CN107908177B - Method for identifying working state of satellite power supply controller - Google Patents
Method for identifying working state of satellite power supply controller Download PDFInfo
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- CN107908177B CN107908177B CN201711157631.4A CN201711157631A CN107908177B CN 107908177 B CN107908177 B CN 107908177B CN 201711157631 A CN201711157631 A CN 201711157631A CN 107908177 B CN107908177 B CN 107908177B
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/28—Testing of electronic circuits, e.g. by signal tracer
- G01R31/282—Testing of electronic circuits specially adapted for particular applications not provided for elsewhere
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- Automation & Control Theory (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Voltage And Current In General (AREA)
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Abstract
A satellite power supply controller working state identification method compares a bus MEA value of a satellite power supply controller with a reference voltage of each branch circuit in the satellite power supply controller, and judges the working state of each branch circuit; if the bus MEA is less than or equal to the lower voltage limit of a certain branch circuit, the branch circuit is in a full-off state; if the bus MEA is more than or equal to the upper voltage limit of a certain shunt circuit, the shunt circuit is in a full working state; if the lower voltage limit of a certain shunt circuit < the bus MEA < the upper voltage limit of the certain shunt circuit, the shunt circuit is in a modulation working state. According to the invention, through reading the existing parameters of the satellite power controller, the fault and the state of the satellite power controller in operation can be rapidly identified without designing an additional sampling circuit, and the circuit design complexity of the satellite power controller can be effectively reduced.
Description
Technical Field
The invention relates to a method for identifying the working state of a satellite power supply controller.
Background
The satellite power supply control system is an important component of the satellite system, and the running state of the satellite power supply control system is one of important indexes for normal running of the satellite. At present, the running state of a satellite power supply control system is judged by acquiring a plurality of telemetering parameters, because the internal circuit structure of the control system is complex, the number of circuit components is large, the running state of the controller is identified by reading the output of each circuit through telemetering, not only are a plurality of output parameters large, but also the circuit complexity and the design difficulty of the system are increased, and the weight of the controller is increased.
Disclosure of Invention
The invention provides a method for identifying the working state of a satellite power supply controller, which can quickly identify the fault and the state of the satellite power supply controller in operation by reading the existing parameters of the satellite power supply controller without designing an additional sampling circuit, and can effectively reduce the circuit design complexity of the satellite power supply controller.
In order to achieve the above object, the present invention provides a method for identifying a working state of a satellite power controller, comprising the steps of:
comparing the bus MEA value of the satellite power supply controller with the reference voltage of each branch circuit in the satellite power supply controller, and judging the working state of each branch circuit;
if the bus MEA is less than or equal to the lower voltage limit of a certain branch circuit, the branch circuit is in a full-off state;
if the bus MEA is more than or equal to the upper voltage limit of a certain shunt circuit, the shunt circuit is in a full working state;
if the lower voltage limit of a certain shunt circuit < the bus MEA < the upper voltage limit of the certain shunt circuit, the shunt circuit is in a modulation working state.
And detecting and acquiring a bus MEA value from an output bus of the satellite power controller.
And detecting and obtaining a bus MEA (MEA) from an output bus of the satellite power controller by using a voltage sampling conditioning circuit.
And comparing the reference voltage of the bus MEA and each branch circuit by adopting a differential amplifying circuit.
A reference voltage source is used to provide a reference voltage for each of the shunt circuits.
And further judging the working state of the satellite power supply controller according to the working state of each branch circuit, wherein if the satellite power supply controller has one branch circuit and only one branch circuit is in a modulation working state, the satellite power supply controller is in a normal working state.
And if no shunt circuit is in the modulation working state or the number of the shunt circuits in the modulation working state is more than 1, the satellite power supply controller is in a fault state.
According to the invention, through reading the existing parameters of the satellite power controller, the fault and the state of the satellite power controller in operation can be rapidly identified without designing an additional sampling circuit, the circuit design complexity of the satellite power controller can be effectively reduced, and the method is suitable for identifying the working state of the satellite power controller circuit, especially for identifying the working state of the satellite power controller circuit outputting stable bus voltage.
Drawings
Fig. 1 is a circuit diagram of a shunt circuit inside a satellite power supply controller.
Fig. 2 is a schematic diagram of a method for identifying an operating state of a satellite power controller according to the present invention.
Detailed Description
The preferred embodiment of the present invention will be described in detail below with reference to fig. 1 and 2.
As shown in fig. 1, the satellite power supply controller is internally provided with n branch circuits, each branch circuit is respectively connected with a power input, the power input can be a solar array input or a storage battery input, and bus outputs of all the branch circuits are summarized into a bus output of the satellite power supply controller.
The method comprises the following steps of obtaining bus MEA parameters of a satellite power supply controller by using a voltage sampling conditioning circuit, wherein the bus MEA is used for bus output end error amplification, for example: the designed bus voltage value is 30v, the actual bus voltage value is 31v, the error is amplified by ten times, and the bus MEA is 10 v.
Each shunt circuit has two reference voltages, one lower voltage limit and one upper voltage limit, and if the bus MEA is greater than the lower voltage limit of the shunt circuit, the shunt circuit is turned on and shunts the bus output power.
Taking the 1 st shunt circuit as an example for explanation, the reference voltage 11 is the lower voltage limit of the 1 st shunt circuit, the reference voltage 12 is the upper voltage limit of the 1 st shunt circuit, if the bus MEA is less than the reference voltage 11, the triode T1 is turned off, the 1 st shunt circuit does not work, and the 1 st shunt bus has no power output; if the bus MEA is greater than the reference voltage 11 and less than the reference voltage 12, the triode T1 is partially conducted, the emitter of the triode T1 outputs a switch control signal G1, the MOS tube M1 is conducted, and the 1 st branch bus outputs power; if the bus MEA is larger than the reference voltage 12, the triode T1 is completely conducted, the emitter of the triode T1 outputs a switch control signal G1, the MOS tube M1 is conducted, and the 1 st branch bus outputs power.
Differential amplifier X1 is used to compare the bus MEA to the reference voltages 11 and 12 and generate a drive signal to the base of transistor T1.
The circuit shunting principle of the satellite power supply controller is that a reference voltage shunt circuit is set, the reference voltage 11 of a 1 st shunt circuit is 0V, the reference voltage 12 is 1V, and when a bus MEA is larger than 0V and does not exceed 1V, the 1 st shunt circuit is in a modulation working state; similarly, the reference voltage 21 of the 2 nd shunt circuit is 1V, the reference voltage 22 is 2V, when the bus MEA is greater than 1V and does not exceed 2V, the 1 st shunt circuit is fully operated, and the 2 nd shunt circuit is in a modulation operation state; similarly, the reference voltage 31 of the 3 rd branch circuit is 2V, the reference voltage 32 is 3V, and when the bus MEA is greater than 2V and does not exceed 3V, the 1 st branch circuit is fully operated, the 2 nd branch circuit is fully operated, and the 3 rd branch circuit is in the modulation operation state.
The full working state is as follows: for one circuit, the circuit is completely unscrewed from a faucet, and the circuit works fully when water is at the maximum; the fully off state is: completely screwing off, and turning off when one drop does not flow; the modulation working state is as follows: half-on, running water but not fully on, is a modulated state. Only one of the multi-path circuit branches of the satellite power supply controller is allowed to work in a modulation working state, namely the branch circuit is not completely turned off or is not completely turned on, and the rest branch circuits are either completely worked or completely turned off.
Based on the principle, the fault and the working state of the satellite power controller can be identified by measuring the bus MEA value of the satellite power controller.
The invention provides a method for identifying the working state of a satellite power supply controller, which comprises the following steps:
step S1, detecting and acquiring a bus MEA value of the satellite power supply controller;
step S2, comparing the bus MEA value with the reference voltage of each branch circuit, and judging the working state of each branch circuit;
if the bus MEA is less than or equal to the lower voltage limit of the shunt circuit, the shunt circuit is in a full-off state;
if the bus MEA is larger than or equal to the upper voltage limit of the shunt circuit, the shunt circuit is in a full working state;
if the lower voltage limit of the shunt circuit < the busbar MEA < the upper voltage limit of the shunt circuit, the shunt circuit is in a modulation working state;
step S3, judging the working state of the satellite power supply controller according to the working state of each branch circuit;
if only one branch circuit is in the modulation working state, the satellite power supply controller is in the normal working state;
and if no shunt circuit is in the modulation working state or the number of the shunt circuits in the modulation working state is more than 1, the satellite power supply controller is in a fault state.
Preferably, a voltage sampling conditioning circuit can be adopted to detect and obtain the bus MEA from the output bus of the satellite power supply controller. The comparison of the reference voltage of the bus MEA with the reference voltage of each shunt circuit can be realized by using a differential amplification circuit. A reference voltage source may be used to provide a reference voltage for each of the shunt circuits.
As shown in fig. 2, in an embodiment of the invention, the satellite power controller is divided into 10 branch circuits, the reference voltage of the 1 st branch circuit is 0V to 1V, the reference voltage of the 2 nd branch circuit is 1V to 2V, the reference voltage of the 3 rd branch circuit is 2V to 3V, the reference voltage of the 4 th branch circuit is 3V to 4V, the reference voltage of the 5 th branch circuit is 4V to 5V, the reference voltage of the 6 th branch circuit is 5V to 6V, the reference voltage of the 7 th branch circuit is 6V to 7V, the reference voltage of the 8 th branch circuit is 7V to 8V, the reference voltage of the 9 th branch circuit is 8V to 9V, and the reference voltage of the 10 th branch circuit is 9V to 10V. The detected bus MEA is 2.8V, the bus MEA is larger than the upper voltage limit of the 1 st shunt circuit and the upper voltage limit of the 2 nd shunt circuit, so the 1 st shunt circuit and the 2 nd shunt circuit are in a full-operation state, the bus MEA is larger than the lower voltage limit of the 3 rd shunt circuit and is smaller than the upper voltage limit of the 3 rd shunt circuit, so the 3 rd shunt circuit is in a modulation operation state, the bus MEA is smaller than the lower voltage limits of the 4 th to 10 th shunt circuits, and the 4 th to 10 th shunt circuits are in a full-off state. Because only one branch circuit in the whole satellite power supply controller is in a modulation working state, the current working state of the satellite power supply controller can be judged to be normal.
According to the invention, through reading the existing parameters of the satellite power controller, the fault and the state of the satellite power controller in operation can be rapidly identified without designing an additional sampling circuit, the circuit design complexity of the satellite power controller can be effectively reduced, and the method is suitable for identifying the working state of the satellite power controller circuit, especially for identifying the working state of the satellite power controller circuit outputting stable bus voltage.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.
Claims (7)
1. A method for identifying the working state of a satellite power supply controller is characterized by comprising the following steps:
comparing the bus MEA value of the satellite power supply controller with the reference voltage of each branch circuit in the satellite power supply controller, and judging the working state of each branch circuit;
if the bus MEA is less than or equal to the lower voltage limit of a certain branch circuit, the branch circuit is in a full-off state;
if the bus MEA is more than or equal to the upper voltage limit of a certain shunt circuit, the shunt circuit is in a full working state;
if the lower voltage limit of a certain shunt circuit < the bus MEA < the upper voltage limit of the certain shunt circuit, the shunt circuit is in a modulation working state.
2. The method according to claim 1, wherein the bus MEA value is detected and obtained from an output bus of the satellite power controller.
3. The method for identifying the operating condition of the satellite power controller according to claim 2, wherein a voltage sampling conditioning circuit is used to detect and obtain a bus MEA from an output bus of the satellite power controller.
4. The method according to claim 1, wherein the comparing of the reference voltage of the bus MEA and each of the shunt circuits is performed by using a differential amplifier circuit.
5. The method of claim 1, wherein the reference voltage source is used to provide the reference voltage for each of the shunt circuits.
6. The method according to claim 1, wherein the operating state of the satellite power controller is further determined according to the operating state of each of the branch circuits, and if there is one branch circuit and only one branch circuit is in the modulation operating state, the satellite power controller is in the normal operating state.
7. The method according to claim 6, wherein the satellite power controller is in a fault state if no shunt circuit is in the modulation operation state or the number of shunt circuits in the modulation operation state is greater than 1.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711157631.4A CN107908177B (en) | 2017-11-20 | 2017-11-20 | Method for identifying working state of satellite power supply controller |
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| CN201711157631.4A CN107908177B (en) | 2017-11-20 | 2017-11-20 | Method for identifying working state of satellite power supply controller |
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| CN107908177A CN107908177A (en) | 2018-04-13 |
| CN107908177B true CN107908177B (en) | 2020-08-07 |
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| CN110297478A (en) * | 2019-05-07 | 2019-10-01 | 深圳航天科技创新研究院 | Satellite power supply controller, testability verification method and testability verification platform |
| CN113507100A (en) * | 2021-06-09 | 2021-10-15 | 上海空间电源研究所 | Bus overvoltage protection control system of spacecraft power supply system |
| CN114325198B (en) * | 2021-12-29 | 2023-05-02 | 浙江时空道宇科技有限公司 | Testing device and testing system |
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| FR2824203B1 (en) * | 2001-04-27 | 2003-06-13 | Agence Spatiale Europeenne | POWER SUPPLY CONVERTER |
| JP2009099311A (en) * | 2007-10-15 | 2009-05-07 | Equos Research Co Ltd | Fuel cell stack |
| CN102324583B (en) * | 2011-09-01 | 2014-01-15 | 航天东方红卫星有限公司 | Lithium ion storage battery charging method based on sequential shunt switching regulation (S3R) |
| CN103236731B (en) * | 2013-05-03 | 2015-04-29 | 深圳市航天新源科技有限公司 | Power supply controller framework based on separated charge and control method thereof |
| CN104269915B (en) * | 2014-10-20 | 2017-02-15 | 上海空间电源研究所 | Multi-solar-array unified regulation and control method |
| CN104410038B (en) * | 2014-10-21 | 2017-09-29 | 上海空间电源研究所 | One kind electric discharge regulation circuit overvoltage crowbar |
| CN104993693B (en) * | 2015-06-26 | 2017-07-18 | 深圳市航天新源科技有限公司 | A kind of voltage source transconductance mode controls circuit |
| CN105610305B (en) * | 2015-12-30 | 2019-03-26 | 中国电子科技集团公司第十八研究所 | Satellite vapour image parallel regulator current limliting power-supplying circuit |
| CN106410936B (en) * | 2016-08-31 | 2018-08-31 | 航天东方红卫星有限公司 | A kind of large power high efficiency satellite power system based on high-low pressure double-bus |
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