Thermal control management system in normal emergency state of satellite injection

Abstract

The invention provides a thermal control management system for a satellite in normal and emergency injection states. The thermal control management system comprises a thermal control subsystem thermal control large table, a thermal control measure and original code corresponding relation table, an instruction data package format and a thermal control instruction data package. During in-orbit operation of a satellite, a thermal control scheme is modified according to actual operation stages and thermal environment needs, a thermal control subsystem provides a thermal control subsystem thermal control large table according to a certain format, and corresponding instruction code data field content is searched generally according to a defined thermal control measure and original code corresponding relation table. And automatically generating a thermal control instruction data package according to the thermal control data package format. Through the method, the efficiency of on-orbit regulation and control of the thermal control scheme can be effectively improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of satellite thermal control management, and in particular, relates to a thermal control management system for a satellite in a normal emergency state when entering orbit. Background Art

[0002] With the rapid development of aerospace technology, the stability and reliability of satellite in-orbit operation have become important indicators to measure its performance. Among the many factors that affect satellite performance, thermal control management is a crucial link. During the operation of satellites in orbit, on the one hand, they will encounter various complex thermal environments, such as solar radiation, earth reflection, collision of space debris, etc. These factors will directly affect the thermal balance of the satellite and affect the normal operation of the entire satellite. On the other hand, the thermal environment of the satellite in different stages is also different, such as the orbit entry stage, conventional stage, emergency stage, etc., and different thermal control management measures need to be taken. Therefore, an effective thermal control management system is very important for maintaining the stability of the satellite and extending its service life.

[0003] Traditional thermal control management systems usually use a pre-set thermal control scheme that is determined before the satellite is launched and lacks the flexibility to deal with various emergencies encountered during on-orbit operation. When a satellite encounters an abnormal thermal environment or needs to perform certain 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 an on-orbit autonomous operation management method for a spacecraft thermal control system, including the following steps: (1) a software initialization submodule provides the initial values ​​of the parameters of the thermal control system; (2) calling a data acquisition submodule to collect temperature data, spacecraft operating mode, and reference voltage; (3) calling a data processing submodule: calibrating temperature data according to the reference voltage; selecting temperature data involved in closed-loop temperature control and performing validity judgment; selecting a temperature control threshold according to the spacecraft operating mode; (4) after completing data acquisition and processing, judging whether the spacecraft has entered a safe mode, the judgment result is that it is in a normal operating mode or a safe mode, and performing subsequent operations based on the judgment result.

[0004] In order to overcome these limitations, it is urgent to develop a thermal control management system that can adapt to the satellite in the orbit insertion phase, normal phase and emergency phase, realize the on-orbit modification of the thermal control management plan, and meet the satellite's changing thermal control management needs in a complex space thermal environment. Summary of the invention

[0005] In view of the defects in the prior art, the object of the present invention is to provide a thermal control management system for a satellite in a normal emergency state when entering orbit.

[0006] According to the present invention, a thermal control management system for a satellite in orbit under normal emergency conditions includes: a thermal control subsystem and a thermal control scheme modification module;

[0007] Thermal control subsystem: provides a large table of thermal control information related to heater switches and temperature measurement points in the three states of satellite orbit entry, normal state, and emergency state, wherein the large table of thermal control information includes: relevant information on heater switches and relevant information on temperature measurement points;

[0008] Thermal control scheme modification module: According to the actual operation stage and 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 state, and the telemetry address of the heater switch state;

[0010] The relevant information of the temperature measurement point includes: the temperature measurement point adopted, 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 of temperature control under orbit entry, normal and emergency conditions.

[0011] Preferably, the injection number package is modified according to the thermal control measures injected on the ground, and the thermal control information table is adjusted.

[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 injection number packet according to the thermal control injection number instruction packet format.

[0013] Preferably, the collection address of the heater switch state telemetry and the collection address of the temperature measurement point telemetry are pre-stored in the form of telemetry collection channels.

[0014] Preferably, the temperature control measure is executed only when the switch state of the heater and the temperature value of the corresponding temperature measuring point both meet the conditions for executing the temperature control measure.

[0015] According to a method for thermal control management under normal emergency conditions of satellite in-orbit, provided by the present invention, thermal control management is performed using the thermal control management system under normal emergency conditions of satellite in-orbit.

[0016] Preferably, during the on-orbit operation of the satellite, the switch status of the heater and the temperature value of the temperature measuring point are polled at regular intervals to determine whether the conditions for executing thermal control management measures are met and implement corresponding thermal control management measures.

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

[0018] Preferably, when it is determined that temperature control measures need to be executed, 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 ground needs to adjust the thermal control management measures of the satellite, the temperature measurement points, temperature calculation strategies, and upper and lower thresholds of temperature control in the normal emergency state of orbit are modified through the injection instruction package.

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

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

[0021] 2. The thermal control management system of the present invention has strong real-time performance in implementing thermal control management measures. The cycle of each polling of the heater switch status telemetry and the temperature telemetry of the temperature measuring point is short, which can meet the requirements of rapid temperature response. The thermal control management system implements thermal control management measures based on the heater switch status and the temperature of the corresponding temperature measuring point. The logic is simple and the reliability is strong, which avoids the problem of slow response caused by complex logic of the thermal control management system.

[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 entry, normal operation and emergency according to the actual operating environment conditions during the satellite's on-orbit operation, thereby solving the problem that the thermal control management system program is fixed and cannot be modified or the entire system program can only be reconstructed. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0024] Figure 1 It is a flow chart of the implementation method of the orbit entry normal emergency thermal control management system of the present invention;

[0025] Figure 2 It is a temperature control flow chart of the thermal control management system of the present invention. DETAILED DESCRIPTION

[0026] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0027] Figure 1 It is a flow chart of the implementation method of the orbit entry normal emergency thermal control management system of the present invention.

[0028] According to the present invention, a normal emergency thermal control management system for entering orbit includes: a thermal control table of a thermal control subsystem, a table of correspondence between thermal control measures and original codes, a format of an instruction note package, and a thermal control instruction note package. During the on-orbit operation of the satellite, the thermal control scheme needs to be modified according to the actual operation stage and the thermal environment in which it is located. The thermal control subsystem provides a thermal control table of the thermal control subsystem in a certain format, and the overall instruction code data field content is searched according to the defined table of correspondence between thermal control measures and original codes, and the thermal control instruction note package is automatically generated according to the format of the thermal control instruction package. This method can effectively improve the efficiency of on-orbit regulation of the thermal control scheme.

[0029] like Figure 1 As shown, the implementation method of the orbit entry 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 certain format, including information on heater switches and temperature measurement points in the satellite's orbital, normal and emergency states.

[0031] The relevant information of 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 relevant information of the temperature measurement point includes the temperature measurement point adopted, 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 of temperature control under orbital, normal and emergency conditions. The format is shown in the following table.

[0032]

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

[0034] The satellite thermal control management system reads the thermal control information table, and pre-stores the collection address of the heater switch status telemetry in the thermal control information table, the instruction code sent when executing temperature control measures, the number of temperature measurement points adopted, the collection address of the temperature measurement point telemetry, the temperature calculation strategy of the temperature measurement point, and the upper and lower temperature control thresholds during orbit entry, normal and emergency conditions in the Flash or MRAM type of memory of the thermal control management system.

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

[0036] The collection channel includes the APID of the telemetry package, the byte number and bit number of the telemetry parameter.

[0037] 0xAAA and 0xBBB in the table represent the application process identifier APID of the telemetry package, a and b represent the byte position number of the telemetry in the telemetry package, 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 polls the switch status of the heater and the temperature value of the temperature measurement point at regular intervals to determine whether the conditions for executing thermal control management measures are met and implement corresponding thermal control management measures;

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

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

[0041] Step S21: The thermal control management system takes out the heater switch status telemetry and temperature measurement point telemetry from the telemetry packages returned to the satellite onboard computer by each subsystem on the satellite according to the pre-stored acquisition address information at regular intervals.

[0042] Step S22: The thermal control management system sets conditions for determining the execution of temperature control measures based on the switch state of the heater and the temperature value of the corresponding temperature measurement point.

[0043] Temperature control measures are only executed when the heater switch state and the temperature value of the corresponding temperature measuring point meet the conditions for executing the temperature control measures.

[0044] For example, when a heater is in the off state and the temperature telemetry value of the temperature measuring point in the temperature control area is lower than the lower limit of the temperature threshold, the execution condition of the temperature control measure of turning on the heater is met.

[0045] Step S23: During the satellite's on-orbit operation, the thermal control management system polls the switch status of the heater and the temperature value of the temperature measuring point at regular intervals.

[0046] If the switch state of the heater and the temperature of the temperature measuring point simultaneously meet the conditions for executing the temperature control measures, the temperature control measures will be executed, otherwise they will not be executed.

[0047] If the temperature control measures fail to be executed or the temperature remains within the temperature control measures execution range after execution, 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 executed, it first retrieves the on or off command code of the heater to be controlled, and then the thermal control management system issues the command to control the switch of the heater to adjust the temperature.

[0049] When the ground needs to adjust the satellite's thermal control management measures, it can upload a number of instruction packages to modify the temperature measurement points, temperature calculation strategies, and the upper and lower thresholds of temperature control under normal emergency conditions when in orbit.

[0050] The thermal management system can also be reset to return the thermal management measures in a certain state to the initial settings.

[0051] In the embodiment of the present invention, a thermal control management system in the normal emergency state of orbit entry is adopted. The system can read a large table of thermal control information in a standardized format, has strong versatility, is applicable to satellites of different models, is simple to operate, and is easy to change, which significantly improves the work efficiency of software developers. The system has strong real-time performance in implementing thermal control management measures. The cycle of each polling of heater switch status telemetry and temperature measurement point temperature telemetry is short, which can meet the requirements of rapid temperature response. The thermal control management system implements thermal control management measures based on the heater switch status and the temperature of the corresponding temperature measurement point. The logic is simple and the reliability is strong, avoiding the problem of slow response caused by complex logic of the thermal control management system. It can also flexibly modify the number of temperature measurement points, temperature calculation strategy and temperature control threshold in the three modes of orbit entry, normal and emergency according to the actual operating environment conditions during the satellite's on-orbit operation, solving the problem that the thermal control management system program is fixed and cannot be modified or the entire system program can only be reconstructed.

[0052] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A thermal control management system for a satellite in orbit under normal emergency conditions, characterized in that: include: Thermal control subsystem, thermal control scheme modification module; Thermal control subsystem: provides a large table of thermal control information related to heater switches and temperature measurement points in the three states of satellite orbit entry, normal state, and emergency state, wherein the large table of thermal control information includes: relevant information on heater switches and relevant information on temperature measurement points; Thermal control scheme modification module: According to the actual operation stage and thermal environment, the thermal control scheme can be modified by adjusting the thermal control information table.

2. The thermal control management system for satellite orbit entry under normal emergency conditions according to claim 1, characterized in that: 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 state, and the telemetry address of the heater switch state; The relevant information of the temperature measurement point includes: the temperature measurement point adopted, 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 of temperature control under orbit entry, normal and emergency conditions.

3. The thermal control management system for satellite orbit entry under normal emergency conditions according to claim 1, characterized in that: Modify the injection data package according to the thermal control measures injected on the ground and adjust the thermal control information table.

4. The thermal control management system for satellite orbit entry under normal emergency conditions according to claim 1, characterized in that: 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 injection number packet according to the thermal control injection number instruction packet format.

5. The thermal control management system for satellite in orbit under normal emergency state according to claim 2, characterized in that: The collection address of the heater switch status telemetry and the collection address of the temperature measurement point telemetry are pre-stored in the form of telemetry collection channels.

6. The thermal control management system for satellite in orbit under normal emergency state according to claim 1, characterized in that: Temperature control measures are only executed when the heater switch state and the temperature value of the corresponding temperature measuring point meet the conditions for executing the temperature control measures.

7. A method for thermal control management of a satellite in a normal emergency state during orbit entry, characterized in that: Thermal control management is performed by adopting the thermal control management system in the normal emergency state of satellite in orbit as described in any one of claims 1 to 6.

8. The method for thermal control management of satellites in normal emergency state when entering orbit according to claim 7, characterized in that: During the satellite's in-orbit operation, the switch status of the heater and the temperature value of the temperature measuring point are polled at regular intervals to determine whether the conditions for executing thermal control management measures are met and implement corresponding thermal control management measures.

9. The method for thermal control management of satellites in normal emergency state when entering orbit according to claim 7, characterized in that: When the ground needs to adjust the satellite thermal control management measures, the thermal control measures modification package is modified according to a certain format.

10. The method for thermal control management of satellites in normal emergency state when entering orbit according to claim 7, characterized in that: When it is determined that temperature control measures need to be implemented, the on or off command code of the heater that needs to be controlled is first retrieved, and then the switch of the heater is controlled to adjust the temperature; when the ground needs to adjust the satellite's thermal control management measures, the temperature measurement points, temperature calculation strategies, and upper and lower thresholds of temperature control in the normal emergency state of orbit are modified through the injection instruction package.

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