CN107546725A - A kind of spacecraft discharge circuit overvoltage protective system - Google Patents
A kind of spacecraft discharge circuit overvoltage protective system Download PDFInfo
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- CN107546725A CN107546725A CN201710689538.1A CN201710689538A CN107546725A CN 107546725 A CN107546725 A CN 107546725A CN 201710689538 A CN201710689538 A CN 201710689538A CN 107546725 A CN107546725 A CN 107546725A
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Abstract
The present invention provides a kind of spacecraft discharge circuit overvoltage protective system, including busbar voltage sample circuit, bus overvoltage delay trigger circuit, signal lock circuit, autonomous reset circuit and the execution circuit being connected respectively with discharge circuit；When the execution circuit receives the high level of the trigger output, the discharge circuit loop of power circuit and signal control circuit are cut off.Spacecraft provided by the invention discharge circuit overvoltage protective system, simple equipments, practicality are high, and overcoming existing discharge circuit can not automatically recover, cross the problem of pressure point sets difficult and response speed slow, improve the reliability and security of discharge circuit.
Description
Technical field
The present invention relates to circuit overvoltage protection field, more particularly to a kind of spacecraft discharge circuit overvoltage protective system.
Background technology
Spacecraft is a kind of DC/DC translation circuits with electric discharge regulation circuit, by the energy of batteries by conversion, output
It is adapted to the voltage source of spacecraft demand, is part important in spacecraft power supply subsystem.According to spacecraft energy demand
With reliability design requirement, discharge circuit is typically using mode of operation (the multipath hot backup work of multichannel regulation circuit in parallel output
Operation mode).Due to device in discharge circuit after the electronic environment (single-particle overturns control chip) of spatial complex or operation for many years
Functional deterioration, certain road electric discharge regulation circuit occur output overvoltage failure, such as cut off the faulty circuit not in time, whole piece can be caused female
Line output overvoltage, secondary damage is caused to spacecraft rear class electrical equipment, therefore multichannel electric discharge adjusts setting for circuit in parallel power supply
Need to design overvoltage crowbar in meter.
The overvoltage crowbar of the regulation circuit of spacecraft electric discharge at present, is directly entered using single channel output voltage with reference voltage
Three shortcomings be present in the working method that row compares, this mode：First, there is high energy particle and overturn control in the electronic environment of spatial complex
Coremaking piece, cause electric discharge regulation circuit busbar electric voltage over press concussion, overvoltage protection locking electric discharge regulation circuit, power supply is exited on the road
No longer recover, need ground artificial intervention to recover normal work；Second, pressure point is difficult sets, set too high can be adjusted to electric discharge
Circuit rear class power unit impacts, and crosses pressure point and sets the too low malfunction for easily causing overvoltage crowbar；Third, overvoltage
Protect response speed slow, before faulty circuit is introduced into overvoltage protection state, have been enter into excessively stream or current limliting mode of operation, make electric discharge
Adjust the overvoltage protection failure of circuit.
The content of the invention
It is an object of the invention to provide a kind of spacecraft discharge circuit overvoltage protective system, to solve existing electric discharge
Regulation circuit can not automatically recover, cross the problem of pressure point sets difficult and response speed slow.
In order to solve the above-mentioned technical problem, the technical scheme is that：A kind of spacecraft discharge circuit overvoltage is provided
Protection system, including busbar voltage sample circuit, bus overvoltage triggers circuit, the semaphore lock electricity being connected respectively with discharge circuit
Road, the autonomous reset circuit of delay and execution circuit；
The busbar voltage sample circuit includes sampling resistor network and voltage follower；The sampling resistor network is by mother
Line voltage is scaled 1/10th of initial value；Busbar voltage after scaling is by voltage follower, into late-class circuit；
The bus overvoltage triggers circuit includes triggers circuit and the first delay circuit；Comparator is electric by the bus after scaling
For pressure compared with setting voltage threshold, busbar voltage is more than setting voltage threshold, then comparator output high level；Comparator is defeated
The duration of the high level gone out exceedes the delay time of setting, then sends high level to signal lock circuit；
The signal lock circuit includes trigger；The set end of the trigger receives the bus overvoltage triggers circuit
After the high level of transmission, output end output high level；When the reset terminal of the trigger receives high level, output end is again defeated
Go out low level；
The time-delay reset circuit includes reset circuit, counter and the second delay circuit；Busbar voltage warp after scaling
After crossing the delay of the second delay circuit, compared with bus reset threshold, if busbar voltage is less than setting value, comparator to
Counter exports high level, and counter exports high level to the signal lock circuit；
When the execution circuit receives the high level of trigger output, cut off the discharge circuit loop of power circuit and
Signal control circuit.Further, the discharge circuit is SUPER-BUCK topology reduction voltage circuits.
Further, the trigger is CD4013.
Further, the time-delay reset circuit, after resetting five times, if discharge circuit voltage is still over-pressed, electric discharge electricity
Road is stopped power supply, and needs ground artificial to send reset instruction.
Further, the execution circuit includes electromagnetic relay and two-way level-conversion circuit.
Spacecraft provided by the invention discharge circuit overvoltage protective system, simple equipments, practicality are high, overcome existing
Electric discharge regulation circuit can not automatically recover, cross the problem of pressure point sets difficult and response speed slow, improve discharge circuit can
By property and security.
Brief description of the drawings
Invention is described further below in conjunction with the accompanying drawings：
Fig. 1 is discharge power schematic block circuit diagram in the embodiment of the present invention；
Fig. 2 is median generatrix voltage sampling circuit of the embodiment of the present invention；
Fig. 3 is median generatrix overvoltage triggers circuit of the embodiment of the present invention；
Fig. 4 is signal lock circuit in the embodiment of the present invention；
Fig. 5 is the autonomous reset circuit that is delayed in the embodiment of the present invention；
Fig. 6 is execution circuit in the embodiment of the present invention.
Embodiment
Spacecraft proposed by the present invention is made with discharge circuit overvoltage protective system below in conjunction with the drawings and specific embodiments
It is further described.According to following explanation and claims, advantages and features of the invention will become apparent from.It should be noted
It is that accompanying drawing uses using very simplified form and non-accurately ratio, only to convenience, lucidly aids in illustrating this hair
The purpose of bright embodiment.
The discharge power schematic block circuit diagram of the present invention is as shown in figure 1, be SUPERBUCK topological circuit structures, by inputting
PMOS, inductance 1, inductance 2, voltage adjustment NMOS tube, power diode, output capacitance battle array, MEA circuits, PWM wave generation circuits
(SG1525) composition such as.MEA circuit acquisition process busbar voltages, output level is to PWM wave generation circuits, and SG1525 is according to input
Level signal produce the break-make of PWM ripples control NMOS tube, accumulator battery voltage is transformed to the voltage of spacecraft demand.
Fig. 2 is the busbar voltage sample circuit of the present invention, and busbar voltage is reduced ten times (U1) by sampling resistor network, is reduced
Busbar voltage U1 afterwards passes through voltage follower, gives late-class circuit level signal.
Fig. 3 is the bus overvoltage triggers circuit of the present invention, is made up of over-pressed triggers circuit and time delay integration circuit.Electric discharge is adjusted
Save circuit output busbar voltage scope:Umin~Umax, median generatrix electric voltage over press threshold value of the present invention is set as UmaxMagnitude of voltage is very
One of (Uref1).Busbar voltage U1With Uref1Compare, if U1 is more than Uref1, comparator output high level (being here 11V).
If U1 is more than Uref1Duration be more than 40ms, the high level that comparator exports charges to the electric capacity of time delay integration circuit
(resistance 3K, diode BZ1D, electric capacity 1uF and resistance 120K compositions), time delay integration circuit output high level to trigger signal is extremely
Signal lock circuit.
Fig. 4 is the signal lock circuit of the present invention, is mainly made up of trigger CD4013.System electrification moment, reset terminal R
For 12V, output end Q acquiescence output ground levels.After trigger CD4013 set end S receives high level, output end Q outputs are high
Level simultaneously keeps often high, and after only reset terminal R receives high level, output end Q just exports low level.
Fig. 5 is the autonomous reset circuit of delay of the present invention, is made up of reset circuit and counting circuit.System electrification moment,
Counter CD4022 reset terminal RE is 12V, counter CD4022 acquiescences Vo0Export high level.Electric discharge regulation circuit output bus
Voltage range:Umin~Umax, the present invention in discharge circuit bus resetting voltage threshold value be set as Umin/ 10th of magnitude of voltage
(Uref2).Busbar voltage U1It is delayed (resistance 300K and electric capacity 10uF compositions) by 10s, busbar voltage U1With Uref2Compare, such as
Fruit U1 is less than Uref2, comparator output high level (being here 11V), counter CD4022 clock end CLK receives a height
Level, counter CD4022Vo1Output high level, Vo0It is low level with other output ends.Counter CD4022 clock end
CLK often receives a high level, and output high level is moved back (a Vo0→Vo1→Vo2→Vo3→Vo4→Vo5), the present invention is set
Having put can reset 5 times.After resetting 5 times, electric discharge regulation circuit output voltage is still over-pressed, and discharge circuit is stopped power supply, and is now needed
Ground artificial is wanted to send reset instruction, electric discharge regulation circuit could recover normal power supply.
Fig. 6 is the execution circuit of the present invention, is made up of electromagnetic relay and two-way level-conversion circuit, electromagnetic relay connects
After receiving high level, normally opened contact 1 closes, and normally-closed contact 2 disconnects.After contact 1 closes, terminal voltage is changed into from 0V on resistance 5.1K
5V, 5V level give PWM chip circuit SG1525, and 11 pin and 14 pin for making SG1525 export without PWM ripples.After contact 2 disconnects, three poles
Pipe Q1 disconnects, and triode Q2 E pin export 0.7V voltages lower than accumulator battery voltage to the G pin of PMOS, PMOS shut-off, cut
Disconnected discharge circuit power input.
Obviously, those skilled in the art can carry out the essence of various changes and deformation without departing from the present invention to the present invention
God and scope.So, if these modifications and variations of the present invention belong to the scope of the claims in the present invention and its equivalent technologies
Within, then the present invention is also intended to comprising including these changes and modification.
Claims (4)
1. a kind of spacecraft discharge circuit overvoltage protective system, it is characterised in that including the mother being connected respectively with discharge circuit
Line voltage sample circuit, bus overvoltage delay trigger circuit, signal lock circuit, the autonomous reset circuit of delay and execution circuit；
The busbar voltage sample circuit includes sampling resistor network and voltage follower；The sampling resistor network is electric by bus
Pressure is scaled 1/10th of initial value；Busbar voltage after scaling is by voltage follower, into late-class circuit；
The bus overvoltage delay trigger circuit includes triggers circuit and the first delay circuit；By the busbar voltage after scaling with setting
Determine voltage threshold to be compared, busbar voltage is more than setting voltage threshold, then comparator output high level；The height of comparator output
The duration of level exceedes the delay time of setting, then sends high level to signal lock circuit；
The signal lock circuit includes trigger；The set end of the trigger receives the bus overvoltage delay trigger circuit
After the high level of transmission, output end output high level；When the reset terminal of the trigger receives high level, output end is again defeated
Go out low level；
The autonomous reset circuit of delay includes reset circuit, counter and the second delay circuit；Busbar voltage warp after scaling
After crossing the delay of the second delay circuit, compared with bus reset threshold, if busbar voltage is less than setting value, comparator to
Counter exports high level, and counter exports high level to the signal lock circuit；
When the execution circuit receives the high level of the trigger output, the discharge circuit loop of power circuit and signal are cut off
Control circuit.
2. spacecraft as claimed in claim 1 discharge circuit overvoltage protective system, it is characterised in that the first delay electricity
Road, the delay circuit can accumulate the concussion time that busbar voltage is more than setting value, if the concussion time is less than setting time, trigger
The high level signal of circuit is shielded.
3. spacecraft as claimed in claim 1 discharge circuit overvoltage protective system, it is characterised in that the delay is autonomous multiple
Position circuit, system automatically resets after busbar voltage triggers overvoltage protection, after resetting five times, if discharge circuit busbar voltage still mistake
Pressure, discharge circuit are stopped power supply, and need ground artificial to send reset instruction.
4. spacecraft as claimed in claim 1 discharge circuit overvoltage protective system, it is characterised in that the execution circuit bag
Include electromagnetic relay and two-way level-conversion circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710689538.1A CN107546725B (en) | 2017-08-11 | 2017-08-11 | A kind of spacecraft discharge circuit overvoltage protective system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710689538.1A CN107546725B (en) | 2017-08-11 | 2017-08-11 | A kind of spacecraft discharge circuit overvoltage protective system |
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| CN107546725A true CN107546725A (en) | 2018-01-05 |
| CN107546725B CN107546725B (en) | 2019-04-12 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109039064A (en) * | 2018-07-20 | 2018-12-18 | 上海空间电源研究所 | A kind of shunt regulator device of the anti-single power supply shorted diode of spacecraft |
| CN111443629A (en) * | 2020-04-02 | 2020-07-24 | 南京理工大学 | Power supply and control circuit applied to cube star brake sail |
| CN112034317A (en) * | 2020-08-31 | 2020-12-04 | 国网山东省电力公司电力科学研究院 | Oscillation partial discharge voltage locking circuit, partial discharge test system and working method |
| CN112054483A (en) * | 2020-08-04 | 2020-12-08 | 上海空间电源研究所 | Simple high-reliability overvoltage protection circuit |
| CN112217429A (en) * | 2020-09-29 | 2021-01-12 | 西安微电子技术研究所 | Brushless motor driving circuit and method |
| CN112421714A (en) * | 2020-11-06 | 2021-02-26 | 上海空间电源研究所 | Current-limiting control method of discharge regulator for satellite |
| CN115184724A (en) * | 2022-06-29 | 2022-10-14 | 南通通成自动化技术有限公司 | Join in marriage abnormal voltage detection circuit of electrical room |
| CN115207877A (en) * | 2022-09-15 | 2022-10-18 | 江苏广识电气有限公司 | Automatic power supply switching circuit of electrical equipment |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1169785A (en) * | 1997-08-27 | 1999-03-09 | Hitachi Ltd | Power supply circuit |
| CN1212521A (en) * | 1997-09-03 | 1999-03-31 | 索尼公司 | Digital controlled oscillation circuit and PLL circuit |
| CN201623482U (en) * | 2009-12-28 | 2010-11-03 | 中国航空工业集团公司第六三一研究所 | UUT (Unit Under Test) protection circuit |
| CN102386653A (en) * | 2006-10-05 | 2012-03-21 | 日本电信电话株式会社 | Discharger and discharger control method |
| CN103545785A (en) * | 2013-10-25 | 2014-01-29 | 上海臻和防雷电气技术有限责任公司 | Power supply MOV surge protection device failure fault current cyclic wave monitoring device and method |
| CN204154882U (en) * | 2014-08-06 | 2015-02-11 | 中国电子科技集团公司第三十八研究所 | The sampling of a kind of power supply noble potential fault and holding circuit |
| CN104410038A (en) * | 2014-10-21 | 2015-03-11 | 上海空间电源研究所 | Overvoltage protection circuit for discharge regulating circuit |
| US20150236530A1 (en) * | 2012-03-30 | 2015-08-20 | Renesas Electronics Corporation | Semiconductor device for battery control and battery pack |
| CN106249803A (en) * | 2016-09-30 | 2016-12-21 | 上海空间电源研究所 | Solaode power control circuit based on MPPT |
| CN106300275A (en) * | 2016-09-26 | 2017-01-04 | 辉芒微电子（深圳）有限公司 | A kind of BUCK drive circuit, power supply chip and application thereof |
-
2017
- 2017-08-11 CN CN201710689538.1A patent/CN107546725B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1169785A (en) * | 1997-08-27 | 1999-03-09 | Hitachi Ltd | Power supply circuit |
| CN1212521A (en) * | 1997-09-03 | 1999-03-31 | 索尼公司 | Digital controlled oscillation circuit and PLL circuit |
| CN102386653A (en) * | 2006-10-05 | 2012-03-21 | 日本电信电话株式会社 | Discharger and discharger control method |
| CN201623482U (en) * | 2009-12-28 | 2010-11-03 | 中国航空工业集团公司第六三一研究所 | UUT (Unit Under Test) protection circuit |
| US20150236530A1 (en) * | 2012-03-30 | 2015-08-20 | Renesas Electronics Corporation | Semiconductor device for battery control and battery pack |
| CN103545785A (en) * | 2013-10-25 | 2014-01-29 | 上海臻和防雷电气技术有限责任公司 | Power supply MOV surge protection device failure fault current cyclic wave monitoring device and method |
| CN204154882U (en) * | 2014-08-06 | 2015-02-11 | 中国电子科技集团公司第三十八研究所 | The sampling of a kind of power supply noble potential fault and holding circuit |
| CN104410038A (en) * | 2014-10-21 | 2015-03-11 | 上海空间电源研究所 | Overvoltage protection circuit for discharge regulating circuit |
| CN106300275A (en) * | 2016-09-26 | 2017-01-04 | 辉芒微电子（深圳）有限公司 | A kind of BUCK drive circuit, power supply chip and application thereof |
| CN106249803A (en) * | 2016-09-30 | 2016-12-21 | 上海空间电源研究所 | Solaode power control circuit based on MPPT |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109039064B (en) * | 2018-07-20 | 2020-06-02 | 上海空间电源研究所 | Shunting adjusting device for preventing short circuit of single power supply diode of spacecraft |
| CN109039064A (en) * | 2018-07-20 | 2018-12-18 | 上海空间电源研究所 | A kind of shunt regulator device of the anti-single power supply shorted diode of spacecraft |
| CN111443629A (en) * | 2020-04-02 | 2020-07-24 | 南京理工大学 | Power supply and control circuit applied to cube star brake sail |
| CN111443629B (en) * | 2020-04-02 | 2021-09-10 | 南京理工大学 | Power supply and control circuit applied to cube star brake sail |
| CN112054483A (en) * | 2020-08-04 | 2020-12-08 | 上海空间电源研究所 | Simple high-reliability overvoltage protection circuit |
| CN112034317B (en) * | 2020-08-31 | 2023-11-28 | 国网山东省电力公司电力科学研究院 | Oscillating partial discharge voltage locking circuit, partial discharge test system and working method |
| CN112034317A (en) * | 2020-08-31 | 2020-12-04 | 国网山东省电力公司电力科学研究院 | Oscillation partial discharge voltage locking circuit, partial discharge test system and working method |
| CN112217429A (en) * | 2020-09-29 | 2021-01-12 | 西安微电子技术研究所 | Brushless motor driving circuit and method |
| CN112421714A (en) * | 2020-11-06 | 2021-02-26 | 上海空间电源研究所 | Current-limiting control method of discharge regulator for satellite |
| CN112421714B (en) * | 2020-11-06 | 2023-02-21 | 上海空间电源研究所 | Current-limiting control method of discharge regulator for satellite |
| CN115184724A (en) * | 2022-06-29 | 2022-10-14 | 南通通成自动化技术有限公司 | Join in marriage abnormal voltage detection circuit of electrical room |
| CN115207877A (en) * | 2022-09-15 | 2022-10-18 | 江苏广识电气有限公司 | Automatic power supply switching circuit of electrical equipment |
| CN115207877B (en) * | 2022-09-15 | 2022-12-02 | 江苏广识电气有限公司 | Automatic power switching circuit of electrical equipment |
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