CN112332411B - Spacecraft ground power supply safety alarm and processing system based on load characteristics - Google Patents
Spacecraft ground power supply safety alarm and processing system based on load characteristics Download PDFInfo
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- CN112332411B CN112332411B CN202011150125.4A CN202011150125A CN112332411B CN 112332411 B CN112332411 B CN 112332411B CN 202011150125 A CN202011150125 A CN 202011150125A CN 112332411 B CN112332411 B CN 112332411B
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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
- H02J3/00—Circuit arrangements for ac mains or ac distribution networks
- H02J3/001—Methods to deal with contingencies, e.g. abnormalities, faults or failures
- H02J3/00125—Transmission line or load transient problems, e.g. overvoltage, resonance or self-excitation of inductive loads
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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
- H02J13/00—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
- H02J13/00002—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network characterised by monitoring
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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
- H02J3/00—Circuit arrangements for ac mains or ac distribution networks
- H02J3/001—Methods to deal with contingencies, e.g. abnormalities, faults or failures
- H02J3/0012—Contingency detection
Abstract
The invention relates to a spacecraft ground power supply safety alarm and processing system based on load characteristics. The maximum output power of the ground power supply is adjusted in real time, so that the bus undervoltage or the over-discharge of a storage battery caused by insufficient output capacity of the ground power supply is prevented, and the power supply is prevented from being aged too fast and the failure rate is increased due to overhigh output capacity of the ground power supply; monitoring the electricity utilization health degree of the load, and realizing timely alarming for the condition that the actual power of the load is inconsistent with the expected power; the bus short-circuit fault and the bus overvoltage fault are quickly processed, the fault range is prevented from being enlarged, the load is prevented from being burnt or overcurrent, and the safety of the ground test of the spacecraft is greatly improved.
Description
Technical Field
The invention belongs to the technical field of spacecraft ground power supply safety alarming and processing, relates to a spacecraft ground power supply safety alarming and processing system based on load characteristics, and is suitable for spacecraft ground testing.
Background
During the spacecraft test, if a power supply fault occurs, equipment power failure or equipment overvoltage can be caused, and even equipment burnout can be caused. Therefore, the safety of power supply directly affects the safety and efficiency of spacecraft development. With the rapid development of aerospace technology in China, the complexity of the functions of the spacecraft is higher and higher, and the number of the spacecraft in research is increased year by year. In the face of continuously increasing development pressure, the probability of power supply faults is continuously increased, the influence range of the power supply faults is also enlarged, and the problem of spacecraft test safety is urgently to be solved. The ground power supply safety alarm and processing system of the spacecraft plays an important role in the development of the aerospace technology.
In the spacecraft test, the ground power supply safety alarm and processing system can acquire the current bus telemetering and ground power supply states in real time, and realize bus power supply capacity early warning and power supply fault emergency treatment based on the load power consumption characteristics. At present, a ground power supply system of a spacecraft only considers functions such as overvoltage protection and overcurrent protection, and the processing capacity also has a larger promotion space, which is mainly embodied in the following points:
firstly, after the bus power supply capacity is early-warned and processed, the monitoring and warning on the electric health degree of the load equipment are lacked. The conventional ground power supply system for the spacecraft generally only adjusts the output power of a power supply curve, and cannot realize timely alarm under the condition that the actual power consumption of equipment is inconsistent with the expected power consumption, so that the fault is further worsened.
Secondly, the bus power supply fault emergency treatment method is single and the emergency treatment capacity is weak. The traditional spacecraft ground power supply system only considers the emergency treatment of ground equipment aiming at bus faults, does not consider the emergency treatment of equipment on a spacecraft, lacks the processing function of bus short-circuit faults, and cannot effectively realize the emergency treatment of the power supply faults of the spacecraft system.
Therefore, the ground power supply safety alarm and processing system of the spacecraft is very necessary for the development of the aerospace technology and the improvement of the test safety of the spacecraft.
Disclosure of Invention
The technical problem solved by the invention is as follows: the system can adjust the power supply curve of the ground power supply in real time, thereby not only preventing the undervoltage of a bus or the over-discharge of a storage battery caused by the insufficient output capacity of the ground power supply, but also preventing the over-quick aging and the rising of the failure rate of the power supply caused by the over-high output capacity of the ground power supply; monitoring the electricity utilization health degree of the load, and realizing timely alarm for the condition that the actual power of the load is inconsistent with the expected power; the bus short-circuit fault and the bus overvoltage fault are quickly processed, the fault range is prevented from being enlarged, the load is prevented from being burnt or overcurrent, and the safety of the ground test of the spacecraft is greatly improved.
The technical solution of the invention is as follows:
a spacecraft ground power supply safety alarm and processing system based on load characteristics comprises a data acquisition module, a logic judgment module, an early warning and fault processing module and a ground power supply module;
the data acquisition module is used for acquiring spacecraft bus voltage V in real time bus Spacecraft bus current I bus Maximum output power P of ground power supply max Marking the command type and collecting the spacecraft bus voltage V bus Bus current I of spacecraft bus The maximum output power P of the ground power supply max And the instruction type mark is output to the logic judgment module. The instruction types are divided into a load power-on instruction and a non-load power-on instruction. When the instruction type is a load power-on instruction, the instruction type mark is 1; when the instruction type is a non-load power-on instruction or a no instruction, the instruction type mark is 0;
the logic judgment module is used for receiving the spacecraft bus voltage V output by the data acquisition module bus Bus current I of spacecraft bus Maximum output power P of ground power supply max And a command type mark, and according to the received spacecraft bus voltage V bus Bus current I of spacecraft bus Maximum output power P of ground power supply max Judging the current spacecraft ground power supply safety state by the instruction type mark, and outputting a judgment result to the early warning and fault processing module;
the early warning and fault processing module is used for generating early warning and fault processing measures according to the output result of the logic judgment module and sending the fault processing measures to the ground power supply;
and the ground power supply module is used for executing fault processing measures according to the output result of the early warning and fault processing module.
The method for judging the current ground power supply safety state by the logic judgment module comprises the following steps:
(1) When the instruction type is a load power-up instruction, the expected power P of the load is determined before the spacecraft executes the load power-up instruction load And calculating the redundant power delta P after the spacecraft executes the load power-on command.
If the redundant power DeltaP is not less than the redundant power threshold DeltaP min The spacecraft executes the load power-up command and calculates the actual load power P load ’ . If the error power is larger than the error upper limit delta P error If the actual power of the load is inconsistent with the expected power of the load, generating an alarm signal of abnormal health degree of the load electricity consumption, and calling the alarm signal as a fault signal 1; if the error power is not larger than the upper error limit, the actual power of the load is consistent with the expected power of the load, and the load is considered to be healthy in power utilization. The actual load power is the difference between the spacecraft power after the load power-up command is executed and the spacecraft power before the load power-up command is executed. The error power is the absolute value of the difference between the actual power of the load and the expected power of the load. If the redundant power DeltaP is less than the redundant power threshold DeltaP min And generating a bus power supply capacity early warning signal called as a fault signal 2.
When the instruction type is a non-load power-on instruction, no processing is performed;
(2) Calculating the jump value delta I of the bus current bus Judging the bus current jump value delta I bus Whether the current jump mild alarm upper limit delta I is exceeded max1 . If the bus current jump value delta I bus The upper limit Delta I of the mild alarm of the current jump is not exceeded max1 If yes, no treatment is carried out; if the bus current jump value delta I bus Exceeding the upper limit Delta I of the light alarm of current jump max1 But not exceeding the current jump severity alarm upper limit Delta I max2 Generating a slight bus current jumpAn alarm signal, referred to as fault signal 3; if the bus current jump value delta I bus Exceeding the current jump severity alarm upper limit Delta I max2 And the current bus voltage V bus Higher than the lower limit V of the bus voltage min Generating a bus current jump severity alarm signal called as a fault signal 4; if the bus current jump value delta I bus Exceeding the current jump heavy alarm upper limit Delta I max2 And the current bus voltage is not higher than the lower limit V of the bus voltage min A bus short fault alarm signal, referred to as fault signal 5, is generated. Bus current jump value delta I bus The current value of the bus current of the spacecraft is the absolute value of the difference value of the last sampling value;
(3) Judging spacecraft bus voltage V bus Whether it is higher than the upper limit V of the bus voltage max If spacecraft bus voltage V bus Not higher than the upper limit V of the bus voltage max Then no processing is needed; if spacecraft bus voltage V bus Higher than the upper limit V of the bus voltage max And judging the discharge current state of the storage battery. If the battery discharges current I discharge If the voltage is greater than 0, generating a storage battery power supply overvoltage alarm signal called as a fault signal 6; if the battery discharges current I discharge If the voltage is not greater than 0, generating a ground power supply overvoltage alarm signal called a fault signal 7;
the method for generating the early warning and fault handling measures by the early warning and fault handling module comprises the following steps:
(1) If the result output by the logic judgment module is an alarm signal with abnormal load electricity utilization health degree, namely a fault signal 1, automatically recording the current moment, a load power-on instruction and an alarm signal;
(2) If the result output by the logic judgment module is a bus power supply capacity early warning signal, namely a fault signal 2, sending an instruction to the ground power supply module, gradually increasing the maximum output power of the ground power supply module until the redundant power is greater than a redundant power threshold value, and automatically recording the current time, the maximum output power and an alarm signal;
(3) If the result output by the logic judgment module is a bus current jump slight alarm signal, namely a fault signal 3, automatically recording the current moment, a bus current jump value and an alarm signal;
(4) If the result output by the logic judgment module is a bus current jump severity alarm signal, namely a fault signal 4, automatically recording the current moment, a bus current jump value and an alarm signal;
(5) If the output result of the logic judgment module is a bus short circuit fault alarm signal, namely a fault signal 5, sending an instruction to the spacecraft, disconnecting a storage battery discharge switch, closing a load, sending an instruction to a ground power supply module, prohibiting output, and automatically recording the current moment, a bus current jump value, bus voltage and an alarm signal;
(6) If the result output by the logic judgment module is a storage battery power supply overvoltage alarm signal, namely a fault signal 6 occurs, an instruction is sent to the spacecraft, a storage battery discharge switch is disconnected, and the current time, the bus voltage and the alarm signal are automatically recorded;
(7) If the result output by the logic judgment module is a ground power supply overvoltage alarm signal, namely a fault signal 7, an instruction is sent to the ground power supply module, the output voltage is reduced, an instruction is sent to the spacecraft, a storage battery discharge switch is switched on, an instruction is sent to the ground power supply module again, the output is forbidden, and the current time, the bus voltage and the alarm signal are automatically recorded.
A spacecraft ground power supply safety alarm and processing method based on load characteristics comprises the following steps:
firstly, a data acquisition module acquires spacecraft bus voltage V bus Bus current I of spacecraft bus Maximum output power P of ground power supply max Marking the command type and collecting the spacecraft bus voltage V bus Bus current I of spacecraft bus Maximum output power P of ground power supply max And the instruction type mark is output to a logic judgment module;
secondly, the logic judgment module receives the spacecraft bus voltage V bus Bus current I of spacecraft bus Maximum output power P of ground power supply max And the command type mark judges the current ground power supply safety state of the spacecraft, andoutputting the judgment result to an early warning and fault processing module;
thirdly, the early warning and fault processing module generates early warning and fault processing measures according to the output result of the logic judgment module and sends the fault processing measures to the ground power supply module;
and fourthly, the ground power supply module executes a processing measure according to the output result of the early warning and fault processing module.
Compared with the prior art, the invention has the advantages that:
(1) Real-time spacecraft bus voltage V acquisition bus Spacecraft bus current I bus Maximum output power P of ground power supply max And an instruction type flag. If the command is a load power-up command, adjusting the maximum output power of the ground power supply; calculating the actual power of the load, and if the actual power of the load is inconsistent with the expected power, sending an alarm signal indicating that the health degree of the load electricity utilization is abnormal; aiming at bus short circuit faults and overvoltage faults, instructions are generated to a spacecraft or a ground system, faults are quickly processed, the fault range is prevented from being enlarged or loads are prevented from overflowing and burning, and the safety of spacecraft ground testing is greatly improved.
(2) The invention relates to a spacecraft ground power supply safety alarm and processing system based on load characteristics. The data acquisition module acquires spacecraft bus voltage, spacecraft bus current, ground power supply maximum output power and instruction type marks in real time and outputs the marks to the logic judgment module. The logic judgment module judges the current ground power supply safety state of the spacecraft according to the received data and outputs a judgment result to the early warning and fault processing module; the early warning and fault processing module generates early warning and fault processing measures according to the result output by the logic judgment module and sends the fault processing measures to the ground power supply; and the ground power supply module executes the fault processing measures according to the output result of the early warning and fault processing module. Therefore, the maximum output power of the ground power supply is adjusted in real time, the undervoltage of a bus or the over-discharge of a storage battery caused by the insufficient output capacity of the ground power supply is prevented, and the over-fast aging and the increase of the failure rate of the power supply caused by the over-high output capacity of the ground power supply are prevented; monitoring the electricity utilization health degree of the load, and realizing timely alarming for the condition that the actual power of the load is inconsistent with the expected power; the bus short-circuit fault and the bus overvoltage fault are quickly processed, the fault range is prevented from being enlarged, the load is prevented from being burnt or overcurrent, and the safety of the ground test of the spacecraft is greatly improved.
Drawings
Fig. 1 is a block diagram of a spacecraft ground power supply safety alarm and processing system based on load characteristics.
Fig. 2 is a flow chart of a spacecraft ground power supply safety alarm and processing system based on load characteristics.
Detailed Description
The invention is further described below with reference to the accompanying drawings. The specific implementation mode is as follows:
the invention provides a spacecraft ground power supply safety alarm and processing system based on load characteristics, which can adjust the maximum output power of a ground power supply in real time, prevent bus under-voltage or over-discharge of a storage battery caused by insufficient output capacity of the ground power supply, and prevent the power supply from aging too fast and the fault rate from rising caused by overhigh output capacity of the ground power supply; monitoring the electricity utilization health degree of the load, and realizing timely alarming for the condition that the actual power of the load is inconsistent with the expected power; the method has the advantages that the bus short-circuit fault and the bus overvoltage fault are quickly processed, the fault range is prevented from being enlarged, the load is prevented from being burnt or overcurrent is prevented, and the safety of the ground test of the spacecraft is greatly improved.
FIG. 1 is a block diagram of a spacecraft ground power supply safety alarm and processing system based on load characteristics. The system comprises a data acquisition module, a logic judgment module, an early warning and fault processing module and a ground power supply module;
the data acquisition module is used for acquiring spacecraft bus voltage V in real time bus Bus current I of spacecraft bus Output power P of ground power supply max Marking the command type and collecting the spacecraft bus voltage V bus Spacecraft bus current I bus Output power P of ground power supply max And outputting the instruction type mark to a logic judgment module. The instruction types are divided into load power-up instructions anda no load power up command. When the instruction type is a load power-on instruction, the instruction type mark is 1; when the instruction type is a non-load power-on instruction or no instruction, the instruction type mark is 0;
the logic judgment module is used for receiving the spacecraft bus voltage V output by the data acquisition module bus Bus current I of spacecraft bus Ground power supply output power P max And a command type mark, and according to the received spacecraft bus voltage V bus Bus current I of spacecraft bus Output power P of ground power supply max Judging the current spacecraft ground power supply safety state by the instruction type mark, and outputting a judgment result to the early warning and fault processing module;
the early warning and fault processing module is used for generating early warning and fault processing measures according to the output result of the logic judgment module and sending the fault processing measures to the ground power supply;
and the ground power supply module is used for executing fault processing measures according to the output result of the early warning and fault processing module.
FIG. 2 is a flow chart of a spacecraft ground power supply safety alarm and processing system based on load characteristics. The implementation process of the spacecraft ground power supply safety alarm and processing system based on the load characteristics is described below by taking the embodiment 1 and the embodiment 2 as examples.
Example 1
In this embodiment, the load is expected to have a power P load =150W, redundant power threshold Δ P min ＝100W，ΔP error =10W, upper limit Δ I of light alarm of current jump max1 =15A, upper limit of current jump heavy alarm Δ I max2 =20A, lower bus voltage limit V min =95V, bus voltage upper limit V max ＝105V。
Firstly, a data acquisition module acquires spacecraft bus voltage V bus =100V, spacecraft busbar current I bus =20A, ground power supply output power P max =2200W, the instruction type flag is 1, and the acquired spacecraft bus voltage V is set bus Bus current I of spacecraft bus Ground power supply output power P max And the instruction type mark is output to a logic judgment module;
secondly, the logic judgment module receives the spacecraft bus voltage V bus Bus current I of spacecraft bus Output power P of ground power supply max And judging the current spacecraft ground power supply safety state by the instruction type mark. Calculating the redundant power delta P =50W after the spacecraft executes the load power-on command<ΔP min And generating a bus power supply capacity early warning signal called as a fault signal 2.
Thirdly, the early warning and fault processing module generates early warning and fault processing measures according to the fault signal 2 output by the logic judgment module, sends an instruction to the ground power supply module and adjusts the maximum output power P of the ground power supply module max =2300W, and recording the current moment, the maximum output power and the alarm signal;
fourthly, the ground power supply module adjusts the maximum output power P of the ground power supply module according to the output result of the early warning and fault processing module max ＝2300W。
Fifthly, because the load power-on instruction is not executed yet, the logic judgment module acquires the instruction type mark as 1 again and acquires the spacecraft bus voltage V at the same time bus =100V, spacecraft busbar current I bus =20A, maximum output power P of ground power supply max =2300W, and the collected spacecraft bus voltage V bus Bus current I of spacecraft bus Ground power supply output power P max And the instruction type mark is output to a logic judgment module;
sixthly, the logic judgment module calculates the redundant power delta P =150W after the spacecraft executes the load power-on command>ΔP min The spacecraft executes the load power-up command. Assuming that the spacecraft executes the load power-on instruction, the current I of the bus of the spacecraft is bus When the power becomes 21.7A, the actual power P of the load is load ’ =170W. Therefore, the error power is 20W, which is larger than the upper error limit Δ P error =10W. The logic judgment module generates an alarm signal called fault signal 1 for abnormal health degree of the load electricity utilization.
And seventhly, generating early warning and fault processing measures by the early warning and fault processing module according to the fault signal 1 output by the logic judgment module, and automatically recording the current moment, the load power-on instruction and the alarm signal.
Eighthly, after the spacecraft executes the load power-on instruction, the spacecraft bus current I bus The voltage is changed into 21.7A, and the logic judgment module acquires the spacecraft bus voltage V bus =100V, spacecraft busbar current I bus =21.7A, maximum output power P of ground power supply max =2300W, and collected spacecraft bus voltage V bus Bus current I of spacecraft bus Output power P of ground power supply max And outputting the instruction type mark to a logic judgment module
The ninth step, the logic judgment module calculates the bus current jump value delta I bus ＝1.7A<ΔI max1 =15A, the logic determination module assumes that no processing is required.
Example 2
In this embodiment, the load is expected to have a power P load =150W, redundant power threshold Δ P min ＝100W，ΔP error =10W, upper limit Δ I of light alarm of current jump max1 =15A, upper limit of current jump heavy alarm Δ I max2 =20A, lower bus voltage limit V min =95V, bus voltage upper limit V max ＝105V。
Firstly, a data acquisition module acquires spacecraft bus voltage V bus =90V, spacecraft bus current I bus 20A to 45A, ground power supply output power P max =2200W, the command type flag is 0, and the acquired spacecraft bus voltage V is detected bus Bus current I of spacecraft bus Output power P of ground power supply max And the instruction type mark is output to a logic judgment module;
secondly, the logic judgment module receives the spacecraft bus voltage V bus Bus current I of spacecraft bus Output power P of ground power supply max And judging the current spacecraft ground power supply safety state by the instruction type mark. Calculating the current jump of the busValue Δ I bus ＝25A>ΔI max2 And bus voltage V bus =90V, less than V min If the voltage is not less than 95V, generating a bus short-circuit fault alarm signal called as a fault signal 5;
thirdly, the early warning and fault processing module generates early warning and fault processing measures according to the fault signal 5 output by the logic judgment module, sends an instruction to the spacecraft, disconnects a discharge switch of the storage battery, closes a load, sends an instruction to the ground power supply module, prohibits output, and automatically records the current moment, the bus current jump value, the bus voltage and an alarm signal;
and fourthly, the ground power supply module prohibits output according to the output result of the early warning and fault processing module.
Claims (4)
1. The utility model provides a spacecraft ground power supply safety warning and processing system based on load characteristic which characterized in that comprises data acquisition module, logic judgment module, early warning and fault handling module and ground power module, wherein:
the data acquisition module is used for acquiring spacecraft bus voltage, spacecraft bus current, ground power supply maximum output power and instruction type marks in real time and outputting the marks to the logic judgment module;
the logic judgment module is used for judging the current ground power supply safety state of the spacecraft according to the received data and outputting a judgment result to the early warning and fault processing module; the logic judgment module is used for receiving the spacecraft bus voltage V output by the data acquisition module bus Bus current I of spacecraft bus Maximum output power P of ground power supply max And a command type mark, and according to the received spacecraft bus voltage V bus Bus current I of spacecraft bus Maximum output power P of ground power supply max Judging the current spacecraft ground power supply safety state by the instruction type mark, and outputting a judgment result to the early warning and fault processing module; the method for judging the current ground power supply safety state by the logic judgment module comprises the following steps:
(1) When the instruction type is a load power-up instruction, the load power-up is executed at the spacecraftBefore command, according to load expected power P load Calculating the redundant power delta P after the spacecraft executes the load power-up command;
if the redundant power Δ P is greater than or equal to the redundant power threshold Δ P min The spacecraft executes the load power-up command and calculates the actual load power P load ’ (ii) a If the error power is larger than the error upper limit delta P error If the actual power of the load is inconsistent with the expected power of the load, generating an alarm signal of abnormal health degree of the load electricity consumption, and calling the alarm signal as a fault signal 1; if the error power is not greater than the upper error limit, the actual power of the load is consistent with the expected power of the load, and the load is considered to be healthy in power utilization; the actual load power is the difference between the spacecraft power after the load power-up instruction is executed and the spacecraft power before the load power-up instruction is executed; the error power is the absolute value of the difference between the actual power of the load and the expected power of the load; if the redundant power is smaller than the redundant power threshold, generating a bus power supply capacity early warning signal called as a fault signal 2;
when the instruction type is a non-load power-on instruction, no processing is performed;
(2) Calculating the jump value delta I of the bus current bus Judging the bus current jump value delta I bus Whether the current jump mild alarm upper limit delta I is exceeded max1 (ii) a If the bus current jump value delta I bus The upper limit Delta I of the mild alarm of the current jump is not exceeded max1 If yes, no treatment is carried out; if the bus current jump value delta I bus Exceeding the mild alarm upper limit Delta I of current jump max1 But not exceeding the current jump severity alarm upper limit Delta I max2 Generating a bus current jump mild alarm signal called as a fault signal 3; if the bus current jump value delta I bus Exceeding the current jump severity alarm upper limit Delta I max2 And the current bus voltage V bus Higher than the lower limit V of the bus voltage min Generating a bus current jump severity alarm signal called as a fault signal 4; if the bus current jump value delta I bus Exceeding the current jump severity alarm upper limit Delta I max2 And the current bus voltage is not higher than the lower limit V of the bus voltage min Generating a bus short-circuit fault alarm signal called faultSignal 5; bus current jump value delta I bus The current value of the bus current of the spacecraft is the absolute value of the difference value of the last sampling value;
(3) Judging spacecraft bus voltage V bus Whether it is higher than the upper limit V of the bus voltage max If spacecraft bus voltage V bus Not higher than the upper limit V of bus voltage max No processing is needed; if spacecraft bus voltage V bus Higher than the upper limit V of the bus voltage max Judging the discharge current state of the storage battery; if the battery discharges current I discharge If the voltage is greater than 0, generating a storage battery power supply overvoltage alarm signal which is called a fault signal 6; if the battery discharges current I discharge If the voltage is not greater than 0, generating a ground power supply overvoltage alarm signal called a fault signal 7;
the early warning and fault processing module is used for generating early warning and fault processing measures according to the result output by the logic judgment module and sending the fault processing measures to the ground power supply; the method for generating early warning and fault handling measures by the early warning and fault handling module comprises the following steps:
(1) If the result output by the logic judgment module is an alarm signal with abnormal load electricity utilization health degree, namely a fault signal 1, automatically recording the current moment, a load electricity-up instruction and an alarm signal;
(2) If the result output by the logic judgment module is a bus power supply capacity early warning signal, namely a fault signal 2, sending an instruction to the ground power supply module, gradually increasing the maximum output power of the ground power supply module until the redundant power is greater than a redundant power threshold value, and automatically recording the current time, the maximum output power and an alarm signal;
(3) If the result output by the logic judgment module is a bus current jump mild alarm signal, namely a fault signal 3, automatically recording the current moment, a bus current jump value and an alarm signal;
(4) If the result output by the logic judgment module is a bus current jump heavy alarm signal, namely a fault signal 4, automatically recording the current moment, a bus current jump value and an alarm signal;
(5) If the output result of the logic judgment module is a bus short circuit fault alarm signal, namely a fault signal 5, sending an instruction to the spacecraft, disconnecting a storage battery discharge switch, closing a load, sending an instruction to a ground power supply module, prohibiting output, and automatically recording the current moment, a bus current jump value, bus voltage and an alarm signal;
(6) If the result output by the logic judgment module is a storage battery power supply overvoltage alarm signal, namely a fault signal 6 occurs, an instruction is sent to the spacecraft, a storage battery discharge switch is disconnected, and the current time, the bus voltage and the alarm signal are automatically recorded;
(7) If the result output by the logic judgment module is a ground power supply overvoltage alarm signal, namely a fault signal 7, sending an instruction to a ground power supply module, reducing the output voltage, sending an instruction to a spacecraft, switching on a storage battery discharge switch, then sending an instruction to the ground power supply module, prohibiting output, and automatically recording the current time, the bus voltage and the alarm signal;
and the ground power supply module is used for executing fault processing measures according to the output result of the early warning and fault processing module.
2. A spacecraft ground powered safety alarm and processing system in accordance with claim 1, wherein: the data acquisition module is used for acquiring spacecraft bus voltage V in real time bus Bus current I of spacecraft bus Maximum output power P of ground power supply max Marking the command type and collecting the spacecraft bus voltage V bus Spacecraft bus current I bus The maximum output power P of the ground power supply max And the instruction type mark is output to a logic judgment module; the instruction types are divided into a load power-on instruction and a non-load power-on instruction; when the instruction type is a load power-on instruction, the instruction type mark is 1; when the instruction type is a non-load power-on instruction or a no instruction, the instruction type flag is 0.
3. A spacecraft ground power supply safety alarm and processing system based on load characteristics according to claim 1, characterized in that: and the ground power supply module is used for executing fault processing measures according to the output result of the early warning and fault processing module.
4. A spacecraft ground power supply safety alarm and processing system based on load characteristics is characterized by comprising the following steps:
(1) The data acquisition module acquires spacecraft bus voltage V bus Bus current I of spacecraft bus Maximum output power P of ground power supply max Marking the command type and collecting the spacecraft bus voltage V bus Bus current I of spacecraft bus Maximum output power P of ground power supply max And the instruction type mark is output to a logic judgment module;
(2) The logic judgment module receives the spacecraft bus voltage V bus Bus current I of spacecraft bus Maximum output power P of ground power supply max Judging the current spacecraft ground power supply safety state by the instruction type mark, and outputting a judgment result to the early warning and fault processing module; the method for judging the current ground power supply safety state by the logic judgment module comprises the following steps:
(2-1) when the instruction type is a load power-up instruction, before the spacecraft executes the load power-up instruction, the power P is expected according to the load load Calculating the redundant power delta P after the spacecraft executes the load power-up command;
if the redundant power Δ P is greater than or equal to the redundant power threshold Δ P min The spacecraft executes the load power-up command and calculates the actual load power P load ’ (ii) a If the error power is larger than the error upper limit delta P error If the actual power of the load is inconsistent with the expected power of the load, generating an alarm signal of abnormal health degree of the load electricity consumption, and calling the alarm signal as a fault signal 1; if the error power is not greater than the upper error limit, the actual power of the load is consistent with the expected power of the load, and the load is considered to be healthy in power utilization; the actual load power is the difference between the spacecraft power after the load power-up instruction is executed and the spacecraft power before the load power-up instruction is executed; the error power is the actual power of the load and the expected power of the loadThe absolute value of the difference; if the redundant power is smaller than the redundant power threshold, generating a bus power supply capacity early warning signal called as a fault signal 2;
when the instruction type is a non-load power-on instruction, no processing is performed;
(2-2) calculating a bus current jump value Delta I bus And judging the bus current jump value delta I bus Whether the current jump mild alarm upper limit Delta I is exceeded or not max1 (ii) a If the bus current jump value delta I bus The upper limit Delta I of the mild alarm of the current jump is not exceeded max1 If yes, no treatment is carried out; if the bus current jump value delta I bus Exceeding the upper limit Delta I of the light alarm of current jump max1 But not exceeding the current jump severity alarm upper limit Delta I max2 Generating a bus current jump mild alarm signal called as a fault signal 3; if the bus current jump value delta I bus Exceeding the current jump severity alarm upper limit Delta I max2 And the current bus voltage V bus Higher than the lower limit V of the bus voltage min Generating a bus current jump severity alarm signal called as a fault signal 4; if the bus current jump value delta I bus Exceeding the current jump severity alarm upper limit Delta I max2 And the current bus voltage is not higher than the lower limit V of the bus voltage min Generating a bus short circuit fault alarm signal called as a fault signal 5; bus current jump value delta I bus The current value of the bus current of the spacecraft is the absolute value of the difference value of the last sampling value;
(2-3) judging spacecraft bus voltage V bus Whether it is higher than the upper limit V of the bus voltage max If spacecraft bus voltage V bus Not higher than the upper limit V of bus voltage max Then no processing is needed; if spacecraft bus voltage V bus Higher than the upper limit V of the bus voltage max Judging the discharge current state of the storage battery; if the battery discharges current I discharge If the voltage is greater than 0, generating a storage battery power supply overvoltage alarm signal called as a fault signal 6; if the battery discharges current I discharge If the voltage is not greater than 0, generating a ground power supply overvoltage alarm signal called a fault signal 7;
(3) The early warning and fault processing module generates early warning and fault processing measures according to the output result of the logic judgment module and sends the fault processing measures to the ground power supply module; the method for generating early warning and fault handling measures by the early warning and fault handling module comprises the following steps:
(3-1) if the result output by the logic judgment module is an alarm signal with abnormal load electricity utilization health degree, namely a fault signal 1, automatically recording the current moment, a load power-on instruction and the alarm signal;
(3-2) if the result output by the logic judgment module is a bus power supply capacity early warning signal, namely a fault signal 2, sending an instruction to the ground power supply module, gradually increasing the maximum output power of the ground power supply module until the redundant power is greater than a redundant power threshold value, and automatically recording the current time, the maximum output power and an alarm signal;
(3-3) if the result output by the logic judgment module is a bus current jump mild alarm signal, namely a fault signal 3, automatically recording the current time, a bus current jump value and the alarm signal;
(3-4) if the result output by the logic judgment module is a bus current jump severity alarm signal, namely a fault signal 4, automatically recording the current time, the bus current jump value and the alarm signal;
(3-5) if the result output by the logic judgment module is a bus short circuit fault alarm signal, namely a fault signal 5, sending an instruction to the spacecraft, disconnecting a storage battery discharge switch, closing a load, sending an instruction to a ground power supply module, prohibiting output, and automatically recording the current time, a bus current jump value, a bus voltage and an alarm signal;
(3-6) if the result output by the logic judgment module is a storage battery power supply overvoltage alarm signal, namely a fault signal 6, sending an instruction to the spacecraft, disconnecting a discharge switch of the storage battery, and automatically recording the current moment, the bus voltage and an alarm signal;
(3-7) if the result output by the logic judgment module is a ground power supply overvoltage alarm signal, namely a fault signal 7, sending an instruction to a ground power supply module, reducing the output voltage, sending an instruction to a spacecraft, switching on a storage battery discharge switch, then sending an instruction to the ground power supply module, prohibiting output, and automatically recording the current time, the bus voltage and the alarm signal;
(4) And the ground power supply module executes processing measures according to the output result of the early warning and fault processing module.
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| CN103279077A (en) * | 2013-04-25 | 2013-09-04 | 上海卫星工程研究所 | Ground power supply intelligent control system for satellite electrical test |
| CN109066977A (en) * | 2018-08-08 | 2018-12-21 | 上海宇航系统工程研究所 | A kind of distribution aerospace craft intelligence power supply-distribution system |
| CN109873414A (en) * | 2019-02-21 | 2019-06-11 | 北京空间飞行器总体设计部 | A kind of spacecraft-testing power supply-distribution system health monitoring processing method |
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| CN103279077A (en) * | 2013-04-25 | 2013-09-04 | 上海卫星工程研究所 | Ground power supply intelligent control system for satellite electrical test |
| CN109066977A (en) * | 2018-08-08 | 2018-12-21 | 上海宇航系统工程研究所 | A kind of distribution aerospace craft intelligence power supply-distribution system |
| CN109873414A (en) * | 2019-02-21 | 2019-06-11 | 北京空间飞行器总体设计部 | A kind of spacecraft-testing power supply-distribution system health monitoring processing method |
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