A spacecraft system and control method thereof

Abstract

The present invention relates to the field of spacecraft control technology, and in particular to a spacecraft system and a control method thereof, the system comprising: a microwave electric propulsion module, a charging module, a data acquisition module and a power supply determination module; judging whether the operation of a single microwave electric propulsion meets the preset standard according to the actual operating parameters of the main power supply module collected, and determining the reason for not meeting the standard, judging whether it is necessary to use a backup power supply module according to the reason for not meeting the standard, and detecting whether the operation of the backup power supply module meets the standard when determining to switch the backup power supply module for power supply, and determining the corresponding optimization method when the backup power supply module does not meet the standard. The present invention can timely discover problems and take corresponding measures, including switching to the backup power supply module or making optimization suggestions, through real-time monitoring and fault diagnosis of the operating parameters of the power supply module, thereby improving the self-repair ability of the system, reducing the need for external intervention, and improving reliability and controllability.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft control technology, and in particular to a spacecraft system and a control method thereof. Background Art

[0002] At present, microwave plasma thrusters (microwave electric thrusters) are used on spacecraft to propel spacecraft, but the control and optimization of the main power supply and backup power supply of the thrusters cannot be better controlled and optimized, making it impossible to understand the operating status of the power supply in a timely manner; it is impossible to discover problems in time and take measures to solve them.

[0003] Chinese patent application publication number CN111913467A discloses a system-level fault diagnosis method for a spacecraft control system: the method is used to diagnose attitude reference loss faults, control performance degradation faults, thruster excessive jet faults, and energy safety failure faults of a spacecraft control system.

[0004] It can be seen from this that the current spacecraft control system cannot improve the autonomy and controllability of flight; it cannot provide guarantee for the long-term reliable operation of spacecraft. Summary of the invention

[0005] To this end, the purpose of the present invention is to provide a spacecraft system and a control method thereof, so as to overcome the problem that the current spacecraft control system cannot improve the autonomy and controllability of flight and cannot provide guarantee for the long-term reliable operation of the spacecraft.

[0006] To achieve the above object, the present invention provides a spacecraft system, comprising:

[0007] A microwave electric propulsion module is used to provide power for the flight of a spacecraft; it includes: a main power supply module and a backup power supply module; the main power supply module is used as the main power supply for the operation of the spacecraft and is used to continuously perform microwave electric propulsion on the spacecraft; the backup power supply module includes a plurality of storage battery packs as the backup power supply for the operation of the spacecraft;

[0008] A charging module, which charges the main power module and the backup power module by converting solar energy into chemical energy;

[0009] A data acquisition module, which is used to collect the actual operating parameters of each power module in real time;

[0010] A power supply determination module determines whether the operation of a single microwave electric pusher meets the preset standards based on the actual operating parameters collected, and determines the reasons for not meeting the standards. It determines whether the backup power supply module needs to be used based on the reasons for not meeting the standards. When it is determined to switch the backup power supply module for power supply, it detects whether the operation of the backup power supply module meets the standards, and determines the corresponding optimization method when the backup power supply module does not meet the standards.

[0011] Further, the data acquisition module includes: a first acquisition unit, a second acquisition unit, a third acquisition unit and a fourth acquisition unit;

[0012] The first acquisition unit is used to acquire actual operating parameters of the main power supply of the main power supply module;

[0013] The second acquisition unit is used to acquire the actual operating parameters of the backup power supply of the backup power supply module;

[0014] The third acquisition unit is used to collect the actual fluctuation frequency of the main power module during the power supply process;

[0015] The fourth collection unit is used to collect the single power supply power consumption of the backup power module;

[0016] The actual operating parameters of the main power supply include: the actual main operating current, the actual main operating voltage, the actual fluctuation frequency and the single power supply power consumption.

[0017] Furthermore, for each main actual operating current and each main actual operating voltage in any single microwave electric propulsion process;

[0018] The power source determination module integrates the types of each main actual operating current and each main actual operating voltage, including: a number of main safe operating currents, a number of abnormal operating currents, a number of main safe operating voltages and a number of abnormal operating voltages; and calculates a single microwave electric propulsion evaluation value according to the integration situation;

[0019] Wherein, for any main actual operating current; if the main actual operating current falls within the preset current safety fluctuation range, the power supply determination module determines that the main actual operating current type is a safe current;

[0020] If the main actual operating current does not fall within the current safety fluctuation range, the power source determination module determines that the main actual operating current type is an abnormal current;

[0021] For any main actual operating voltage; if the main actual operating voltage falls within the preset voltage safety fluctuation range, the power supply determination module determines that the main actual operating voltage type is a safe voltage;

[0022] If the main actual operating voltage does not fall within the voltage safety fluctuation range, the power source determination module determines that the main actual operating voltage type is an abnormal voltage.

[0023] Further, the power determination module determines whether the operation of the main power module meets the preset standard according to the first difference absolute value and the preset first operation evaluation value;

[0024] If the absolute value of the first difference is less than or equal to the first operation evaluation value, it is determined that the operation of the main power module meets the preset standard;

[0025] If the absolute value of the first difference is greater than the first operation evaluation value and the single microwave electric pushing evaluation value is greater than the preset single microwave electric pushing standard value, it is determined that the operation of the main power supply module meets the preset standard;

[0026] If the absolute value of the first difference is greater than the first operation evaluation value and the single microwave electric pushing evaluation value is less than the single microwave electric pushing standard value, it is determined that the operation of the main power module does not meet the preset standard;

[0027] The first absolute value of the difference is the absolute value of the difference between the single microwave electric-pushing evaluation value and the single microwave electric-pushing standard value.

[0028] Further, when the power source determination module determines that the operation of the main power source module meets the preset standard, the main power source module continues to be used as the power source for the next propulsion;

[0029] When it is determined that the operation of the main power module does not meet the preset standard based on the power determination module, historical data is retrieved, and the operation status of the main power module is determined according to the historical data;

[0030] The historical data is the historical fluctuation frequency of the main power module during the historical operation cycle.

[0031] Further, the power supply determination module determines the power supply fault level of the main power supply module according to the second difference absolute value combined with a preset second operation evaluation value;

[0032] If the absolute value of the second difference is less than or equal to the second operation evaluation value, the power source determination module determines that the main power source module has no fault and the data acquisition module collects abnormal data;

[0033] If the absolute value of the second difference is greater than the second operation evaluation value and the historical fluctuation frequency is less than the preset standard fluctuation frequency, the power source determination module determines that the main power source module is a secondary power source failure, and switches the backup power source module to advance;

[0034] If the absolute value of the second difference is greater than the second operation evaluation value and the historical fluctuation frequency is greater than the standard fluctuation frequency, the power source determination module determines that the main power source module is a primary power source failure, and switches to the backup power source module for advancement;

[0035] The second absolute value of the difference is the absolute value of the difference between the historical fluctuation frequency and the standard fluctuation frequency.

[0036] Further, the power source determination module determines the abnormal cause of the main power source module according to the actual fluctuation frequency combined with the power source fault level of the main power source module;

[0037] If the power supply fault level is the secondary power supply fault and the actual fluctuation frequency is less than or equal to the standard fluctuation frequency, the power supply determination module determines that the abnormal cause is: the remaining power of the power supply is low;

[0038] If the power supply fault level is the secondary power supply fault and the actual fluctuation frequency is greater than the standard fluctuation frequency, the power supply determination module determines that the abnormal cause is: the main power supply module is damaged;

[0039] If the power supply fault level is the first-level power supply fault and the actual fluctuation frequency is greater than or equal to the standard fluctuation frequency, the power supply determination module determines that the abnormal cause is: thruster overload;

[0040] If the power supply fault level is the first-level power supply fault and the actual fluctuation frequency is less than the standard fluctuation frequency, the power supply determination module determines that the abnormal cause is: the main power supply module is damaged.

[0041] Further, based on the abnormal reason being: when the remaining power of the power supply is low, the power supply determination module sends a charging signal to charge the main power supply module;

[0042] Based on the abnormal reason being: when the propeller is overloaded, the power supply determination module sends a first adjustment signal to expand the capacity of the main power supply module;

[0043] After switching the backup power supply, the power supply determination module determines whether the operation of the backup power supply module meets the preset standard according to the single power supply power consumption;

[0044] If the single power supply power consumption is less than or equal to the preset standard power supply power consumption, it is determined that the operation of the backup power supply module meets the preset standard;

[0045] If the single power supply power consumption is greater than the standard power supply power consumption, it is determined that the operation of the backup power module does not meet the preset standard, and a second adjustment signal is sent to expand the capacity of the backup power module.

[0046] Further, the power supply determination module obtains each single power supply power consumption during the propulsion process of the spacecraft; calculates the average power consumption according to each single power supply power consumption; and determines the adjustment strategy for the backup power supply module according to the average power consumption combined with the standard power supply power consumption;

[0047] If the average power consumption is greater than or equal to the standard power consumption, the power determination module determines that the backup power module has been partially damaged, and repairs the backup power module based on the loss ratio;

[0048] If the average power consumption is less than the standard power consumption, the power determination module determines that the backup power module has no loss.

[0049] Another aspect of the present invention further provides a method for controlling a spacecraft system, comprising:

[0050] Step S1, collecting the main operating parameters of the main power module, and judging whether the single microwave electric pushing operation of the main power module meets the preset standard according to the main operating parameters;

[0051] Step S2, when the operation of the single microwave electric propulsion does not meet the preset standard, determining the reason why the main power module does not meet the standard and corresponding adjustment measures;

[0052] Step S3, when the main power module does not meet the preset standard and the backup power module needs to be replaced, the backup power module is tested to determine whether it meets the preset standard, and based on the failure to meet the preset standard, an optimization method for the backup power module is determined.

[0053] Compared with the prior art, the beneficial effects of the present invention are that, by adopting the main and standby power supply module design, a stable power source is ensured for the spacecraft during operation; the main power supply module provides continuous microwave electric propulsion, and the standby power supply module provides reliable standby power when the main power supply fails, thereby enhancing the reliability and stability of the system; the main power supply module uses microwave electric propulsion to continuously provide power to the spacecraft, while the standby power supply module ensures that the operation of the spacecraft can be maintained when the main power supply is unavailable, so that the spacecraft can continue to work for a long time, thereby enhancing the continuity of mission execution; the charging module converts solar energy into chemical energy to charge the main and standby power supply modules; the use of renewable energy not only reduces the energy consumption of the system, but also reduces the dependence on traditional energy, and has the characteristics of environmental protection and energy saving; by real-time sampling The actual operating parameters of each power module are collected, so that the operating status of the power supply can be understood in time; it is helpful to find problems in time and take measures to solve them, improving the fault detection and diagnosis capabilities; based on the collected actual operating parameters, it is judged whether the operation of a single microwave electric propulsion meets the preset standards, the reasons for non-compliance are determined, and the backup power module is switched according to the situation; when switching to the backup power module for power supply, the operating status of the backup power module is also detected, and optimization methods are proposed when it does not meet the standards, thereby ensuring the stability and efficiency of the system; through real-time monitoring and fault diagnosis of the power module operating parameters, problems can be discovered in time and corresponding measures can be taken, including switching to the backup power module or proposing optimization suggestions, thereby improving the self-repair capability of the system, reducing the need for external intervention, and improving reliability and controllability.

[0054] In particular, through different acquisition units, all key operating parameters of the main power module and the backup power module are fully collected, including current, voltage, fluctuation frequency, and single power consumption of the backup power supply, etc.; all key indicators of system operation are covered; through intelligent analysis of the current and voltage fluctuations of the main power module, it can accurately determine which operating parameters are within the safe range and which are abnormal; this sophisticated fault diagnosis capability helps the system to detect potential problems in a timely manner and take appropriate measures; based on the collected safe and abnormal operating parameters, the comprehensive evaluation value K1 of a single microwave electric propulsion is calculated and compared with the preset standard value K0; based on Based on the comprehensive evaluation of multiple indicators, it is possible to more objectively judge whether the overall operation of the main power module meets the standards; when the operation of the main power module does not meet the preset standards, it will automatically switch to the backup power module for power supply; at the same time, the operation of the backup power module will be monitored to ensure that the backup power supply can also work normally; the reliable fault-tolerant mechanism greatly improves stability and reliability; it can not only diagnose faults, but also make corresponding optimization suggestions based on the fault conditions, and the ability of self-repair and optimization can help the spacecraft to operate continuously and stably, reduce the need for manual intervention, and improve the autonomy and controllability of the system; it provides a strong guarantee for the long-term reliable operation of the spacecraft.

[0055] In particular, when the operation of the main power module meets the preset standards, the system will continue to use the main power module to supply power to ensure the continuous and stable propulsion of the spacecraft; if the operation of the main power module does not meet the preset standards, the system will intelligently retrieve historical data and make fault judgments based on historical fluctuation frequencies, avoiding the limitations of relying solely on current data to make decisions; by analyzing historical fluctuation frequencies, the system can more comprehensively evaluate the status of the main power module, and based on the analysis of historical data, it helps to locate faults more accurately and take corresponding countermeasures; based on the comparison results of historical fluctuation frequencies with preset standard fluctuation frequencies, the faults are divided into level one and level two, and corresponding processing is made, with flexible fault levels. Division helps the system to adopt different response strategies according to specific circumstances, improving the pertinence and effectiveness of responding to faults; reliability and safety indicators are taken into account in the fault judgment mechanism, which makes the system design closer to actual operation needs; the setting of reliability and safety indicators is closely related to the long-term stable operation of the spacecraft, ensuring that the system can work reliably in various environments; the fault judgment mechanism also takes into account the impact of environmental factors on reliability and safety indicators, such as temperature, humidity, air pressure, etc. Comprehensive considerations enable the system to more comprehensively evaluate the operating status of the main power module, improving the accuracy and reliability of the judgment; it can more reliably respond to various complex situations and ensure the safe and stable operation of the spacecraft.

[0056] In particular, the specific cause of the abnormality of the main power module can be accurately determined through the actual fluctuation frequency and the power failure level of the main power module. Accurate judgment helps to quickly find the fault point and reduce the time and cost of troubleshooting. Targeted abnormality handling strategies are adopted for power failures of different levels. For example, in the case of a secondary power failure, the fluctuation frequency is used to determine whether the remaining power of the power supply is low or the main power module is damaged, so that corresponding repair measures can be taken in a targeted manner. The fault judgment takes into account the relationship between the power failure level and the actual fluctuation frequency, so as to comprehensively evaluate the status of the main power module. Comprehensive consideration makes the system's handling of abnormal situations more comprehensive and accurate. Each abnormal situation has a clear judgment logic, which makes the analysis of the cause of the abnormality clear and easy to understand, which helps engineers quickly understand the fault situation and take corresponding countermeasures. By judging the cause of the abnormality by the fluctuation frequency and the fault level, potential fault risks can be discovered in advance, and preventive measures can be taken to avoid the impact of the fault on the spacecraft. The early warning and prevention mechanism helps to improve the stability and reliability of the spacecraft. It can more effectively deal with various abnormal situations of the main power module and ensure the safe and stable operation of the spacecraft.

[0057] In particular, accurate processing strategies are adopted for different abnormal reasons, such as sending a charging signal, a first adjustment signal or a second adjustment signal, so as to process and adjust the main power module or the backup power module accordingly; after switching to the backup power module, the operation status of the backup power module is dynamically judged according to the single power consumption, and expansion or maintenance measures are taken to ensure that the backup power module can operate normally when needed; the average power consumption is calculated based on the single power consumption, and combined with the standard power consumption, it is intelligently judged whether the backup power module needs to be adjusted. The intelligent adjustment strategy helps to respond to changes in the backup power module in a timely manner. , ensuring stable power supply for the spacecraft; by obtaining the power consumption during the propulsion of the spacecraft and calculating the average power consumption, real-time monitoring of the operating status of the backup power module is achieved, and maintenance is carried out according to the loss situation. The real-time monitoring and maintenance mechanism helps to promptly discover and solve problems with the backup power module, ensuring the reliability of the spacecraft; intelligent adjustment strategies and real-time monitoring and maintenance can effectively save costs and resources, avoid unnecessary repairs and replacements, and at the same time ensure the effective use and long-term stable operation of the backup power module; can more effectively respond to various abnormal situations of the main power module and the backup power module, ensuring the safe and stable operation of the spacecraft.

[0058] In particular, by collecting the main operating parameters of the main power module and judging the operating status of a single microwave electric propulsion, the status of the main power module can be monitored in real time, and whether it meets the preset standards can be discovered in time to ensure the normal operation of the main power module; when the operation of a single microwave electric propulsion does not meet the preset standards, the reasons for the non-compliance of the main power module can be quickly determined, and corresponding adjustment measures can be taken. The rapid response can effectively avoid the impact of the non-compliance on the spacecraft, thereby ensuring the stability of the spacecraft; when the main power module does not meet the preset standards and the backup power module needs to be replaced, the backup power module is tested to determine whether it meets the preset standards; if it does not meet the preset standards, the optimization method for the backup power module is determined to ensure the performance and stability of the backup power module; through real-time monitoring, rapid response and timely switching and optimization of the backup power module, the reliability and stability of the spacecraft system can be improved, and the control method for improving reliability and stability helps to ensure the long-term stable operation of the spacecraft and cope with various abnormal situations; it can effectively ensure the safe operation of the spacecraft system. BRIEF DESCRIPTION OF THE DRAWINGS

[0059] Figure 1 A schematic diagram of the structure of a spacecraft system according to an embodiment of the present invention;

[0060] Figure 2 It is a schematic diagram of the structure of a microwave electric propulsion module in a spacecraft system according to an embodiment of the present invention;

[0061] Figure 3This is a schematic diagram of the structure of a data acquisition module in a spacecraft system according to an embodiment of the present invention;

[0062] Figure 4 A schematic diagram of a flow chart of a control method of a spacecraft system according to an embodiment of the present invention;

[0063] The figure includes: a microwave electric pushing module 1, a charging module 2, a data acquisition module 3 and a power source determination module 4. DETAILED DESCRIPTION

[0064] In order to make the objects and advantages of the present invention more clearly understood, the present invention is further described below in conjunction with embodiments; it should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0065] The preferred embodiments of the present invention are described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only used to explain the technical principles of the present invention and are not intended to limit the protection scope of the present invention.

[0066] It should be noted that, in the description of the present invention, terms such as "up", "down", "left", "right", "inside" and "outside" indicating directions or positional relationships are based on the directions or positional relationships shown in the drawings. This is merely for the convenience of description and does not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it cannot be understood as a limitation on the present invention.

[0067] See also Figure 1-Figure 4 As shown, Figure 1 A schematic diagram of the structure of a spacecraft system according to an embodiment of the present invention; Figure 2 It is a schematic diagram of the structure of a microwave electric propulsion module in a spacecraft system according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the structure of a data acquisition module in a spacecraft system according to an embodiment of the present invention; Figure 4 The figure is a flow chart of a control method of a spacecraft system according to an embodiment of the present invention.

[0068] An embodiment of the present invention provides a spacecraft system, including:

[0069] The microwave electric propulsion module 1 is used to provide power for the flight of the spacecraft; it includes: a main power supply module and a backup power supply module;

[0070] The main power supply module serves as the main power supply for the operation of the spacecraft and is used to continuously perform microwave electric propulsion on the spacecraft;

[0071] The backup power module includes a plurality of battery packs, which serve as a backup power source for the operation of the spacecraft;

[0072] A charging module 2, which charges the main power module and the backup power module by converting solar energy into chemical energy;

[0073] Data acquisition module 3, which is used to collect the actual operating parameters of each power module in real time;

[0074] The power supply determination module 4 determines whether the operation of a single microwave electric pusher meets the preset standards based on the actual operating parameters collected, and determines the reasons for not meeting the standards. It determines whether the backup power supply module needs to be used based on the reasons for not meeting the standards. When it is determined to switch the backup power supply module for power supply, it detects whether the operation of the backup power supply module meets the standards, and determines the corresponding optimization method when the backup power supply module does not meet the standards.

[0075] The embodiment of the present invention adopts a main and standby power supply module design to ensure that the spacecraft has a stable power source during operation; the main power supply module provides continuous microwave electric propulsion, and the standby power supply module provides reliable standby power when the main power supply fails, thereby enhancing the reliability and stability of the system; the main power supply module uses microwave electric propulsion to continuously provide power to the spacecraft, while the standby power supply module ensures that the operation of the spacecraft can be maintained when the main power supply is unavailable, so that the spacecraft can continue to work for a long time, thereby enhancing the continuity of mission execution; the charging module converts solar energy into chemical energy to charge the main and standby power supply modules; the use of renewable energy not only reduces the energy consumption of the system, but also reduces the dependence on traditional energy, and has the characteristics of environmental protection and energy saving; by collecting the real-time The actual operating parameters enable timely understanding of the operating status of the power supply; it helps to promptly discover problems and take measures to resolve them, improving fault detection and diagnosis capabilities; based on the collected actual operating parameters, it is determined whether the operation of a single microwave electric propulsion meets the preset standards, the reasons for non-compliance are determined, and the backup power module is switched according to the situation; when switching to the backup power module for power supply, the operating status of the backup power module is also detected, and optimization methods are proposed when it does not meet the standards, thereby ensuring the stability and efficiency of the system; through real-time monitoring and fault diagnosis of the power module operating parameters, problems can be discovered in a timely manner and corresponding measures can be taken, including switching to the backup power module or proposing optimization suggestions, thereby improving the system's self-repair capability, reducing the need for external intervention, and improving reliability and controllability.

[0076] Specifically, the data acquisition module 3 in this embodiment includes: a first acquisition unit, a second acquisition unit, a third acquisition unit and a fourth acquisition unit; the first acquisition unit is used to acquire the actual operating parameters of the main power supply of the main power supply module; the second acquisition unit is used to acquire the actual operating parameters of the backup power supply of the backup power supply module; the third acquisition unit is used to acquire the actual fluctuation frequency of the main power supply module during the power supply process; the fourth acquisition unit is used to acquire the single power supply power consumption of the backup power supply module;

[0077] The actual operating parameters of the main power supply include: the actual operating current of the main power supply, the actual operating voltage of the main power supply, the actual fluctuation frequency and the power consumption of the single power supply;

[0078] The first acquisition unit can acquire each main actual operating current in a single microwave electric propulsion process, including: a first main actual operating current A11, a second main actual operating current A12, ..., an nth main actual operating current A1n;

[0079] The first acquisition unit can acquire each main actual operating voltage during a single microwave electric propulsion process, including: a first main actual operating voltage A21, a second main actual operating voltage A22, ..., an nth main actual operating voltage A2n;

[0080] For any main actual operating current A1i, where i=1, 2, ..., n;

[0081] If the ith main actual operating current A1i falls within the current safety fluctuation range, the power source determination module 4 determines that the ith main actual operating current A1i is a safe current;

[0082] If the i-th main actual operating current A1i does not fall within the current safety fluctuation range, the power source determination module 4 determines that the i-th main actual operating current A1i is an abnormal current;

[0083] For any main actual operating voltage A2i;

[0084] If the ith main actual operating voltage A2i falls within the voltage safety fluctuation range, the power source determination module 4 determines that the ith main actual operating voltage A2i is a safe voltage;

[0085] If the i-th main actual operating voltage A2i does not fall within the voltage safety fluctuation range, the power source determination module 4 determines that the i-th main actual operating voltage A2i is an abnormal voltage;

[0086] In this embodiment, the current safety fluctuation range should be within ±5% of the standard operating current, and the voltage safety fluctuation range should be within ±2% of the standard operating voltage; the setting of the standard operating current and the standard operating voltage depends on the design requirements and specifications of the spacecraft, and the current safety fluctuation range and the voltage safety fluctuation range are set within a reasonable range to ensure the normal operation of the equipment and minimize safety risks; the current safety fluctuation range and the voltage safety fluctuation range are set differently according to the different environments of the spacecraft. For example, due to the different temperatures at different locations in space, the current safety fluctuation range and the voltage safety fluctuation range should also change accordingly;

[0087] The power source determination module 4 integrates the types of each main actual operating current and each main actual operating voltage, including:

[0088] 1) Renumbering each main actual operating current of the safety current type, recording as the first main safety operating current B11, the second main safety operating current B12, ... the mth main safety operating current B1m;

[0089] 2) renumbering each main actual operating current of the abnormal current type, recording as the first abnormal operating current B21, the second abnormal operating current B22, ... the rth abnormal operating current B2r;

[0090] 3) renumbering each main actual operating voltage of the safety voltage type, recording as the first main safety operating voltage C11, the second main safety operating voltage C12, ... the pth main safety operating voltage C1p;

[0091] 4) renumbering each main actual operating voltage of the abnormal voltage type, recording as the first abnormal operating voltage C21, the second abnormal operating voltage C22, ..., the qth abnormal operating voltage C2q;

[0092] Calculate the single microwave electric push evaluation value K1 according to the integration situation, and set

[0093]

[0094] Among them, B1X1 is the X1th main safety operation current, EX1 is the first calculation compensation parameter of the X1th main safety operation current B1X1 for the single microwave electric pushing evaluation value K1; C1Y1 is the Y1th main safety operation voltage, EY1 is the second calculation compensation parameter of the Y1th main safety operation voltage C1Y1 for the single microwave electric pushing evaluation value K1, B2X2 is the X2th abnormal operation current; EX2 is the third calculation compensation parameter of the X2th abnormal operation current B2X2 for the single microwave electric pushing evaluation value K1; C2Y2 is the Y2th abnormal operation voltage; EY2 is the fourth calculation compensation parameter of the Y2th abnormal operation voltage C2Y2 for the single microwave electric pushing evaluation value K1;

[0095] The power source determination module 4 calculates a first difference absolute value G1 according to the single microwave electric pushing evaluation value K1 and a preset single microwave electric pushing standard value K0, where G1=|K1-K0|;

[0096] If G1≤G10, the power determination module 4 determines that the operation of the main power module meets the preset standard;

[0097] If G1>G10 and K1>K0, the power determination module 4 determines that the operation of the main power module meets the preset standard;

[0098] If G1>G10 and K1<K0, the power determination module 4 determines that the operation of the main power module does not meet the preset standard;

[0099] Among them, G10 is the preset first operation evaluation value;

[0100] In this embodiment, the first calculation compensation parameter EX1 is set to 0.4; the second calculation compensation parameter EY1 is set to 0.4; the third calculation compensation parameter EX2 is set to 0.6; the fourth calculation compensation parameter EY2 is set to 0.6; each calculation compensation parameter is set differently according to the different environments in which the spacecraft is located; the setting of the single microwave electric propulsion standard value K0 and the first operation evaluation value G10 is related to the reliability and safety index of the main power supply module, and the reliability and safety index is that within one operation cycle, the stable operation time of the spacecraft must reach more than 80% of the entire operation cycle. The specific setting of the reliability and safety index is also affected by the operating environment. For example, environmental factors such as temperature, humidity, and air pressure may affect the reliability and safety index of the power supply equipment.

[0101] The embodiment of the present invention comprehensively collects various key operating parameters of the main power module and the backup power module through different collection units, including current, voltage, fluctuation frequency, and single power consumption of the backup power supply, etc.; covers various key indicators of system operation; through intelligent analysis of the current and voltage fluctuations of the main power module, it can accurately determine which operating parameters are within the safe range and which are abnormal; this sophisticated fault diagnosis capability helps the system to discover potential problems in a timely manner and take appropriate measures; based on the collected safe and abnormal operating parameters, the comprehensive evaluation value K1 of a single microwave electric propulsion is calculated and compared with the preset standard value K0; Based on the comprehensive evaluation of multiple indicators, it is possible to more objectively judge whether the overall operation of the main power module meets the standards; when the operation of the main power module does not meet the preset standards, it will automatically switch to the backup power module for power supply; at the same time, the operation of the backup power module will be monitored to ensure that the backup power supply can also work normally; the reliable fault-tolerant mechanism greatly improves stability and reliability; it can not only diagnose faults, but also make corresponding optimization suggestions based on the fault conditions, and the ability of self-repair and optimization can help the spacecraft to operate continuously and stably, reduce the need for human intervention, and improve the autonomy and controllability of the system; it provides a strong guarantee for the long-term reliable operation of the spacecraft.

[0102] Specifically, in this embodiment, when the power source determination module 4 determines that the operation of the main power source module meets the preset standard, the main power source module continues to be used as the power source for the next propulsion;

[0103] When the power source determination module 4 determines that the operation of the main power source module does not meet the preset standard, historical data is retrieved, and the operation status of the main power source module is determined according to the historical data;

[0104] The historical data is the historical fluctuation frequency of the main power module during the historical operation cycle;

[0105] The power source determination module 4 calculates a second difference absolute value G2 according to the historical fluctuation frequency W1 and a preset standard fluctuation frequency W0; G2 = |W1-W0|;

[0106] If G2≤G20, the power source determination module 4 determines that the main power source module has no fault, and the data acquisition module 3 collects abnormal data;

[0107] If G2>G20 and W1<W0; the power source determination module 4 determines that the main power source module is a secondary power source failure, and switches to the backup power source module for advancement;

[0108] If G2>G20 and W1>W0; the power source determination module 4 determines that the main power source module is a primary power source failure, and switches to the backup power source module for advancement;

[0109] Among them, G20 is the preset second operation evaluation value;

[0110] In this embodiment, the setting of the standard fluctuation frequency W0 and the second operation evaluation value G20 is related to the reliability and safety index of the main power supply module. The reliability and safety index is that within an operation cycle, the stable operation time of the spacecraft must reach more than 80% of the entire operation cycle. The specific setting of the reliability and safety index is also affected by the operating environment. For example, environmental factors such as temperature, humidity, and air pressure may affect the reliability and safety index of the power supply equipment.

[0111] In the embodiment of the present invention, when the operation of the main power module meets the preset standard, the system will directly continue to use the main power module to supply power, thereby ensuring the continuous and stable propulsion of the spacecraft; if the operation of the main power module does not meet the preset standard, the system will intelligently retrieve historical data and make a fault judgment based on the historical fluctuation frequency, thereby avoiding the limitation of relying solely on current data to make decisions; by analyzing the historical fluctuation frequency, the system can more comprehensively evaluate the status of the main power module, and based on the analysis of historical data, it is helpful to locate the fault more accurately and take corresponding countermeasures; according to the comparison result of the historical fluctuation frequency with the preset standard fluctuation frequency, the fault is divided into primary and secondary, and corresponding processing is made, which is flexible. The level division helps the system to adopt different response strategies according to specific circumstances, improving the pertinence and effectiveness of responding to faults; the reliability and safety indicators are taken into account in the fault judgment mechanism, which makes the system design closer to actual operation needs; the setting of reliability and safety indicators is closely related to the long-term stable operation of the spacecraft, ensuring that the system can work reliably in various environments; the fault judgment mechanism also takes into account the impact of environmental factors on reliability and safety indicators, such as temperature, humidity, air pressure, etc. Comprehensive considerations enable the system to more comprehensively evaluate the operating status of the main power module, improving the accuracy and reliability of the judgment; it can more reliably respond to various complex situations and ensure the safe and stable operation of the spacecraft.

[0112] Specifically, the power source determination module 4 in this embodiment determines the abnormal cause of the main power source module according to the actual fluctuation frequency combined with the power source fault level of the main power source module;

[0113] If the power supply fault level is the secondary power supply fault and the actual fluctuation frequency is less than or equal to the standard fluctuation frequency, the power supply determination module 4 determines that the abnormal cause is: the remaining power of the power supply is low;

[0114] If the power supply fault level is the secondary power supply fault and the actual fluctuation frequency is greater than the standard fluctuation frequency, the power supply determination module 4 determines that the abnormal cause is: the main power supply module is damaged;

[0115] If the power supply fault level is the first-level power supply fault and the actual fluctuation frequency is greater than or equal to the standard fluctuation frequency, the power supply determination module 4 determines that the abnormal cause is: thruster overload;

[0116] If the power supply fault level is the first-level power supply fault and the actual fluctuation frequency is less than the standard fluctuation frequency, the power supply determination module 4 determines that the abnormal cause is: the main power supply module is damaged.

[0117] The present invention can accurately determine the specific cause of the abnormality of the main power module through the actual fluctuation frequency and the power fault level of the main power module in real time. Accurate determination helps to quickly find the fault point and reduce the time and cost of troubleshooting. For power faults of different levels, targeted abnormality handling strategies are adopted. For example, in the case of a secondary power failure, the power remaining power is judged to be low or the main power module is damaged according to the fluctuation frequency, so as to take corresponding repair measures in a targeted manner. The fault judgment takes into account the relationship between the power fault level and the actual fluctuation frequency, so as to comprehensively evaluate the state of the main power module. Comprehensive consideration makes the system handle abnormal situations more comprehensive and accurate. Each abnormal situation has a clear judgment logic, so that the analysis of the abnormal cause is clear and easy to understand, which helps engineers to quickly understand the fault situation and take corresponding countermeasures. By judging the abnormal cause by the fluctuation frequency and the fault level, potential fault risks can be discovered in advance, and preventive measures can be taken to avoid the impact of the fault on the spacecraft. The early warning and prevention mechanism helps to improve the stability and reliability of the spacecraft. It can more effectively deal with various abnormal situations of the main power module and ensure the safe and stable operation of the spacecraft.

[0118] Specifically, in this embodiment, based on the abnormal reason being: when the remaining power of the power supply is low, the power supply determination module sends a charging signal to charge the main power supply module;

[0119] Based on the abnormal reason being: when the propeller is overloaded, the power supply determination module sends a first adjustment signal to expand the capacity of the main power supply module;

[0120] After switching the backup power supply, the power supply determination module determines whether the operation of the backup power supply module meets the preset standard according to the single power supply power consumption;

[0121] If the single power supply power consumption is less than or equal to the preset standard power supply power consumption, it is determined that the operation of the backup power supply module meets the preset standard;

[0122] If the single power consumption is greater than the standard power consumption, it is determined that the operation of the backup power module does not meet the preset standard, and a second adjustment signal is sent to expand the capacity of the backup power module;

[0123] The power source determination module 4 obtains the power consumption of each single power supply during the propulsion process of the spacecraft; calculates the average power consumption according to each single power supply power consumption; and determines the adjustment strategy for the backup power supply module according to the average power consumption combined with the standard power consumption;

[0124] If the average power consumption is greater than or equal to the standard power consumption, the power determination module 4 determines that the backup power module has been partially damaged, and repairs the backup power module based on the loss ratio;

[0125] If the average power consumption is less than the standard power consumption, the power determination module 4 determines that the backup power module has no loss.

[0126] The embodiment of the present invention adopts precise processing strategies for different abnormal reasons, such as sending a charging signal, a first adjustment signal or a second adjustment signal, to process and adjust the main power module or the backup power module accordingly; after switching to the backup power module, the operation status of the backup power module is dynamically determined according to the single power consumption, and expansion or maintenance measures are taken to ensure that the backup power module can operate normally when needed; the average power consumption is calculated according to the single power consumption, and combined with the standard power consumption, it is intelligently determined whether the backup power module needs to be adjusted. The intelligent adjustment strategy helps to deal with the backup power module in a timely manner. changes to ensure stable power supply for the spacecraft; by obtaining the power consumption during the propulsion of the spacecraft and calculating the average power consumption, real-time monitoring of the operating status of the backup power module is achieved, and maintenance is carried out according to the loss situation. The real-time monitoring and maintenance mechanism helps to promptly discover and solve problems with the backup power module, ensuring the reliability of the spacecraft; intelligent adjustment strategies and real-time monitoring and maintenance can effectively save costs and resources, avoid unnecessary repairs and replacements, and at the same time ensure the effective use and long-term stable operation of the backup power module; can more effectively deal with various abnormal situations of the main power module and the backup power module, ensuring the safe and stable operation of the spacecraft.

[0127] Specifically, this embodiment further provides a control method for a spacecraft system, including:

[0128] Step S1, collecting the main operating parameters of the main power module, and judging whether the single microwave electric pushing operation of the main power module meets the preset standard according to the main operating parameters;

[0129] Step S2, when the operation of the single microwave electric propulsion does not meet the preset standard, determining the reason why the main power module does not meet the standard and corresponding adjustment measures;

[0130] Step S3, when the main power module does not meet the preset standard and the backup power module needs to be replaced, the backup power module is tested to determine whether it meets the preset standard, and based on the failure to meet the preset standard, an optimization method for the backup power module is determined.

[0131] The embodiment of the present invention can monitor the status of the main power module in real time by collecting the main operating parameters of the main power module and judging the operating status of a single microwave electric propulsion, and promptly find out whether it meets the preset standards to ensure the normal operation of the main power module; when the operation of a single microwave electric propulsion does not meet the preset standards, the reason for the non-compliance of the main power module can be quickly determined, and corresponding adjustment measures can be taken. The rapid response can effectively avoid the impact of the non-compliance on the spacecraft, thereby ensuring the stability of the spacecraft; when the main power module does not meet the preset standards and needs to be replaced with a backup power module, the backup power module is detected to determine whether it meets the preset standards; if it does not meet the preset standards, the optimization method for the backup power module is determined to ensure the performance and stability of the backup power module; through real-time monitoring, rapid response and timely switching and optimization of the backup power module, the reliability and stability of the spacecraft system can be improved, and the control method for improving reliability and stability helps to ensure the long-term stable operation of the spacecraft and cope with various abnormal situations; it can effectively ensure the safe operation of the spacecraft system.

[0132] The calculation compensation parameters and the calculation adjustment parameters described in the present invention have two functions: one is to balance the left and right dimensions of the formula, and the other is to adjust the numerical results. No specific assignment is performed in this embodiment. In addition, the calculation formulas in this embodiment are used to intuitively reflect the adjustment relationship between the numerical values, such as positive correlation and negative correlation. Unless otherwise specified, the parameter values ​​that are not specifically limited to numerical values ​​are all positive.

[0133] So far, the technical solutions of the present invention have been described in conjunction with the preferred embodiments shown in the accompanying drawings. However, it is easy for those skilled in the art to understand that the protection scope of the present invention is obviously not limited to these specific embodiments. Without departing from the principle of the present invention, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present invention.

[0134] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A spacecraft system, characterized in that: include: Microwave electric propulsion module, which is used to provide power for the flight of spacecraft; It includes: a main power module and a backup power module; the main power module is used as the main power source for the operation of the spacecraft and is used to continuously perform microwave electric propulsion on the spacecraft; the backup power module includes a plurality of battery packs as the backup power source for the operation of the spacecraft; A charging module, which charges the main power module and the backup power module by converting solar energy into chemical energy; A data acquisition module, which is used to collect the actual operating parameters of each power module in real time; A power supply determination module, which determines whether the operation of a single microwave electric propulsion meets the preset standard according to the collected actual operation parameters, and determines the reason for not meeting the standard, and determines whether the backup power supply module needs to be used according to the reason for not meeting the standard, and when it is determined to switch the backup power supply module for power supply, detects whether the operation of the backup power supply module meets the standard, and determines a corresponding optimization method when the backup power supply module does not meet the standard; The data acquisition module includes: a first acquisition unit, a second acquisition unit, a third acquisition unit and a fourth acquisition unit; The first acquisition unit is used to acquire actual operating parameters of the main power supply of the main power supply module; The second acquisition unit is used to acquire the actual operating parameters of the backup power supply of the backup power supply module; The third acquisition unit is used to collect the actual fluctuation frequency of the main power module during the power supply process; The fourth collection unit is used to collect the single power supply power consumption of the backup power module; The actual operating parameters of the main power supply include: the actual operating current of the main power supply, the actual operating voltage of the main power supply, the actual fluctuation frequency and the single power consumption; The power source determination module determines the abnormal cause of the main power source module according to the actual fluctuation frequency and the power source fault level of the main power source module; If the power supply fault level is a secondary power supply fault and the actual fluctuation frequency is less than or equal to the standard fluctuation frequency, the power supply determination module determines that the abnormal cause is: the remaining power of the power supply is low; If the power supply fault level is the secondary power supply fault and the actual fluctuation frequency is greater than the standard fluctuation frequency, the power supply determination module determines that the abnormal cause is: the main power supply module is damaged; If the power supply fault level is a first-level power supply fault and the actual fluctuation frequency is greater than or equal to the standard fluctuation frequency, the power supply determination module determines that the abnormal cause is: thruster overload; If the power supply fault level is the first-level power supply fault and the actual fluctuation frequency is less than the standard fluctuation frequency, the power supply determination module determines that the abnormal cause is: the main power supply module is damaged; Based on the abnormal reason being: when the remaining power of the power supply is low, the power supply determination module sends a charging signal to charge the main power supply module; Based on the abnormal reason being: when the thruster is overloaded, the power source determination module sends a first adjustment signal to expand the capacity of the main power source module; After switching the backup power supply, the power supply determination module determines whether the operation of the backup power supply module meets the preset standard according to the single power supply power consumption; If the single power supply power consumption is less than or equal to the preset standard power supply power consumption, it is determined that the operation of the backup power supply module meets the preset standard; If the single power consumption is greater than the standard power consumption, it is determined that the operation of the backup power module does not meet the preset standard, and a second adjustment signal is sent to expand the capacity of the backup power module; The power supply determination module obtains the power consumption of each single power supply during the propulsion process of the spacecraft; calculates the average power consumption according to each single power supply power consumption; and determines the adjustment strategy for the backup power supply module according to the average power consumption combined with the standard power supply power consumption; If the average power consumption is greater than or equal to the standard power consumption, the power determination module determines that the backup power module has been partially damaged, and repairs the backup power module based on the loss ratio; If the average power consumption is less than the standard power consumption, the power determination module determines that the backup power module has no loss.

2. The spacecraft system according to claim 1, characterized in that: For each main actual operating current and each main actual operating voltage during any single microwave electric propulsion process; The power source determination module integrates the types of each main actual operating current and each main actual operating voltage, including: a number of main safe operating currents, a number of abnormal operating currents, a number of main safe operating voltages and a number of abnormal operating voltages; and calculates a single microwave electric propulsion evaluation value according to the integration situation; Wherein, for any main actual operating current; if the main actual operating current falls within the preset current safety fluctuation range, the power supply determination module determines that the main actual operating current type is a safe current; If the main actual operating current does not fall within the current safety fluctuation range, the power source determination module determines that the main actual operating current type is an abnormal current; For any main actual operating voltage; if the main actual operating voltage falls within the preset voltage safety fluctuation range, the power supply determination module determines that the main actual operating voltage type is a safe voltage; If the main actual operating voltage does not fall within the voltage safety fluctuation range, the power source determination module determines that the main actual operating voltage type is an abnormal voltage.

3. The spacecraft system according to claim 2, characterized in that: The power determination module determines whether the operation of the main power module meets the preset standard according to the first difference absolute value and the preset first operation evaluation value; If the absolute value of the first difference is less than or equal to the first operation evaluation value, it is determined that the operation of the main power module meets the preset standard; If the absolute value of the first difference is greater than the first operation evaluation value and the single microwave electric pushing evaluation value is greater than the preset single microwave electric pushing standard value, it is determined that the operation of the main power supply module meets the preset standard; If the absolute value of the first difference is greater than the first operation evaluation value and the single microwave electric pushing evaluation value is less than the single microwave electric pushing standard value, it is determined that the operation of the main power module does not meet the preset standard; The first absolute value of the difference is the absolute value of the difference between the single microwave electric-pushing evaluation value and the single microwave electric-pushing standard value.

4. The spacecraft system according to claim 3, characterized in that: When the power source determination module determines that the operation of the main power source module meets the preset standard, the main power source module continues to be used as the power source for the next propulsion; When it is determined that the operation of the main power module does not meet the preset standard based on the power determination module, historical data is retrieved, and the operation status of the main power module is determined according to the historical data; The historical data is the historical fluctuation frequency of the main power module during the historical operation cycle.

5. The spacecraft system according to claim 4, characterized in that: The power supply determination module determines the power supply fault level of the main power supply module according to the second difference absolute value combined with a preset second operation evaluation value; If the absolute value of the second difference is less than or equal to the second operation evaluation value, the power source determination module determines that the main power source module has no fault and the data acquisition module collects abnormal data; If the absolute value of the second difference is greater than the second operation evaluation value and the historical fluctuation frequency is less than the preset standard fluctuation frequency, the power source determination module determines that the main power source module is a secondary power source failure, and switches the backup power source module to advance; If the absolute value of the second difference is greater than the second operation evaluation value and the historical fluctuation frequency is greater than the standard fluctuation frequency, the power source determination module determines that the main power source module is a primary power source failure, and switches to the backup power source module for advancement; The second absolute value of the difference is the absolute value of the difference between the historical fluctuation frequency and the standard fluctuation frequency.

6. A method for controlling a spacecraft system, based on the spacecraft system according to any one of claims 1 to 5, characterized in that: Step S1, collecting the main operating parameters of the main power module, and judging whether the single microwave electric pushing operation of the main power module meets the preset standard according to the main operating parameters; Step S2, when the operation of the single microwave electric propulsion does not meet the preset standard, determining the reason why the main power module does not meet the standard and corresponding adjustment measures; Step S3, when the main power module does not meet the preset standard and the backup power module needs to be replaced, the backup power module is tested to determine whether it meets the preset standard, and based on the failure to meet the preset standard, an optimization method for the backup power module is determined.

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