered on again, ensure the satellite energy security, and ensure the stable operation of the basic functions of the satellite platform.

[0005] In order to solve the above problems, the technical solution of the present invention is: A satellite operating system cold start load reduction method, comprising: After the onboard computer is powered on, the system startup status is automatically determined by the satellite time. If it is a cold start, the satellite operating system enters the load reduction process, obtains the pre-stored list of high-power stand-alone machines, and sends OC commands to all high-power stand-alone machines in sequence to power off the high-power stand-alone machines. The satellite operating system is reduced to the minimum working system to prevent the satellite operating system from losing power again due to excessive load. Among them, judging the system startup status by star time includes: Obtain the count value of the star time recorder and compare it with the preset threshold. If it is less than the preset threshold, it is determined to be a cold start, otherwise it is a hot start.

[0006] According to one embodiment of the present invention, after the onboard computer is initialized and before the normal startup process of the satellite operating system, the system startup status is automatically determined by satellite time, thereby avoiding time consumption of the satellite operating system startup, completing the satellite operating system load reduction in the shortest time, and ensuring the stable operation of the minimum working system.

[0007] According to an embodiment of the present invention, the satellite operating system enters the load reduction process further comprising: Read the pre-stored list of high-power stand-alone machines, obtain the communication interfaces of each high-power stand-alone machine, and send OC instructions to the communication interfaces of each high-power stand-alone machine through the RS422 interface, so that the high-power stand-alone machine that receives the OC instruction will immediately perform the power-off operation. The satellite operating system is reduced to the minimum working system including power supply, computer platform, telemetry and remote control, and attitude and orbit control subsystems.

[0008] According to an embodiment of the present invention, when sending an OC command to the communication interface of each high-power stand-alone machine, multiple repeated sending operations are performed to ensure that each high-power stand-alone machine receives the OC command.

[0009] According to an embodiment of the present invention, determining the system startup status by using the star time further includes: Based on the timing characteristics of the temperature-compensated crystal oscillator 48-bit clock, if power is off, the count value will be reset to zero and will start counting from zero after power is restored; Read the star time recorded by the temperature-compensated crystal oscillator 48-bit clock, convert the star time into hours, and compare it with the preset threshold. If it is less than the preset threshold, it is determined to be a cold start, otherwise it is a hot start.

[0010] A satellite operating system cold start load reduction device, comprising: The cold start judgment module is configured to automatically judge the system startup status through satellite time after the onboard computer is powered on. If it is a cold start, the satellite operating system enters the load reduction process; if it is a hot start, no processing is performed; The load shedding module is configured to obtain a pre-stored list of high-power standalone machines and send OC commands to all of them in sequence, so that they are powered off and the satellite operating system is reduced to the minimum working system, thus preventing the satellite operating system from losing power again due to excessive load. Wherein, the cold start judgment module is further configured to: Obtain the count value of the star time recorder and compare it with the preset threshold. If it is less than the preset threshold, it is determined to be a cold start, otherwise it is a hot start.

[0011] A satellite operating system cold start load reduction device comprises a memory and a processor, wherein the memory stores computer-readable instructions, and when the processor executes the computer-readable instructions, the satellite operating system cold start load reduction method is implemented.

[0012] A computer-readable medium stores a computer program, which, when executed by one or more processors, implements the satellite operating system cold start load reduction method.

[0013] Due to the adoption of the above technical solution, the present invention has the following advantages and positive effects compared with the prior art: A satellite operating system cold start load reduction method, according to one embodiment of the present invention, addresses the issue of unstable satellite system operation caused by abnormal power failure and restart of onboard computers during on-orbit operation due to excessive power consumption. By quickly performing satellite rescue operations after the computer is powered back on, the system startup status is determined using satellite time before the operating system is restarted. If a cold start is detected, a load reduction command is sent to a high-power standalone computer. Upon receiving the command, the high-power standalone computer is powered off, effectively reducing satellite system power consumption. The process is simple and efficient. This method can reduce the power consumption load of the satellite system in the shortest possible time, ensuring stable operation of the minimum operating system, including the power supply, computer platform, telemetry and remote control, and attitude and orbit control subsystems. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a flow chart of a cold start load reduction method for a satellite operating system according to an embodiment of the present invention; Figure 2 This is a process flow chart of the operating system after the onboard computer is powered on in one embodiment of the present invention; Figure 3 This is a block diagram of a satellite operating system cold start load reduction device in one embodiment of the present invention; Figure 4 Schematic diagram of a satellite operating system cold start load reduction device in one embodiment of the present invention. DETAILED DESCRIPTION

[0015] The following is a detailed description of a satellite operating system cold start load reduction method, device, equipment and storage medium proposed by the present invention in conjunction with the accompanying drawings and specific embodiments. The advantages and features of the present invention will become more apparent from the following description and claims.

[0016] Please see Figure 1 This embodiment provides a method for cold start load reduction of a satellite operating system, including: After the onboard computer is powered on, the system startup status is automatically determined by the satellite time. If it is a cold start, the satellite operating system enters the load reduction process, obtains the pre-stored list of high-power stand-alone machines, and sends OC commands to all high-power stand-alone machines in turn to power off the high-power stand-alone machines. The satellite operating system is reduced to the minimum working system to prevent the satellite operating system from losing power again due to excessive load.

[0017] For details, please see Figure 2After the onboard computer is powered on, the operating system first initializes the device to prepare for subsequent command transmission. Next, the operating system automatically determines the star time. The star time determination process is as follows: read the 48-bit clock located on the FPGA, compare the star time stored in the 48-bit clock with the 10-hour threshold, and if the star time is within 10 hours, it is determined that the star time has returned to the initial state and the computer starts in a cold boot mode, otherwise it is a hot boot mode. Since the time unit of the 48-bit clock is 0.1ms, the time unit needs to be converted when determining the star time.

[0018] If the satellite's time determination indicates a hot boot, it indicates the onboard computer has not experienced a power outage within a short period of time, and the operating system boots normally without any special processing. If the determination indicates a cold boot, the operating system enters a load reduction process, which involves obtaining the address of a list of high-power standalone computers, reading the list, and sequentially sending an OC command to each computer indicated by an entry. This process is repeated three times to ensure that each computer correctly receives the command and improve reliability. The high-power standalone computer list is pre-set in the operating system and lists the satellite's high-power standalone computers, such as the payload unit. The OC command is a shutdown command for the onboard processor and is sent via the RS422 port.

[0019] Upon receiving the OC command, the high-power stand-alone computer immediately performs a power-off operation. After the power-off is complete, the satellite system is reduced to a minimum operating system, effectively reducing the power consumption load, ensuring the satellite's energy security, and maintaining the operational stability of the satellite system. After the load shedding process is completed, the operating system enters the normal startup process. Because the cold start determination and load shedding method in this embodiment precede the operating system startup process, the timeliness of the load shedding process is maximized. After powering back on, the onboard computer completes the satellite system load shedding in the shortest possible time, thus preventing the satellite base platform from losing power again due to excessive load, which could cause the satellite system to fail to operate normally.

[0020] This embodiment also provides a satellite operating system cold start load reduction device to apply the above satellite operating system cold start load reduction method. Figure 3 , the device comprises: The cold start judgment module is configured to automatically judge the system startup status through satellite time after the onboard computer is powered on. If it is a cold start, the satellite operating system enters the load reduction process; if it is a hot start, no processing is performed; The load reduction module is configured to obtain a pre-stored list of high-power stand-alone machines and send OC instructions to all high-power stand-alone machines in sequence to power off the high-power stand-alone machines and reduce the satellite operating system to the minimum working system, thereby preventing the satellite operating system from losing power again due to excessive load.

[0021] The implementation of the cold start judgment module and the load reduction module is as described in the above method and will not be repeated here.

[0022] The above device describes the satellite operating system cold start load reduction device in detail from the perspective of modular functional entities. The following describes the satellite operating system cold start load reduction device in detail from the perspective of hardware processing.

[0023] Please see Figure 4 The satellite operating system cold start load shedding device 500 may vary significantly depending on configuration or performance. It may include one or more central processing units (CPUs) 510 (e.g., one or more processors), memory 520, and one or more storage media 530 (e.g., one or more mass storage devices) storing application programs 533 or data 532. The memory 520 and storage media 530 may be either ephemeral or persistent storage. The programs stored in the storage medium 530 may include one or more modules (not shown), each of which may include a series of instructions operating on the satellite operating system cold start load shedding device 500.

[0024] Furthermore, the processor 510 may be configured to communicate with the storage medium 530 and execute a series of instruction operations in the storage medium 530 on the satellite operating system cold start load reduction device 500 .

[0025] The satellite operating system cold start load reduction device 500 may further include one or more power supplies 540, one or more wired or wireless network interfaces 550, one or more input and output interfaces 560, and / or one or more operating systems 531, such as AIC-OS, Linux, etc.

[0026] Those skilled in the art will understand that Figure 4 The structure of the satellite operating system cold start load reduction device shown does not constitute a limitation on the satellite operating system cold start load reduction device, and may include more or fewer components than shown in the figure, or combine certain components, or arrange the components differently.

[0027] The present invention also provides a computer-readable storage medium, which may be a non-volatile computer-readable storage medium or a volatile computer-readable storage medium. The computer-readable storage medium stores instructions that, when executed on a computer, cause the computer to execute the steps of the satellite operating system cold start load reduction method of Example 1.

[0028] If the modules in the satellite operating system cold start load reduction device are implemented as software functional modules and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the portion that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of software. This computer software is stored in a storage medium and includes several instructions for enabling a computer device (which can be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in various embodiments of the present invention. The aforementioned storage media include various media capable of storing program code, such as USB flash drives, mobile hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0029] Those skilled in the art will clearly understand that, for the convenience and brevity of description, the specific working processes of the above-described devices and equipment can refer to the corresponding processes in the aforementioned method embodiments and will not be repeated here.

[0030] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, if these changes fall within the scope of the claims of the present invention and their equivalents, they still fall within the scope of protection of the present invention.

Claims

1. A method for cold start load reduction of a satellite operating system, characterized in that: include: After the onboard computer is powered on, the system startup status is automatically determined by the satellite time. If it is a cold start, the satellite operating system enters the load reduction process, obtains the pre-stored list of high-power stand-alone machines, and sends OC commands to all high-power stand-alone machines in sequence to power off the high-power stand-alone machines. The satellite operating system is reduced to the minimum working system to prevent the satellite operating system from losing power again due to excessive load. Among them, judging the system startup status by star time includes: Obtain the count value of the star time recorder and compare it with the preset threshold. If it is less than the preset threshold, it is determined to be a cold start, otherwise it is a hot start.

2. The satellite operating system cold start load reduction method according to claim 1, wherein: After the onboard computer is initialized and before the normal startup process of the satellite operating system, the system startup status is automatically judged by the satellite time to avoid time consumption of the satellite operating system startup, complete the satellite operating system load reduction in the shortest time, and ensure the stable operation of the minimum working system.

3. The satellite operating system cold start load reduction method according to claim 1, wherein: The satellite operating system enters the load reduction process further including: Read the pre-stored list of high-power stand-alone machines, obtain the communication interfaces of each high-power stand-alone machine, and send OC instructions to the communication interfaces of each high-power stand-alone machine through the RS422 interface, so that the high-power stand-alone machine that receives the OC instruction will immediately perform the power-off operation. The satellite operating system is reduced to the minimum working system including power supply, computer platform, telemetry and remote control, and attitude and orbit control subsystems.

4. The satellite operating system cold start load reduction method according to claim 3, wherein: When sending an OC command to the communication interface of each high-power stand-alone machine, multiple repeated transmissions are performed to ensure that each high-power stand-alone machine receives the OC command.

5. The satellite operating system cold start load reduction method according to claim 1, wherein: Judging the system startup status by star time further includes: Based on the timing characteristics of the temperature-compensated crystal oscillator 48-bit clock, if power is off, the count value will be reset to zero and will start counting from zero after power is restored; Read the star time recorded by the 48-bit clock of the temperature-compensated crystal oscillator, convert the star time into hours, and compare it with the preset threshold. If it is less than the preset threshold, it is determined to be a cold start, otherwise it is a hot start.

6. A satellite operating system cold start load reduction device, characterized in that: include: The cold start judgment module is configured to automatically judge the system startup status through satellite time after the onboard computer is powered on. If it is a cold start, the satellite operating system enters the load reduction process; If it is a hot start, no processing is performed; The load shedding module is configured to obtain a pre-stored list of high-power standalone machines and send OC commands to all of them in sequence, so that they are powered off and the satellite operating system is reduced to the minimum working system, thus preventing the satellite operating system from losing power again due to excessive load. Wherein, the cold start judgment module is further configured to: Obtain the count value of the star time recorder and compare it with the preset threshold. If it is less than the preset threshold, it is determined to be a cold start, otherwise it is a hot start.

7. A satellite operating system cold start load reduction device, characterized in that: The method comprises a memory and a processor, wherein the memory stores computer-readable instructions, and when the processor executes the computer-readable instructions, the method for cold start load reduction of a satellite operating system according to any one of claims 1 to 5 is implemented.

8. A computer-readable medium storing a computer program, characterized in that: When the computer program is executed by one or more processors, the satellite operating system cold start load reduction method according to any one of claims 1 to 5 is implemented.

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