Thermal control management system in normal state and emergency state of satellite orbiting

Abstract

The application provides a thermal control management system in a normal state of satellite orbiting and an emergency state, comprising a thermal control subsystem thermal control table, a thermal control measure and original code corresponding relation table, an instruction number package format and a thermal control instruction number package. During satellite orbiting operation, the thermal control scheme is modified according to the actual operation stage and the thermal environment, the thermal control subsystem thermal control table is provided by the thermal control subsystem according to a certain format, the corresponding instruction code data field content is found according to the defined thermal control measure and original code corresponding relation table, and the thermal control instruction number package is automatically generated according to the thermal control number instruction package format. Through the method, the efficiency of the in-orbit regulation and control of the thermal control scheme can be effectively improved.

Description

Technical Field

[0001] This invention belongs to the field of satellite thermal control management technology, specifically relating to a thermal control management system for satellites under normal emergency conditions during orbit insertion. Background Technology

[0002] With the rapid development of aerospace technology, the stability and reliability of satellites in orbit have become crucial indicators for evaluating their performance. Among the many factors affecting satellite performance, thermal management is a critical element. During in-orbit operation, satellites encounter various complex thermal environments, such as solar radiation, Earth's albedo, and space debris collisions. These factors directly affect the satellite's thermal balance and its overall operation. Furthermore, the thermal environment varies at different stages of a satellite's lifecycle, such as the orbit insertion phase, the normal operation phase, and the emergency phase, requiring different thermal management measures. Therefore, an effective thermal control management system is essential for maintaining satellite stability and extending its lifespan.

[0003] Traditional thermal control management systems typically employ pre-set thermal control schemes, which are determined before satellite launch and lack the flexibility to handle various emergencies encountered during on-orbit operation. When a satellite encounters an abnormal thermal environment or requires specific operations for rescue, this pre-set thermal control scheme cannot be adjusted in time and is difficult to adapt to complex thermal environments. For example, patent document CN110294146A provides a method for autonomous on-orbit operation management of a spacecraft thermal control system, including the following steps: (1) The software initialization submodule provides initial values ​​of the thermal control system parameters; (2) The data acquisition submodule is called to acquire temperature data, spacecraft operating mode, and reference voltage; (3) The data processing submodule is called to calibrate temperature data according to the reference voltage; select temperature data for closed-loop temperature control and perform validity judgment; select the temperature control threshold through the spacecraft operating mode; (4) After completing data acquisition and processing, it is judged whether the spacecraft has entered a safe mode. The judgment result is that it is in normal operating mode or safe mode, and subsequent operations are performed according to the judgment result.

[0004] To overcome these limitations, there is an urgent need to develop a thermal control management system that can adapt to the satellite's orbital insertion phase, normal phase, and emergency phase, enabling on-orbit modification of the thermal control management scheme and meeting the satellite's variable thermal control management needs in the complex space thermal environment. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the purpose of this invention is to provide a thermal control management system for satellites in normal emergency conditions during orbit insertion.

[0006] A thermal control management system for satellites in normal emergency conditions during orbit insertion, provided by the present invention, includes: a thermal control subsystem and a thermal control scheme modification module;

[0007] Thermal control subsystem: Provides a large thermal control information table with information on heater switches and temperature measuring points under three states: satellite orbit insertion, normal operation, and emergency. The large thermal control information table includes information on heater switches and information on temperature measuring points.

[0008] Thermal control scheme modification module: Based on the actual operating stage and the thermal environment, the thermal control scheme can be modified by adjusting the thermal control information table.

[0009] Preferably, the relevant information of the heater switch includes: the name of the heater switch, the instruction code of the heater switch, the telemetry name of the heater switch status, and the telemetry address of the heater switch status;

[0010] The relevant information of the temperature measurement point includes: the temperature measurement point used, the name of the temperature measurement point telemetry, the address of the temperature measurement point telemetry, the temperature calculation strategy and entry into orbit, and the upper and lower limit thresholds for temperature control under normal and emergency conditions.

[0011] Preferably, the injection number package is modified according to the ground-based heat control measures, and the heat control information table is adjusted accordingly.

[0012] Preferably, the thermal control subsystem searches for the corresponding instruction code data field content according to the defined thermal control measures and original code correspondence table, and automatically generates a thermal control instruction package according to the thermal control instruction package format.

[0013] Preferably, the acquisition addresses for the heater switch status telemetry and the acquisition addresses for the temperature measurement point telemetry are pre-stored in the form of a telemetry acquisition channel.

[0014] Preferably, temperature control measures are only implemented when both the heater switch status and the temperature value at the corresponding temperature measuring point meet the conditions for implementing temperature control measures.

[0015] According to the present invention, a thermal control management method for satellites in normal emergency states during orbit insertion is provided, wherein the thermal control management system for satellites in normal emergency states during orbit insertion is used for thermal control management.

[0016] Preferably, during the satellite's operation in orbit, the on / off status of the heater and the temperature value of the temperature measuring point are polled periodically to determine whether the conditions for implementing thermal control management measures are met, and the corresponding thermal control management measures are implemented.

[0017] Preferably, when the ground needs to adjust the satellite thermal control management measures, the thermal control measures modification data package is modified according to a certain format.

[0018] Preferably, when it is determined that temperature control measures need to be implemented, the on or off command code of the heater to be controlled is first retrieved, and then the switch of the heater is controlled to adjust the temperature; when the thermal control management measures of the satellite need to be adjusted on the ground, the temperature measurement point, temperature calculation strategy, and upper and lower threshold values ​​of temperature control under normal emergency conditions are modified through the upper-level data instruction package.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] 1. This invention establishes a standardized thermal control information table with strong versatility. This table includes all the information required for developing a thermal control management system and is applicable to different satellite models. The thermal control management system can directly read the thermal control information table, is easy to operate and modify, significantly improving the work efficiency of software developers and substantially enhancing the automation level of satellite on-orbit temperature control.

[0021] 2. The thermal control management system of this invention has strong real-time performance in implementing thermal control management measures. The short cycle of each polling of the heater switch status telemetry and the temperature telemetry of the measuring point meets the requirement of rapid temperature response. The thermal control management system implements thermal control management measures based on the heater switch status and the corresponding temperature of the measuring point. Its logic is simple and highly reliable, avoiding the problem of slow response caused by complex logic in thermal control management systems.

[0022] 3. The thermal control management system of the present invention can flexibly modify the number of temperature measurement points, temperature calculation strategies and temperature control thresholds in the three modes of orbit insertion, normal operation and emergency operation according to the actual operating environment conditions during satellite operation. This solves the problem that the thermal control management system program is fixed and therefore cannot be modified or can only be completely reconstructed. Attached Figure Description

[0023] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0024] Figure 1 This is a flowchart of the implementation method of the orbital normal emergency thermal control management system of the present invention;

[0025] Figure 2 This is a temperature control flowchart of the thermal control management system of the present invention. Detailed Implementation

[0026] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0027] Figure 1 This is a flowchart of the implementation method of the orbital normal emergency thermal control management system of the present invention.

[0028] The present invention provides an on-orbit routine emergency thermal control management system, comprising: a thermal control subsystem thermal control table, a thermal control measure-to-original code correspondence table, an instruction annotation package format, and a thermal control instruction annotation package. During satellite on-orbit operation, the thermal control scheme is modified according to the actual operational stage and the required thermal environment. The thermal control subsystem provides a thermal control table in a specific format. The system then searches for the corresponding instruction code data field content based on the defined thermal control measure-to-original code correspondence table and automatically generates a thermal control instruction annotation package according to the thermal control annotation package format. This method effectively improves the efficiency of on-orbit thermal control scheme regulation.

[0029] like Figure 1 As shown, the implementation method of the orbital normal emergency thermal control management system of the present invention includes the following steps:

[0030] S11: The thermal control subsystem provides a large table of thermal control information in a specific format, showing heater switching and temperature measurement point information under three conditions: satellite orbit insertion, normal operation, and emergency.

[0031] The information related to the heater switch in the thermal control information table includes the name of the heater switch, the instruction code of the heater switch, the telemetry name of the heater switch status, and the telemetry address of the heater switch status; the information related to the temperature measurement point includes the temperature measurement point used, the telemetry name of the temperature measurement point, the telemetry address of the temperature measurement point, the temperature calculation strategy, and the upper and lower limit thresholds for temperature control under normal and emergency conditions, as shown in the table below.

[0032]

[0033] S12: The satellite thermal control management system reads the thermal control information table and pre-stores relevant information about heater switches and temperature measurement points in the thermal control information table.

[0034] The satellite thermal control management system reads the thermal control information table and stores the data in the table, such as the acquisition address of the heater switch status telemetry, the instruction code sent when implementing temperature control measures, the number of temperature measurement points used, the acquisition address of the temperature measurement point telemetry, the temperature calculation strategy of the temperature measurement point and the upper and lower temperature control thresholds under normal and emergency conditions, in the Flash or MRAM memory of the thermal control management system.

[0035] The acquisition addresses for the heater switch status telemetry and the acquisition addresses for the temperature measurement point telemetry are pre-stored in the form of telemetry acquisition channels.

[0036] The acquisition channel includes the APID of the telemetry packet, the byte number, the bit number, and the number of bits of the telemetry parameters.

[0037] In the table, 0xAAA and 0xBBB represent the Application Process Identifier (APID) of the telemetry packet, a and b represent the byte position number of the telemetry in the telemetry packet, and m and n represent the number of bits of the telemetry in the whole byte telemetry.

[0038] S13: During the satellite's on-orbit operation, the thermal control management system periodically polls the on / off status of the heaters and the temperature values ​​at the measuring points to determine whether the conditions for implementing thermal control management measures are met, and then implements the corresponding thermal control management measures.

[0039] S14: When the ground needs to adjust the satellite thermal control management measures, modify the thermal control measures according to a certain format in the data package.

[0040] Figure 2 This is a flowchart of the temperature control process of the thermal control management system of the present invention, as follows: Figure 2 As shown, the temperature control process of the thermal control management system of the present invention includes the following steps:

[0041] Step S21: The thermal control management system retrieves the telemetry data of the heater switch status and the temperature measurement point from the telemetry packets returned to the satellite's onboard computer by each subsystem on the satellite at regular intervals based on the pre-stored acquisition address information.

[0042] Step S22: The thermal control management system sets the conditions for executing temperature control measures based on the heater switch status and the temperature value of the corresponding temperature measuring point.

[0043] Temperature control measures will only be implemented when both the heater's on / off state and the temperature value at the corresponding measuring point meet the conditions for their execution.

[0044] For example, if a heater is in a closed state, and the remote temperature measurement value of the temperature measuring point in the area where it is temperature controlled is lower than the lower limit of the temperature threshold, then the conditions for the temperature control measures to turn on the heater are met.

[0045] Step S23: During the satellite's on-orbit operation, the thermal control management system polls the on / off status of the heaters and the temperature values ​​of the measuring points at regular intervals.

[0046] If the heater's on / off state and the temperature at the measuring point both meet the conditions for implementing temperature control measures, then the temperature control measures will be implemented; otherwise, they will not be implemented.

[0047] If the temperature control measures fail to be implemented or the temperature remains within the range of the temperature control measures after implementation, the error information will be fed back to the ground in the form of telemetry.

[0048] Step S24: When the thermal control management system determines that temperature control measures need to be implemented, it first retrieves the on or off command code of the heater to be controlled, and then issues the command to control the switch of the heater to regulate the temperature.

[0049] When ground control needs to adjust the satellite's thermal management measures, it can upload a command package to modify the temperature measurement points, temperature calculation strategies, and the upper and lower thresholds for temperature control under normal emergency conditions after orbit insertion.

[0050] The thermal control management system can also be reset, returning the thermal control management measures from a certain state to the initial setting.

[0051] In this embodiment of the invention, a thermal control management system for normal and emergency orbital operation is employed. This system can read standardized thermal control information tables, is highly versatile, applicable to different satellite models, simple to operate, and easy to modify, significantly improving the work efficiency of software developers. The system implements thermal control management measures with strong real-time performance. The short cycle of each polling of heater on / off status telemetry and temperature telemetry at measurement points meets the requirements for rapid temperature response. The thermal control management system implements thermal control management measures based on the heater on / off status and the corresponding temperature at measurement points, with simple logic and high reliability, avoiding the problem of slow response caused by complex thermal control management system logic. Furthermore, during satellite in-orbit operation, the number of temperature measurement points, temperature calculation strategies, and temperature control thresholds can be flexibly modified according to actual operating environment conditions in the three modes: orbital entry, normal operation, and emergency operation. This solves the problem of fixed thermal control management system programs, which prevent modification or necessitate complete system program reconstruction.

[0052] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A thermal control management system for satellites under normal emergency conditions during orbit insertion, characterized in that, include: Thermal control subsystem and thermal control scheme modification module; Thermal control subsystem: Provides a large thermal control information table with information on heater switches and temperature measuring points under three states: satellite orbit insertion, normal operation, and emergency. The large thermal control information table includes information on heater switches and information on temperature measuring points. Thermal control scheme modification module: Based on the actual operating stage and the thermal environment, the thermal control scheme can be modified by adjusting the thermal control information table; The relevant information of the heater switch includes: the name of the heater switch, the instruction code of the heater switch, the telemetry name of the heater switch status, and the telemetry address of the heater switch status. The relevant information of the temperature measurement point includes: the temperature measurement point used, the name of the temperature measurement point telemetry, the address of the temperature measurement point telemetry, the temperature calculation strategy and entry into orbit, and the upper and lower limit thresholds for temperature control under normal and emergency conditions. Modify the injection quantity package according to the ground-based heat control measures, and adjust the heat control information table. The thermal control subsystem searches for the corresponding instruction code data field content according to the defined thermal control measures and original code correspondence table, and automatically generates a thermal control instruction package according to the thermal control instruction package format. Temperature control measures will only be implemented when both the heater's on / off state and the temperature value at the corresponding measuring point meet the conditions for their execution.

2. The thermal control management system for satellite orbit insertion under normal emergency conditions as described in claim 1, characterized in that, The acquisition addresses for the heater switch status telemetry and the acquisition addresses for the temperature measurement point telemetry are pre-stored in the form of telemetry acquisition channels.

3. A method for thermal control management under normal emergency conditions during satellite orbit insertion, characterized in that, Thermal control management is performed using the thermal control management system for normal emergency conditions during satellite orbit insertion, as described in any one of claims 1 to 2.

4. The thermal control management method for satellites under normal emergency conditions during orbit insertion according to claim 3, characterized in that, During the satellite's operation in orbit, the on / off status of the heater and the temperature values ​​at the measuring points are polled periodically to determine whether the conditions for implementing thermal control management measures are met, and then the corresponding thermal control management measures are implemented.

5. The thermal control management method for satellites under normal emergency conditions during orbit insertion according to claim 3, characterized in that, When ground control needs to adjust satellite thermal management measures, the thermal control measures should be modified according to a specific format by uploading the modification data package.

6. The thermal control management method for satellites under normal emergency conditions during orbit insertion according to claim 3, characterized in that, When it is determined that temperature control measures need to be implemented, the on or off command code of the heater to be controlled is first retrieved, and then the switch of the heater is controlled to adjust the temperature. When the thermal control management measures of the satellite need to be adjusted on the ground, the temperature measurement point, temperature calculation strategy, and upper and lower threshold values ​​of temperature control under normal emergency conditions are modified through the upper-level data command package.

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