CN113725992B - Spacecraft power supply system fault identification and isolation method - Google Patents
Spacecraft power supply system fault identification and isolation method Download PDFInfo
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- CN113725992B CN113725992B CN202110813498.3A CN202110813498A CN113725992B CN 113725992 B CN113725992 B CN 113725992B CN 202110813498 A CN202110813498 A CN 202110813498A CN 113725992 B CN113725992 B CN 113725992B
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- 238000002955 isolation Methods 0.000 title claims abstract description 37
- 238000000034 method Methods 0.000 claims description 30
- 238000012544 monitoring process Methods 0.000 claims description 20
- 238000013461 design Methods 0.000 claims description 17
- 238000001514 detection method Methods 0.000 claims description 9
- 238000005516 engineering process Methods 0.000 claims description 8
- 238000005070 sampling Methods 0.000 claims description 6
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 claims description 4
- 238000003491 array Methods 0.000 claims description 4
- 239000003990 capacitor Substances 0.000 claims description 4
- 238000005286 illumination Methods 0.000 claims description 4
- 229910001416 lithium ion Inorganic materials 0.000 claims description 4
- JIXYFZKFYITQCJ-UHFFFAOYSA-N 3-(4-methoxyphenyl)-4-phenyl-1,2,4-triazole Chemical compound C1=CC(OC)=CC=C1C1=NN=CN1C1=CC=CC=C1 JIXYFZKFYITQCJ-UHFFFAOYSA-N 0.000 claims description 3
- 230000002159 abnormal effect Effects 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000007257 malfunction Effects 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
- H02J9/061—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems for DC powered loads
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05F—SYSTEMS FOR REGULATING ELECTRIC OR MAGNETIC VARIABLES
- G05F1/00—Automatic systems in which deviations of an electric quantity from one or more predetermined values are detected at the output of the system and fed back to a device within the system to restore the detected quantity to its predetermined value or values, i.e. retroactive systems
- G05F1/66—Regulating electric power
- G05F1/67—Regulating electric power to the maximum power available from a generator, e.g. from solar cell
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
- H02J7/00304—Overcurrent protection
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
- H02J7/00306—Overdischarge protection
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
- H02J7/00308—Overvoltage protection
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
Abstract
The invention discloses a fault identification and isolation method for a spacecraft power supply system, which comprises the steps of classifying all specific fault modes in an MPPT module into an open circuit fault and a short circuit fault, and identifying and isolating the two fault modes; under normal conditions, the backup module has no input, and after a fault is detected, the main MPPT module 1 or the MPPT module 2 is cut off through the change-over switch K1 or the change-over switch K2, and the output of the solar cell array 1 or the solar cell array 2 is connected to the input of the backup MPPT module, so that fault isolation and uninterrupted power supply of a system are realized. The invention solves the problems of complete fault identification and isolation of the MPPT type spacecraft, ensures the working continuity of the power supply system, improves the autonomy and reliability of the power supply system of the spacecraft and ensures the safety of the system.
Description
Technical Field
The invention relates to a power supply system fault identification and isolation method, in particular to a fault identification and isolation method for a spacecraft power supply system based on an MPPT (maximum power point tracking) technology, and belongs to the field of power supply systems.
Background
The spacecraft power supply system is a basic platform system of the spacecraft and is directly related to the safety of the spacecraft, so that the reliability and safety of the spacecraft power supply system are very important, redundant design and fault identification and isolation technologies are often needed to be adopted for the power supply system, particularly for deep space exploration of the spacecraft, real-time measurement and control are often impossible due to the limitation of long-distance and measurement and control arc sections, and the ground can not identify and process faults of the spacecraft in time, so that the spacecraft is required to have very high autonomy and can autonomously identify and isolate faults, and the safety and reliability of the whole satellite system are enhanced.
Unlike traditional parallel split power regulation type spacecraft power supply system, the spacecraft power supply system based on MPPT technology is a series system, namely, an MPPT power regulation module is connected in series between a solar cell array and a load, the solar cell array is an input of the MPPT module, and outputs of the MPPT modules are gathered into a primary power bus to supply power to the load. The current spacecraft is mainly a parallel shunt type power supply system, and is mostly a near-ground orbit, the automatic management function of the spacecraft is not strong, the fault mode of the parallel shunt type power supply system is easy to judge, and the failure influence of a single shunt string is small because the proportion of the power of the single string in the shunt type power supply system to the total power of the system is small. In deep space application represented by Mars detection, the MPPT type power supply system is a serial type power supply system, because real-time measurement and control are not possible, the requirement on the autonomous management function of the power supply system is higher, and because the proportion of solar cell array power corresponding to each MPPT module to the power of the whole device is larger, the influence of failure on the system is larger, the interior of the MPPT module is complex, the fault points and specific fault modes are more, and how to autonomously perform fault identification and isolation is an important function of the MPPT type spacecraft power supply system, so that the MPPT type power supply system is an essential requirement for guaranteeing the safety of the whole device.
In the prior published reports, reports related to MPPT type spacecraft power supply system fault identification and isolation protection are not reported, protection measures reported in other fields are only aimed at protection of specific fault points, fault coverage cannot be achieved, and the adopted measures are all to stop the operation of an MPPT module and cannot meet the requirements of aerospace application. The invention provides a protection method, which classifies all faults in an MPPT module into two types, and performs independent isolation protection aiming at the two types of faults so as to ensure that the continuous operation of a power supply system is not influenced. The reliability and the safety of the spacecraft power supply system are improved.
Disclosure of Invention
The invention solves the technical problems that: the deep space exploration task requirement represented by Mars is met, the defects of the prior art are overcome, the fault identification and isolation method for the spacecraft power supply system is provided, the problem of complete fault identification and isolation of the MPPT type spacecraft is solved, the working continuity of the power supply system is ensured, the autonomy, the reliability and the safety of the spacecraft power supply system are improved.
The technical solution of the invention is as follows: a fault identification and isolation method for a spacecraft power supply system is characterized in that the spacecraft power supply system is a power supply system adopting a serial MPPT power regulation technology and comprises 3 MPPT modules, a plurality of solar battery arrays, a lithium ion storage battery pack, an isolation diode, a change-over switch, a filter capacitor and a load; each MPPT module corresponds to a solar cell array, the output of the solar cell array is used as the input of the MPPT module, the outputs of the MPPT modules are converged into a primary bus, and the primary bus is connected with the lithium ion storage battery pack and the load; at least one module is used as a backup module in the MPPT modules, and the other modules are main modules; the input end of the MPPT module 1 is connected with the solar battery array 1 through the change-over switch k1, the input end of the MPPT module 2 is connected with the solar battery array 2 through the change-over switch k2, the MPPT module 1 and the MPPT module 2 are used as main part modules, the MPPT module 3 is used as a backup module, the outputs of the MPPT module 1, the MPPT module 2 and the MPPT module 3 are respectively connected with anodes of the isolation diodes D1, D2 and D3, cathodes of the isolation diodes D1, D2 and D3 are connected together to form a primary bus, the positive end of the storage battery pack is connected with a primary bus, the negative end of the storage battery pack is grounded, the filter capacitor C is connected between the primary bus and the ground, and the electric load is connected on the primary bus; all specific fault modes in the MPPT module are classified into an open circuit fault and a short circuit fault, and the two fault modes are identified and isolated; under normal conditions, the backup module has no input, and after a fault is detected, the main MPPT module 1 or the MPPT module 2 is cut off through the change-over switch K1 or the change-over switch K2, and the output of the solar cell array 1 or the solar cell array 2 is connected to the input of the backup MPPT module, so that fault isolation and uninterrupted power supply of a system are realized.
The open-circuit fault refers to a fault in the MPPT module that all the MPPT modules cannot correctly transmit the output power of the corresponding solar cell array to the output end; the "short circuit fault" refers to all faults in the MPPT module that cause abnormal continuous transmission of output power of the corresponding solar cell array to the output terminal.
The identification and isolation method of the short-circuit fault is that after the voltage of the storage battery reaches or exceeds the highest design voltage which can be reached, the output power of the solar cell array is still transmitted to the primary bus by the MPPT module, the MPPT module is considered to have the short-circuit fault, and the input end power of the short-circuit fault module is connected to the backup module.
The specific steps of the short-circuit fault identification and isolation method are as follows:
11 After the normal working state is established, the storage battery is connected with the bus; periodically monitoring the battery voltage, i.e. the primary bus voltage, when it is detected that the battery voltage is greater than the maximum design voltage V full And duration T 0 If the set threshold value is larger than the set threshold value, the step 12) is entered;
12 Judging whether the MPPT module 1 and the MPPT module 2 are the main parts, if so, entering a step 13), otherwise, ending;
13 Periodically monitoring the output current I of the solar cell array 1 out1 ；
14 When detecting the output current I of the solar cell array 1 out1 Greater than reference current I ref When and duration is greater than T 0 Switching the main MPPT module 1 into a backup; otherwise, entering step 15);
15 When detecting the output current I of the solar array 2 out2 Greater than I ref And a duration of time greater than T 0 Switching the main MPPT module 2 into a backup; if not, the step 11) is entered, and the monitoring is continued.
The highest design voltage V full Voltage greater than the maximum charge constant voltage point of the storage battery pack, andless than the battery pack safety voltage.
The duration T 0 More than 3 times the monitoring sampling period.
The reference current I ref Is a positive value close to 0, but is greater than the minimum output current of the solar cell array that the system can recognize.
The identification and isolation of the open circuit fault refer to that when the primary bus voltage does not reach the highest design voltage, when the solar cell array can output power and the power is not transmitted to the primary bus by the MPPT module, the MPPT module is considered to have the open circuit fault, and the power of the input end of the open circuit fault module is connected to the backup module.
The specific implementation steps of the open circuit fault identification and isolation method are as follows:
21 After the normal working state is established, the storage battery is assembled into the primary bus, the voltage of the storage battery is periodically monitored, namely, the voltage of the primary bus, when the voltage of the storage battery is detected to be smaller than V ref And duration is greater than T 0 Step 22) is entered; wherein V is ref <V full ；
22 Judging whether the MPPT module 1 and the MPPT module 2 are the main parts, if so, entering a step 23), otherwise, ending;
23 Periodically monitoring the output current I of the solar cell array 1 out1 And the solar cell array 2 outputs current I out2 ；
24 When detecting the output current I of the solar array 2 out2 ＞I high And the solar array 1 outputs current I out1 ＜I ref And duration T 1 Cutting back the MPPT module 1, and ending the program; if the output current I of the solar array 2 is not satisfied in the detection process out2 ＞I high And the solar array 1 outputs current I out1 ＜I ref Condition, go to step 25); the I is high When the output current of the solar cell array is larger than the larger current value, the current has stronger illumination intensity;
25 When detecting the output current I of the solar cell array 1 out1 ＞I high And solar cell array2 output current I out2 ＜I ref And duration T 1 Cutting back the MPPT module 2, and ending the program; the output current I of the solar cell array 1 is not satisfied in the detection process out1 ＞I high And the solar cell array 2 outputs current I out2 ＜I ref Condition ", immediately ending step 25), entering step 21), and performing real-time loop monitoring.
Said voltage V ref The voltage is smaller than the maximum charging constant voltage point voltage of the storage battery and is larger than the overdischarge safety voltage of the storage battery; v (V) ref The voltage value of the battery pack is 80% -90% of the voltage value corresponding to the charge state.
Compared with the prior art, the invention has the advantages that:
(1) The protection method for distinguishing the conventional inspection specific fault points or fault modes is characterized in that the proposed protection strategy classifies the results caused by a plurality of failure factors into short-circuit faults and open-circuit faults according to the application requirements of an actual system, the protection method is not limited by the specific fault points and the fault modes, complicated mode analysis and cause analysis on the internal fault modes of the MPPT module are not needed, so that fault protection becomes feasible, and the protection method has good fault envelope and coverage;
(2) The fault identification and isolation method is convenient for autonomous implementation, can keep the continuity of power supply of the system in the process of implementing protection isolation, ensures that a main task is not affected, and is particularly suitable for deep space detection tasks needing a highly autonomous management function;
(3) The system is easy to realize, and according to the basic protection principle, the power supply system can be changed and expanded according to the design practice of the power supply system, for example, the number of backup modules can be changed according to the practical application, but the basic protection thought is unchanged, so that the application scene of the protection implementation method is richer;
(4) The protection implementation problem of the MPPT type power supply system is solved, the reliability and the safety of the system are enhanced, and the application requirements of the subsequent spacecraft power supply system with large temperature illumination intensity change range and high autonomous management requirement represented by deep space exploration are met.
Drawings
FIG. 1 is a spacecraft power system topology based on 3 MPPT modules suitable for use in the method;
FIG. 2 is a "short-circuit protection" flow chart;
FIG. 3 is a "open circuit protection" flow chart;
Detailed Description
The invention discloses a spacecraft power supply system based on an MPPT technology, which is a power supply system adopting a serial MPPT power regulation technology, namely, each MPPT regulation module corresponds to a solar cell array, the output of the solar cell array is used as the input of the MPPT module, the output of the MPPT module is converged into a primary bus, and a storage battery and a load are connected through the primary bus. At least one or more of the MPPT modules are used as backup modules, and the others are primary modules.
Referring to fig. 1, an exemplary power supply system of a spacecraft based on an MPPT technology corresponding to the protection method of the present invention is shown, an input end of an MPPT1 module is connected with a solar array 1, an input end of an MPPT2 module is connected with a solar array 2, MPPT1 and MPPT2 are used as main modules, MPPT3 is used as a backup module, an output of the backup module is connected with an output of 2 main modules to form a primary bus, a positive end of a storage battery is connected with the primary bus, a negative end of the storage battery is grounded, and an electric load is connected with the primary bus. Under normal conditions, the backup module has no input, and after a fault is detected, the main MPPT module 1 or the MPPT2 is cut off through the change-over switch K1 or the change-over switch K2, and the output of the solar cell array 1 or the solar cell array 2 is connected to the input of the backup MPPT module, so that fault isolation and uninterrupted power supply of the system are realized. In order to avoid searching and analyzing complicated fault points in the MPPT module, based on the energy output capability of the bus, the faults of all MPPT modules are classified into an open circuit fault and a short circuit fault, wherein the open circuit fault refers to the fault that all MPPT modules cannot correctly transmit the output power of a corresponding solar cell array to an output end (primary bus) in the MPPT module, and the specific reasons for causing the fault can be various; the "short-circuit fault" refers to all faults in the MPPT module, which cause the abnormal continuous transmission of the output power of the corresponding solar cell array to the output terminal, and the reasons for specifically causing the faults can be various. The basic idea of the protection against short-circuit fault is that when the voltage of the storage battery reaches or exceeds the highest design voltage which can be reached, the output power of the solar cell array is still transmitted to the primary bus by the MPPT module, the MPPT module is considered to have short-circuit fault, and the input end power of the short-circuit fault module is connected to the backup module. When the primary bus voltage does not reach the highest design maximum voltage, when the solar cell array can output power and the power is not transmitted to the primary bus by the MPPT module, the MPPT module is considered to have an open circuit fault, and the power of the input end of the open circuit fault module is connected to the backup module. The method comprises the following specific implementation steps:
the short-circuit fault protection implementation steps are as follows:
1) After the normal working state is established, the storage battery is assembled into the bus, the voltage of the storage battery (namely, the voltage of the primary bus) is periodically monitored, and when the voltage of the storage battery is detected to be larger than the highest design voltage V full And a duration of time greater than T 0 Step 2) is entered.
The highest design voltage V full Should be greater than the battery maximum charge constant voltage point voltage, while being less than the battery safety voltage; under normal conditions, after the voltage of the storage battery pack is larger than the maximum charging constant voltage point voltage, the normally working MPPT module can not transmit the solar cell array power to the output end, if the solar cell array output power is still transmitted to the output end through the MPPT module at the moment, the MPPT module is considered to be in an uncontrolled short-circuit fault mode, the connection between the input end of the module and the solar cell array output is disconnected through the change-over switch, the solar cell array output is connected to the backup module, and fault removal and isolation are realized. Wherein duration T 0 In order to prevent malfunction caused by interference signals, the duration T should be set according to the monitoring sampling period and the actual application condition 0 In general, the duration T is set 0 More than 3 times the monitoring sampling period.
2) Judging whether the MPPT module 1 and the MPPT module 2 are the main parts, if so, entering a step 3), otherwise, ending.
In the typical application circuit topology of fig. 1, since there are only 1 backup MPPT circuits, and the maximum power capacity that can be handled is the same as that of the main MPPT1 and the main MPPT2, the output power of the solar cell arrays corresponding to the main MPPT module 1 and the main MPPT module 2 cannot be connected to the backup MPPT module at the same time, and for this reason, it is determined whether there is a main MPPT circuit that has been switched to the backup, and if the backup is already occupied, the fault handling procedure is exited. For different application occasions, the number of backups can be increased, and if the backup modules still remain unoccupied, the failure master module is switched to the idle backup module.
3) Periodically and continuously monitoring output current I of solar array 1 out1 。
4) When detecting the output current I of the solar array 1 out1 Greater than reference current I ref When and duration is greater than T 0 And switching the MPPT module 1 to backup. Wherein the reference current I ref A positive value close to 0, but should be greater than the minimum output current of the solar array that the system can recognize. When the steps 1 to 4 are established, it is indicated that when the voltage of the storage battery pack is higher than the maximum design voltage, power is still transmitted from the MPPT module 1 to the output end and enters the primary bus, and it is indicated that an uncontrolled short-circuit fault occurs in the MPPT module 1. Otherwise, enter step 5);
5) When detecting the output current I of the solar array 2 out2 Greater than I ref And a duration of time greater than T 0 And switching the MPPT module 2 main share module into a backup. And 4) the step is the same as that of 4), namely, under the condition that the MPPT module 1 does not have a fault, the MPPT module 2 is continuously judged, and if more MPPT main share modules exist, the sequence judgment is carried out until all the backup modules are occupied. If the conditions are not met, the method enters the step 1, and the real-time cycle monitoring is continued.
A flow chart of the "short circuit failure" protection measures for a power system with 2 primary and 1 backup MPPT modules is shown in fig. 2.
The "open circuit failure" protection implementation steps are as follows:
1) After the normal working state is established, the storage battery is assembled into the primary bus, the voltage of the storage battery (namely the voltage of the primary bus) is periodically monitored, and when the detection is carried outTo a battery voltage less than V ref (V ref <V full ) And duration is greater than T 0 Step 2) is entered. Voltage V ref The voltage which is smaller than the maximum charging constant voltage point voltage of the storage battery and larger than the overdischarge safety voltage of the storage battery can be treated as early as possible after the fault occurs, and the voltage cannot be too small, so that the voltage value corresponding to 80% -90% of the charge state of the storage battery can be taken as a typical application; duration T 0 In order to prevent malfunction caused by interference signals, the duration T should be set according to the monitoring sampling period and the actual application condition 0 In general, the duration T is set 0 More than 3 times the monitoring sampling period.
2) Judging whether the MPPT module 1 and the MPPT module 2 are the main parts, if so, entering a step 3), otherwise, ending the program. In the typical application circuit topology of fig. 1, since there are only 1 backup MPPT modules, and the maximum power capacity that can be handled is the same as that of the main MPPT module 1 and the main MPPT module 2, the output power of the solar cell arrays corresponding to the main MPPT module 1 and the main MPPT module 2 cannot be connected to the backup MPPT module at the same time, and therefore, whether the main MPPT module has been switched to the backup is determined in this step, and if the backup has been occupied, the fault handling procedure is exited. For different application occasions, the number of backups can be increased, and if the backup modules still remain unoccupied, the failure master module is switched to the idle backup module.
3) Periodically monitoring the output current I of the solar cell array 1 out1 And the solar cell array 2 outputs current I out2 ；
4) When detecting the output current I of the solar cell array 2 out2 ＞I high And the solar cell array 1 outputs current I out1 ＜I ref And duration T 1 And (5) cutting back the MPPT module 1, and ending the program. The output current I of the solar cell array 2 is not satisfied in the detection process out2 ＞I high And the solar cell array 1 outputs current I out1 ＜I ref Condition, immediately go to step 5). When the voltage of the storage battery pack is smaller than the maximum charge constant voltage point voltage, the MPPT module working normally will work the solar cell arrayAnd the rate is transmitted to the output end, if the solar cell array can output power at the moment and is not transmitted to the output end from the input end by the MPPT module, the MPPT module is considered to be in an uncontrolled open-circuit fault mode, and the connection between the input end of the module and the output of the solar cell array is disconnected by the change-over switch, so that the output of the solar cell array is connected to the backup module, and fault removal and isolation are realized. I high For a larger current value, when the output current of the solar cell array 2 is larger than the value, the current has stronger illumination intensity, the solar cell array 1 should have current output under the condition that the design difference of the solar cell array 1 and the solar cell array 2 is not large, the storage battery pack is not full (judged by the storage battery pack voltage through the step 1), the MPPT module 1 connected with the solar cell array does not normally transmit the power of the solar cell array to the primary bus, and the MPPT module 1 has uncontrolled open circuit fault for carrying out cut backup isolation protection. Wherein duration T 1 In order to prevent malfunction caused by interference signals, the situation that the solar cell array 1 and the solar cell array 2 respectively correspond to different solar wings of the movable spacecraft due to the fact that the solar light is not output is caused, for example, in the process of moving the solar wings, the conditions can be met to cause false triggering, so that T can be selected according to design application practice 1 Length of time.
5) When detecting the output current I of the solar cell array 1 out1 ＞I high And the solar cell array 2 outputs current I out2 ＜I ref And duration T 1 And (5) cutting back the MPPT module 2, and ending the program. The output current I of the solar cell array 1 is not satisfied in the detection process out1 ＞I high And the solar cell array 2 outputs current I out2 ＜I ref And (5) if the condition is met, immediately ending the step (5), and entering the step (1) to perform real-time cycle monitoring.
A flow chart of the "open circuit failure" protection measures for a power system with 2 primary and 1 backup MPPT modules is shown in fig. 3.
Although the present invention has been described with respect to the preferred embodiments, it is not intended to be limited thereto, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the above embodiments according to the technical matters of the present invention fall within the scope of the technical solution of the present invention.
Claims (7)
1. A fault identification and isolation method for a spacecraft power supply system is characterized in that the spacecraft power supply system is a power supply system adopting a serial MPPT power regulation technology and comprises 3 MPPT modules, a plurality of solar battery arrays, a lithium ion storage battery pack, an isolation diode, a change-over switch, a filter capacitor and a load; each MPPT module corresponds to a solar cell array, the output of the solar cell array is used as the input of the MPPT module, the outputs of the MPPT modules are converged into a primary bus, and the primary bus is connected with the lithium ion storage battery pack and the load; at least one module is used as a backup module in the MPPT modules, and the other modules are main modules; the input end of the MPPT module 1 is connected with the solar battery array 1 through the change-over switch k1, the input end of the MPPT module 2 is connected with the solar battery array 2 through the change-over switch k2, the MPPT module 1 and the MPPT module 2 are used as main part modules, the MPPT module 3 is used as a backup module, the outputs of the MPPT module 1, the MPPT module 2 and the MPPT module 3 are respectively connected with anodes of the isolation diodes D1, D2 and D3, cathodes of the isolation diodes D1, D2 and D3 are connected together to form a primary bus, the positive end of the storage battery pack is connected with the primary bus, the negative end of the storage battery pack is grounded, the filter capacitor C is connected between the primary bus and the ground, and the electric load is connected on the primary bus; the method is characterized in that: all specific fault modes in the MPPT module are classified into an open circuit fault and a short circuit fault, and the two fault modes are identified and isolated; under normal conditions, the backup module has no input, after a fault is detected, the main MPPT module 1 or the MPPT module 2 is cut off through the change-over switch K1 or the change-over switch K2, and the output of the solar cell array 1 or the solar cell array 2 is connected to the input of the backup MPPT module, so that fault isolation and uninterrupted power supply of a system are realized;
the open-circuit fault refers to a fault in the MPPT module that all the MPPT modules cannot correctly transmit the output power of the corresponding solar cell array to the output end; the short circuit fault refers to all faults in the MPPT module, which cause abnormal continuous transmission of output power of the corresponding solar cell array to an output end of the MPPT module;
the identification and isolation method of the short-circuit fault is that after the voltage of the storage battery reaches or exceeds the highest design voltage which can be reached, the output power of the solar cell array is still transmitted to the primary bus by the MPPT module, the MPPT module is considered to have the short-circuit fault, and the power of the input end of the short-circuit fault module is connected to the backup module;
the specific steps of the identification and isolation method of the short circuit fault are as follows:
11 After the normal working state is established, the storage battery is connected with the bus; periodically monitoring the battery voltage, i.e. the primary bus voltage, when it is detected that the battery voltage is greater than the maximum design voltage V full And duration T 0 If the set threshold value is larger than the set threshold value, the step 12) is entered;
12 Judging whether the MPPT module 1 and the MPPT module 2 are the main parts, if so, entering a step 13), otherwise, ending;
13 Periodically monitoring the output current I of the solar cell array 1 out1 ；
14 When detecting the output current I of the solar cell array 1 out1 Greater than reference current I ref When and duration is greater than T 0 Switching the main MPPT module 1 into a backup; otherwise, entering step 15);
15 When detecting the output current I of the solar cell array 2 out2 Greater than I ref And a duration of time greater than T 0 Switching the main MPPT module 2 into a backup; if not, the step 11) is entered, and the monitoring is continued.
2. The method for identifying and isolating faults of a spacecraft power system according to claim 1, wherein the method comprises the following steps: the highest design voltage V full Is larger than the maximum charging constant voltage point voltage of the storage battery, and is smaller than the safety of the storage batteryA voltage.
3. The method for identifying and isolating faults of a spacecraft power system according to claim 1, wherein the method comprises the following steps: the duration T 0 More than 3 times the monitoring sampling period.
4. The method for identifying and isolating faults of a spacecraft power system according to claim 1, wherein the method comprises the following steps: the reference current I ref Is a positive value close to 0, but is greater than the minimum output current of the solar cell array that the system can recognize.
5. The method for identifying and isolating faults of a spacecraft power system according to claim 2, characterized in that: the identification and isolation of the open circuit fault refer to that when the primary bus voltage does not reach the highest design voltage, when the solar cell array can output power and the power is not transmitted to the primary bus by the MPPT module, the MPPT module is considered to have the open circuit fault, and the power of the input end of the open circuit fault module is connected to the backup module.
6. The method for identifying and isolating faults of a spacecraft power system according to claim 5, comprising the steps of: the specific implementation steps of the open circuit fault identification and isolation method are as follows:
21 After the normal working state is established, the storage battery is assembled into the primary bus, the voltage of the storage battery is periodically monitored, namely, the voltage of the primary bus, when the voltage of the storage battery is detected to be smaller than V ref And duration is greater than T 0 Step 22) is entered; wherein V is ref <V full ；
22 Judging whether the MPPT module 1 and the MPPT module 2 are the main parts, if so, entering a step 23), otherwise, ending;
23 Periodically monitoring the output current I of the solar cell array 1 out1 And the solar cell array 2 outputs current I out2 ；
24 When detecting the output current I of the solar cell array 2 out2 ＞I high And the solar cell array 1 outputs current I out1 ＜I ref And duration T 1 Cutting back the MPPT module 1, and ending the program; if the output current I of the solar cell array 2 is not satisfied in the detection process out2 ＞I high And the solar cell array 1 outputs current I out1 ＜I ref Condition ", step 25) is entered; the I is high When the output current of the solar cell array is larger than the larger current value, the current has stronger illumination intensity;
25 When detecting the output current I of the solar cell array 1 out1 ＞I high And the solar cell array 2 outputs current I out2 ＜I ref And duration T 1 Cutting back the MPPT module 2, and ending the program; the output current I of the solar cell array 1 is not satisfied in the detection process out1 ＞I high And the solar cell array 2 outputs current I out2 ＜I ref Condition ", immediately ending step 25), entering step 21), and performing real-time loop monitoring.
7. The method for identifying and isolating faults of a spacecraft power system according to claim 6, comprising the steps of: said voltage V ref The voltage is smaller than the maximum charging constant voltage point voltage of the storage battery and is larger than the overdischarge safety voltage of the storage battery; v (V) ref The voltage value of the battery pack is 80% -90% of the voltage value corresponding to the charge state.
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