CN108089074A - Spacecraft power supply buses voltage overshoot detection device - Google Patents
Spacecraft power supply buses voltage overshoot detection device Download PDFInfo
- Publication number
- CN108089074A CN108089074A CN201611046499.5A CN201611046499A CN108089074A CN 108089074 A CN108089074 A CN 108089074A CN 201611046499 A CN201611046499 A CN 201611046499A CN 108089074 A CN108089074 A CN 108089074A
- Authority
- CN
- China
- Prior art keywords
- power supply
- spacecraft
- voltage
- supply buses
- detection device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/008—Subject matter not provided for in other groups of this subclass by doing functionality tests
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R19/00—Arrangements for measuring currents or voltages or for indicating presence or sign thereof
- G01R19/25—Arrangements for measuring currents or voltages or for indicating presence or sign thereof using digital measurement techniques
- G01R19/2503—Arrangements for measuring currents or voltages or for indicating presence or sign thereof using digital measurement techniques for measuring voltage only, e.g. digital volt meters (DVM's)
-
- 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
- G01R31/005—Testing of electric installations on transport means
- G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Remote Monitoring And Control Of Power-Distribution Networks (AREA)
Abstract
The present invention provides a kind of spacecraft power supply buses voltage overshoot detection device, for accessing spacecraft, automatic monitoring and the voltage overshoot for the power supply buses for judging spacecraft, including：Front-end detection device, the power supply buses of spacecraft are accessed by accessing cable, for monitoring the power supply buses voltage of spacecraft in real time using voltage comparator circuit and system break trigger mechanism, and the voltage ripple size of power supply buses is monitored using A/D Acquisition Circuits；For receiving and storing the monitoring data of front-end detection device transmission, monitoring terminal is sent to as remote terminal access integration test net, and receives the order of turn-key system by control computer for monitoring data, they are communicated by 422 serial ports of RS.Therefore, the present invention realizes the automatic interpretation of spacecraft power supply buses voltage overshoot problem using the technological means such as automatic monitoring, interpretation and record data, remote control, convenient for test event arrangement and implementation, improves the efficiency and security of test job.
Description
Technical field
The invention belongs to spacecraft-testings and experimental technique field, are related to a kind of spacecraft power supply buses voltage overshoot detection
Device, for accessing spacecraft, monitor automatically and judge the spacecraft power supply buses voltage overshoot.
Background technology
At present, most use of domestic spacecraft power supply subsystem divides three domain of configuration to adjust busbar, system topological principle entirely
As shown in Figure 1.Shunting signal or boost signal are generated according to busbar voltage, by extra windsurfing power dividing or cell voltage liter
Pressure, control bus voltage range usually use VIt is female±VΔIt represents.For example, the satellite generally use busbar voltage in China is 28 ± 1V
Or the complete of 100 ± 3V adjusts busbar.
When windsurfing generates electricity it is sufficient when, power management functions generate shunting signal by extra windsurfing power dividing, by busbar
Voltage control existsWhen windsurfing generating capacity declines, busbar voltage declines therewith, busbar voltage
When, it neither generates shunting signal nor generates boost signal.When busbar voltage drops to
It is less than When, power management functions generate boost signal according to busbar voltage, are sent into pulsewidth modulation integrated chip, into
Entering PWM controller, PWM controller generates control signal, when pwm control signal is more than 1.0V, the production of pulsewidth modulation integrated chip
Raw frequency is fixed, the switching tube for recommending booster circuit that pulsewidth is adjusted according to the adjustable drive signal of signal magnitude, control electric discharge
Break-make so that transformer symmetrical operation, to busbar, control bus voltage exists for output after cell voltage is boosted
Due to being linear relationship between busbar voltage and error signal.When busbar voltage drop is less thanWhen,
Boost signal more than 1.0V is generated according to busbar voltage, since pulsewidth modulation integrated chip periphery capacitance powers on the charging at initial stage
Effect, adjusting the resistance-capacitance circuit of closed loop stability, there are delayed phase characteristics so that boosting is lagged behind in pwm control signal phase
There is response delay, busbar voltage caused to continue to drop, boost signal continues to increase, and pwm control signal continues to increase in control signal
Greatly, busbar voltage starts lifting；When busbar voltage rises toWhen, although boost signal is less than 1.0V, due to
The discharge effect of peripheral capacitance, pwm control signal variation lag behind boost signal, and busbar voltage is still according to the boosting of previous moment
Signal is adjusted, and when the voltage up control signal of previous moment is bigger than normal, (previous moment busbar voltage is relatively low, such as less than When voltage up control signal be more than 3.3V, PWM controller will work with maximum duty cycle, and booster will be most to rise higher
Pressure energy power is boosted), busbar will generate overshoot.Particularly to powerful pulse-type load, enter shadow region from Yang Zhao areas
During, windsurfing output power moment deficiency, busbar voltage rapid decrease, due to prolonging for pwm control signal response can be generated
Late so that pwm control signal is excessive, and busbar voltage is caused to generate the overshoot of bigger.
The correctness of test verification busbar voltage control is needed in spacecraft development process, checks the spacecraft disengaging shadow phase
Between matching from each offline mode (workload is different), especially during highpowerpulse type loaded work piece, check busbar
Voltage controls whether over control occur.
In previous spacecraft model test process, when carrying out busbar voltage control function test job, generally use is such as
Lower test method：Spacecraft power supply buses are led to outside spacecraft using transit cable and interconnecting device, by tester's profit
Busbar voltage overshoot condition is captured from interconnecting device with oscillograph, data and busbar voltage waveform is recorded, while utilizes busbar electricity
Press telemetry parameter auxiliary monitoring busbar voltage overshoot condition (as shown in Figure 2).
However, test method shown in Fig. 2 has the following disadvantages：
1) tester is needed to record test result, complicated for operation during test, this class testing to execute-in-place oscillograph
Project can only arrange to test for special project, it is impossible to be combined with other test events, testing efficiency is low, dumb；
2) spacecraft is generally using wireless test, and activity may to wireless signal transmission around spacecraft by tester
It impacts, while spacecraft ambient electromagnetic radiation is stronger, tester needs to take radiation protection safeguard measure, Security of test
It is poor；
3) since telemetry parameter is discrete magnitude, collection period 500ms, busbar voltage overshoot is generally ms phenomenons, tests
Interpretation personnel check the possibility of busbar voltage overshoot substantially less than centesimal probability using telemetry parameter, therefore busbar
Voltage telemeering parameter auxiliary monitoring busbar voltage overshoot condition can only be a kind of supplementary means, it is difficult to capture abnormal phenomenon；
4) using interconnecting device and the access module of transit cable, test equipment access system test session is more, beam worker
Make and remove receipts heavy workload so that test implementation is relatively complicated.
Therefore, with the development of spacecraft function and application, the load of highpowerpulse type is mating more and more, in spacecraft
It is more and more important for the test job of power supply buses voltage control function during ground test is verified, in order to improve spacecraft
Power supply buses voltage control function test verification work, further improve test convenience and operability, it is necessary to design one
Kind spacecraft power supply buses voltage overshoot detection device, conveniently accessible Space Vehicle System are automatic to monitor and judge that busbar voltage surpasses
Phenomenon is adjusted, and test command system is accessed by data-interface, test case is reported to tester, improves the effect of test implementation
Rate and convenience.
The content of the invention
It controls whether there are problems that operate existing for the test method of overshoot for current spacecraft power supply buses voltage multiple
It is miscellaneous, efficient, it is not convenient, there are limitations such as security risks, the present invention proposes a kind of spacecraft power supply buses voltage overshoot
The solution of detection device, with reference to spacecraft-testing demand, using technological means such as automatic monitoring and judgement, remote controls,
Busbar voltage overshoot monitoring is conveniently and effectively completed, convenient for test event arrangement and implementation, improves the efficiency of test job
And security.
Therefore, the present invention provides a kind of spacecraft power supply buses voltage overshoot detection device, for accessing spacecraft, from
Dynamic monitoring and the voltage overshoot for the power supply buses for judging spacecraft, including：Front-end detection device accesses space flight by accessing cable
The power supply buses of device, for monitoring the power supply buses of spacecraft in real time using voltage comparator circuit and system break trigger mechanism
Voltage, and monitor using A/D Acquisition Circuits the voltage ripple size of power supply buses；And control computer, for receiving simultaneously
The monitoring data that front-end detection device is sent are stored, monitoring data are sent to monitoring as remote terminal access integration test net
Terminal, and the order of turn-key system is received, wherein, front-end detection device and control computer are led to by RS-422 serial ports
Letter.
Preferably, front-end detection device is powered using 28V DC power supplies.
In front-end detection device, when the power supply buses voltage of spacecraft is more than preset value, system break is triggered simultaneously
Generatrix voltage overshoot warning message, while record current time, A/D Acquisition Circuits are adopted with every 2ms sample rates once
Collect the power supply buses voltage of spacecraft, so as to detect the voltage ripple size of power supply buses.
Specifically, front-end detection device is by protection module, voltage comparison module, acquisition module, control module, storage mould
Block, serial communication modular, power module composition, wherein, the software for having front-end detection device is run in control module, is used
In：Control voltage comparison module come in real time monitor spacecraft power supply buses voltage whether overshoot；Control acquisition module come according to
The sample rates of 1ms once gather the power supply buses voltage of spacecraft；And control serial communication modular leads to control computer
Letter, so as to send detection data and receive control command.
Control computer is using PC machine realization and is equipped with serial communication board and network interface card, wherein, in control computer
Software control under, serial communication board communicate with front-end detection device and send control command and reception detect data and
Network interface card and the concurrent censorship measured data of integration test Network Communication and reception control command.
It accesses cable to be used between controller switching equipment and cable, and one point is divided into two using expansion point module therebetween
It is a, wherein, the whereabouts of a point remains unchanged and another point is used for connecting test equipment.
Detection data include at least：Busbar voltage overshoot warning message and power supply buses voltage data.
Therefore, the present invention is changed in spacecraft power supply buses voltage control function test process by manual operation, note
Record, interpretation whether there is the operating mode of busbar voltage overshoot problem, using automatic monitoring, interpretation and record data, long-range control
The technological means such as system, realize the automatic interpretation of spacecraft power supply buses voltage overshoot problem, convenient for test event arrangement and reality
It applies, improves the efficiency and security of test job.
Compared with prior art, following advantageous effect can be realized using the present invention：
1) automatic monitoring, interpretation and the data record of spacecraft busbar voltage overshoot are realized, releases test to people's
Demand optimizes testing process, eliminates personnel to complicated rings such as execute-in-place oscillograph, record test result, artificial interpretations
Section so that the test of spacecraft power supply buses voltage control function can parallel be carried out with other test events, effectively increase survey
The exploitativeness of examination project and flexibility；
2) support tester remote operation control test implementation, solve tester at the scene between wireless test
The contradiction to interact, improves Security of test；
3) monitoring pattern compared in real time using voltage, solving acquisition rate of telemetry parameter 500ms causes exposure to be asked
The low restriction of probability is inscribed, the situation of busbar voltage overshoot can be recorded, and effectively increase the efficiency of test job exposure problem；
4) more convenient access cable design is used, the pattern of transit cable and interconnecting device is substituted, optimizes test and set
Standby access system test session so that test implementation is more convenient.
Description of the drawings
Fig. 1 is the full schematic diagram for adjusting busbar of the prior art；
Fig. 2 is the implementation figure of spacecraft busbar voltage control function test of the prior art；
Fig. 3 is the equipment composition and interface relationship of spacecraft power supply buses voltage overshoot detection device according to the present invention
Schematic diagram；
Fig. 4 is the composition frame chart of front-end detection device；
Fig. 5 is the composition frame chart of control computer；
Fig. 6 is the schematic diagram for accessing cable；
Fig. 7 is the implementation figure of improved spacecraft busbar voltage control test according to the present invention；
Fig. 8 is the schematic diagram of protection module circuit；
Fig. 9 is the circuit diagram of voltage comparison module；
Figure 10 is the circuit diagram of acquisition module；
Figure 11 is the outer circuit diagram between program storage and 8032 of piece；
Figure 12 is the circuit diagram of the outer data storage of piece；
Figure 13 is power supply monitoring and the circuit diagram of house dog；
Figure 14 is the circuit diagram of serial communication modular；
Figure 15 is the main program flow chart of front-end detection device control module software；
Figure 16 is the 0 interrupt service routine flow chart of timer of front-end detection device control module software；
Figure 17 is the 0 interrupt service routine flow chart of external interrupt of front-end detection device control module software；
Figure 18 is the flow chart of control computer software.
Specific embodiment
The present invention is described in detail for 3-18 and specific embodiment below in conjunction with the accompanying drawings.
Spacecraft power supply buses voltage overshoot detection device be used to implement to busbar voltage during integration test whether overshoot
Automatic monitoring and interpretation.As shown in figure 3, spacecraft power supply buses voltage overshoot detection device is by front-end detection device and control
Computer forms, and front-end detection device is powered using 28V DC power supplies, accesses spacecraft power supply buses by accessing cable, adopts
With voltage comparator circuit and system break trigger mechanism, spacecraft power supply buses voltage is monitored in real time, when voltage is more than setting value
When, system break generatrix voltage overshoot warning message is triggered, and records and the moment occurs；Front-end detection device is set simultaneously
A/D Acquisition Circuits gather busbar voltage, for monitoring busbar voltage ripple size with the sample rates of every 2ms once；Front-end detection
Device and control computer are communicated by RS-422 serial ports, and front-end detection device is surpassed busbar voltage by RS-422 serial ports
The detection such as warning message, busbar voltage data data is adjusted to be sent to control computer；Control computer is responsible for before receiving and storing
The detection data that end detecting device is sent, while integration test net is accessed as remote terminal, detection data are sent to test hilllock
Monitoring terminal used in the personnel of position, and receive turn-key system order.Specific equipment composition and interface relationship are as shown in Figure 3.
As shown in figure 4, front-end detection device is by protection module, voltage comparison module, acquisition module, control module, storage
Module, serial communication modular, power module composition.Front-end detection device software is run in control module, for controlling voltage
Comparison module monitor in real time busbar voltage whether overshoot；For acquisition module to be controlled to gather busbar according to the sample rates of 1ms once
Voltage；For serial communication modular to be controlled to communicate with control computer, send detection data and receives control command.
As shown in figure 5, control computer is realized using PC machine, installation serial communication board, network interface card.It is soft in control computer
Under the control of part, control serial communication board communicates with front-end detection device, sends control command and receives detection data；Control
Network interface card and test Network Communication, send detection data and receive control command.
28V DC power supplies purchase DC power supply using commercialization.
As shown in fig. 6, access cable is used between controller switching equipment and cable, it will using expansion point module among access cable
Point remains unchanged for 1 minute for 2,1 whereabouts, and 1 is used to connect test equipment.
Fig. 7 is to carry out the test of spacecraft busbar voltage control function based on spacecraft power supply buses voltage overshoot detection device
Implementation figure.Wherein, spacecraft power supply buses voltage overshoot detection device using the present invention is as solution, with reference to space flight
Device testing requirement using technological means such as automatic monitoring and judgement, remote controls, conveniently and effectively completes busbar voltage overshoot
Monitoring convenient for test event arrangement and implementation, improves the efficiency and security of test job.
As shown in figure 8, in the inlet of front-end detection device, the i.e. positive and negative end entrance of spacecraft power supply buses, protection is set
Modular circuit is made of diode and fuse.
Wherein, diode D1 plays the role of insulation blocking, prevents front-end detection device builtin voltage from sealing in spacecraft power supply
Busbar causes failure.D1 models should select to determine according to spacecraft power supply buses voltage, to 100V power supply buses, may be selected
1N5806。
Fuse F1, F2 play the role of short-circuit protection, prevent front-end detection device internal short circuit fault, spacecraft is caused to supply
Electric bus-bar fault.F1, F2 model should select to determine according to spacecraft power supply buses voltage, to 100V power supply buses, may be selected
MGA-S-125V-0.26A。
The schematic diagram of voltage comparison module circuit is as shown in Figure 9.The in-phase end of comparator LM193 meets the+5V of AD586 outputs
Benchmark, spacecraft power supply buses output voltage connect the end of oppisite phase of comparator by electric resistance partial pressure.The low side electricity of output voltage detection
Resistance is considered as taking Parallel Design, prevents from when 1 resistive-open fails LM193 being caused to act.Under normal circumstances, comparator is anti-
Phase terminal voltage is less than in-phase end voltage, and comparator output is that (supply voltage is+12V to high level, and high level is electric by pull-up resistor
Pressure is more than 10V), when spacecraft power supply buses output voltage is more than setting value, comparator output becomes low level (low level electricity
Pressure is less than 1V), comparator output trailing edge, access control module interrupts system, works as interrupt signal trigger control module.
The schematic diagram of acquisition module circuit is as shown in Figure 10.Through amplifier AD620 by 0~5V's after power supply buses voltage
Analog voltage send 12 analog-digital converter ADC574 after being enlarged into the voltage of 0~10V.It is controlled by the signal of the A0 of ADC574,
Transformed 12-bit data are read at twice.
Control module uses 80C32 chips, the clock oscillation circuit of 12M is set, using program storage, 8K pieces outside 8K pieces
Outer data storage, and design configurations power supply monitoring and watchdog circuit.The outer program storage of 8K pieces uses UT28F64T-
35PCC chips, circuit diagram are as shown in figure 11.
With microcontrollerChip gating of the signal as control sheet external expansion program storageSignal.With
MicrocontrollerSignal is enabled as the data output of control sheet external expansion program storageSignal.When microcontroller powers on
During reset, during microcontroller reading program memory data, microcontrollerIt exports as low level, at this point, program storage data are defeated
Go out enabledSignal is effective, and the data that microcontroller is read are the data of program storage storage.
The outer data storage of 8K pieces uses KW064RH chips, and circuit diagram is as shown in figure 12.The CS2 of data storage
Signal sets permanent for height.With microcontrollerRead gate and write strobe signals of the signal as the outer data storage of piece.
When microcontroller needs to read and write data storage outside piece, pass throughIt is strobed it.
Power supply monitoring and watchdog circuit use MAX706M chips, and circuit diagram is as shown in figure 13.Electric source monitoring circuit
For triggering level near 4.4V, trigger is level triggering mode, and system is resetted when power supply is too low,Export low level width
It is automatic after power up is normal to terminate reset signal output for 140~280ms.The house dog time be 1.6s, watchdog reset
(CLRDOG) signal periodically removes electric source monitoring circuit reset signal.Manual reset switch J1, hand-reset as needed are set
System.J2 switches sting signal for controlling whether to introduce house dog dog, and software debugging is carried out for coordinating.J2 is opened when product is delivered
It closes in closure state.
Serial communication modular uses MAX1490 devices, and circuit diagram is as shown in figure 14.
Next, it will be described in detail the software flow of the control module of front-end detection device.
It will be appreciated that front-end detection device control module software flow includes main program flow, 0 interrupt service routine of timer
0 interrupt service routine flow of flow and external interrupt, specifically as shown in Figure 15, Figure 16, Figure 17.
For front-end detection device under the control of control module software, the course of work is as follows：
Main program flow initialization system is carried out first, is led to including data acquisition channel, timer 0, external interrupt, serial ports
The initial works such as letter, message format area variable, wherein timer 0 are initialized as the pattern that 2ms triggers an Interruption, outside
Portion interrupts 0 and is arranged to trailing edge triggering interrupt mode, and serial communication rate is arranged to 19.2kbps；Then it is open to interrupt, then
Main program enters idle loop standby mode；
Voltage acquisition function is realized using 0 interrupt service routine of timer, using 1ms as the cycle, after open interrupt, every
1ms, main program are interrupted into a timer 0 and interrupt, into interruption after gather primary voltage data first, then by this electricity
Pressure data insert message buffer, and (message buffer data sending to control computer is noticed the transmission phase followed by serial ports
Between should close interruption), interruption is exited, into main program idle loop standby mode；
Voltage overshoot monitoring function is realized using 0 interrupt service routine of external interrupt, after open interrupt, when there is busbar
Voltage overshoot triggers voltage comparison module to become low level (low level voltage is less than 1V), when exporting trailing edge, triggers in outside
Disconnected 0, it interrupts main program or 0 interrupt service routine of timer performs, into 0 interrupt service routine of external interrupt, voltage transfinites meter
After number variable adds 1, voltage is transfinited and counts write-in message buffer, exits interruption.
Control computer hardware is intended using business computer (containing Ethernet card), RS422 boards (pci interface) configuration, control
Computer processed is communicated by RS422 serial ports with front-end detection device, realizes the acquisition of voltage acquisition and voltage overshoot monitoring data
And store function；Control computer is communicated by Ethernet with monitoring terminal, and voltage acquisition and voltage overshoot monitoring data are sent
Monitoring terminal is shown, for judging personnel's remotely monitor interpretation.
The software flow of control computer is as shown in figure 18.Control computer software initialization RS422 boards, utilize board
Buffering area can receive all data that at least 1s Inner Front Ends detection device is sent, and software sets timer, and one is entered per 500ms
Secondary cycling, Xun Huan start to read all data of front-end detection device transmission from RS422 boards buffering area first, carry out data inspection
It is being locally stored after looking into, being then sent to monitoring terminal by network shows for tester's interpretation, is looked into after data sending success
The order that " stopping detection " whether is received by network is ask, receives, exits, otherwise enters and cycles next time.
In conclusion by the present invention, change and people is relied in spacecraft power supply buses voltage control function test process
Work is operated, recorded, interpretation is with the presence or absence of the operating mode of busbar voltage overshoot problem, using automatic monitoring, interpretation and records number
According to technological means such as, remote controls, the automatic interpretation of spacecraft power supply buses voltage overshoot problem is realized, convenient for test event
It arranges and implements, improve the efficiency and security of test job.
It is not specified in the present invention and partly belongs to techniques known.
Claims (7)
1. a kind of spacecraft power supply buses voltage overshoot detection device for accessing spacecraft, monitors and judges the boat automatically
The voltage overshoot of the power supply buses of its device, which is characterized in that including：
Front-end detection device accesses the power supply buses of the spacecraft by accessing cable, for using voltage comparator circuit and
System break trigger mechanism monitors the power supply buses voltage of the spacecraft in real time, and using A/D Acquisition Circuits to monitor
State the voltage ripple size of power supply buses；And
Control computer for receiving and storing the monitoring data that the front-end detection device is sent, is accessed as remote terminal
The monitoring data are sent to monitoring terminal by integration test net, and receive the order of turn-key system,
Wherein, the front-end detection device and the control computer are communicated by RS-422 serial ports.
2. spacecraft power supply buses voltage overshoot detection device according to claim 1, which is characterized in that the front end inspection
Device is surveyed to power using 28V DC power supplies.
3. spacecraft power supply buses voltage overshoot detection device according to claim 2, which is characterized in that in the front end
In detection device,
When the power supply buses voltage of the spacecraft is more than preset value, system break is triggered and generatrix voltage overshoot report
Alert information, while current time is recorded,
The A/D Acquisition Circuits gather the power supply buses voltage of the spacecraft with every 2ms sample rates once, so as to detect
The voltage ripple size of the power supply buses.
4. spacecraft power supply buses voltage overshoot detection device according to claim 3, which is characterized in that the front end inspection
Device is surveyed by protection module, voltage comparison module, acquisition module, control module, memory module, serial communication modular, power supply mould
Block forms,
Wherein, the software for having the front-end detection device is run on the control module, is used for：
Control the voltage comparison module monitor in real time the power supply buses voltage of the spacecraft whether overshoot；
The acquisition module is controlled to gather the power supply buses voltage of the spacecraft according to 1ms sample rates once；And
The serial communication modular is controlled to communicate with the control computer, so as to send the detection data and receive control life
Order.
5. spacecraft power supply buses voltage overshoot detection device according to claim 1, which is characterized in that the control meter
Calculation machine is using PC machine realization and is equipped with serial communication board and network interface card,
Wherein, under the software control of the control computer, the serial communication board communicates with the front-end detection device
And it sends control command and receives the detection data and the network interface card and the integration test Network Communication and send the inspection
Measured data and the reception control command.
6. spacecraft power supply buses voltage overshoot detection device according to claim 1, which is characterized in that the access electricity
Cable is used between the controller switching equipment and cable, and one point is divided into two points using expansion point module therebetween, wherein,
The whereabouts of one point remains unchanged and another point is used for connecting test equipment.
7. spacecraft power supply buses voltage overshoot detection device according to any one of the preceding claims, feature exist
In the detection data include at least：The busbar voltage overshoot warning message and the power supply buses voltage data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611046499.5A CN108089074A (en) | 2016-11-23 | 2016-11-23 | Spacecraft power supply buses voltage overshoot detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611046499.5A CN108089074A (en) | 2016-11-23 | 2016-11-23 | Spacecraft power supply buses voltage overshoot detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108089074A true CN108089074A (en) | 2018-05-29 |
Family
ID=62171103
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611046499.5A Pending CN108089074A (en) | 2016-11-23 | 2016-11-23 | Spacecraft power supply buses voltage overshoot detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108089074A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070143048A1 (en) * | 2005-12-02 | 2007-06-21 | Semiconductor Energy Laboratory Co., Ltd. | Test method of microsctructure body and micromachine |
| KR100812183B1 (en) * | 2006-09-18 | 2008-03-12 | (주)그린텍시스템 | An apparatus for monitoring bus bar of power supply facility |
| CN101316050A (en) * | 2007-12-26 | 2008-12-03 | 上海市电力公司超高压输变电公司 | Method and device for monitoring running state of transforming station direct current system |
| CN101950002A (en) * | 2010-08-13 | 2011-01-19 | 航天东方红卫星有限公司 | Comprehensive test method of small satellite power subsystem |
| CN102681529A (en) * | 2012-04-23 | 2012-09-19 | 北京空间飞行器总体设计部 | Spacecraft autonomous delay telemetering method adapted to parameter characteristics |
| CN202929094U (en) * | 2012-10-23 | 2013-05-08 | 云南电网公司楚雄供电局 | Overvoltage online monitoring system for electric grid |
| CN104297699A (en) * | 2014-09-26 | 2015-01-21 | 航天东方红卫星有限公司 | Satellite power supply health condition tracking and detecting method based on intelligent interpretation |
| CN104753124A (en) * | 2014-12-11 | 2015-07-01 | 北京空间飞行器总体设计部 | Simulation system for S4R power supply controller of spacecraft |
-
2016
- 2016-11-23 CN CN201611046499.5A patent/CN108089074A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070143048A1 (en) * | 2005-12-02 | 2007-06-21 | Semiconductor Energy Laboratory Co., Ltd. | Test method of microsctructure body and micromachine |
| KR100812183B1 (en) * | 2006-09-18 | 2008-03-12 | (주)그린텍시스템 | An apparatus for monitoring bus bar of power supply facility |
| CN101316050A (en) * | 2007-12-26 | 2008-12-03 | 上海市电力公司超高压输变电公司 | Method and device for monitoring running state of transforming station direct current system |
| CN101950002A (en) * | 2010-08-13 | 2011-01-19 | 航天东方红卫星有限公司 | Comprehensive test method of small satellite power subsystem |
| CN102681529A (en) * | 2012-04-23 | 2012-09-19 | 北京空间飞行器总体设计部 | Spacecraft autonomous delay telemetering method adapted to parameter characteristics |
| CN202929094U (en) * | 2012-10-23 | 2013-05-08 | 云南电网公司楚雄供电局 | Overvoltage online monitoring system for electric grid |
| CN104297699A (en) * | 2014-09-26 | 2015-01-21 | 航天东方红卫星有限公司 | Satellite power supply health condition tracking and detecting method based on intelligent interpretation |
| CN104753124A (en) * | 2014-12-11 | 2015-07-01 | 北京空间飞行器总体设计部 | Simulation system for S4R power supply controller of spacecraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105468127B (en) | A kind of real-time data acquisition system and its power failure data storage circuit, method | |
| CN103513650B (en) | The record ripple control method of converter valve opertaing device | |
| CN108332060B (en) | Intelligent monitoring system for pipeline water leakage | |
| CN211208607U (en) | Monitoring device for battery management system and battery management system | |
| CN109031131B (en) | The real-time host system of the heterogeneous polynuclear of battery testing and analog meter and method | |
| KR102013413B1 (en) | HILS development system of ESS and operation method of ESS using the same | |
| CN107359676A (en) | A kind of online charge and discharge control of battery and capacity check system and method | |
| CN2562195Y (en) | Anomalous running measuring and recording instrument for intellectual network kilowatt meter | |
| CN105501455B (en) | A kind of unmanned aerial vehicle comprehensive power integrated system and method | |
| CN101119085A (en) | PWM solar power control module of PWM solar controller | |
| CN109582498A (en) | Data protection circuit and guard method when a kind of CPLD powered-off fault | |
| CN105371969A (en) | Track plate temperature remote monitoring system | |
| CN109065975A (en) | A kind of direct current system management system and its control method | |
| CN110597376B (en) | Sequencing circuit and sequencing system | |
| CN108089074A (en) | Spacecraft power supply buses voltage overshoot detection device | |
| CN107506281A (en) | A kind of multiple power supplies monitoring system and method | |
| JPH0622473A (en) | Uninterruptible power source | |
| CN203352229U (en) | Lead-acid battery intelligent activation device | |
| CN201111167Y (en) | Battery state data record device | |
| CN202904758U (en) | Power-down data protection device for fiscal cash register | |
| CN109450309A (en) | A kind of anti-bat conjunction method based on aviation power system engine controller | |
| CN114865770A (en) | Centralized UPS power supply system for rail transit | |
| CN107104506A (en) | A kind of emergency power generation automatic switching system | |
| CN114094658A (en) | All-solid-state power supply and distribution method and device with load characteristic measurement function | |
| CN209373072U (en) | Aviation alkaline storage battery charge and discharge analyzer |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180529 |