CN106371544A - Airborne computer power interruption protection system - Google Patents
Airborne computer power interruption protection system Download PDFInfo
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- CN106371544A CN106371544A CN201610966729.3A CN201610966729A CN106371544A CN 106371544 A CN106371544 A CN 106371544A CN 201610966729 A CN201610966729 A CN 201610966729A CN 106371544 A CN106371544 A CN 106371544A
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- 239000003990 capacitor Substances 0.000 claims description 10
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- 238000001914 filtration Methods 0.000 claims description 3
- 230000000087 stabilizing effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 7
- 230000009471 action Effects 0.000 abstract description 3
- 230000008569 process Effects 0.000 abstract description 3
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F1/00—Details not covered by groups G06F3/00 - G06F13/00 and G06F21/00
- G06F1/26—Power supply means, e.g. regulation thereof
- G06F1/30—Means for acting in the event of power-supply failure or interruption, e.g. power-supply fluctuations
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Abstract
The invention relates to the technical field of power protection, in particular to an airborne computer power interruption protection system. The airborne computer power interruption protection system comprises an EMI power filter, an interruption switching circuit and a backup power supply circuit, wherein the EMI power filter is arranged at the wire inlet end of a power supply for power supply EMI protection, a direct current power supply 28 V of the EMI power filter is connected to the interruption switching circuit and meanwhile is connected with the backup power supply circuit for charging, the interruption switching circuit is responsible for real-time monitoring of main power supply, and once the interruption switching circuit finds that the input direct current power supply 28 V is interrupted or drops, power supply of the direct current power supply 28 V is stopped through an MOS tube and is switched to the backup power supply circuit. Once the system finds that the power supply is interrupted or drops to an interruption switching circuit set value, namely the power supply is switched to the backup power supply circuit through an action within 15 us to ensure seamless power switching supply at the rear end, the switching speed is high, and the process is smooth and stable.
Description
[technical field]
The present invention relates to power protection field, a kind of specifically airborne computer power interruptions protection system.
[background technology]
In aircraft electrical power supply system, of short duration power supply power failure phenomenon is inevitable, either in parallel connection still
In non-parallel system, main generator and apu after ground power supply and apu electromotor before and after Main Engine Start, engine start
Between electromotor, the normal conversion of power supply all can cause the short time power failure of electrical equipment.(time is or not of short duration power failure
More than 100ms) work influence of the electric/electronic device analog to the past less, but the electric electricity to modern digital formula aircraft
The normal work of sub- equipment can produce very big interference, or even can change original working condition, comprehensive as self-navigation
Close electronic system and be necessary for the ability normal work that again resets.In AC power supply system, Power convert is by the conversion interlocking of system
Circuit controls, and when requiring transformation into new power, disconnects original power supply by interlock circuit first, aircraft experienced of short duration electricity
After the interrupt status of source, then connect new power.When the system power supply break period is mainly subject to the time delay of epc conversion time and testing circuit
Between determine.
Developing rapidly with aeronautical technology, is equipped with substantial amounts of microprocessor, such as in Boeing-767 in aircarrier aircraft
51 systems are just had to employ cpu on aircraft, in order to safe and reliable, many systems are even more equipped with 2～3 sets of redundant systems, whole
The cpu of individual aircraft utilization has more than 170.If the operationally suddenly power-off of these equipment, some data may lose and
Cisco unity malfunction, for example, if more than fmc power-off 200ms is it is necessary to could normal work with another fmc re-synchronization.To the greatest extent
Pipe adds auxiliary circuit to reduce the interference to equipment for the power interruptions in electric power system and electronic equipment, but because of power interruptions
And so that the abnormal event of electronic equipment is still happened occasionally, using not interrupt techniques gesture must therefore in power supply normal conversion
OK.
Interrupt techniques generally use in power supply normal conversion, each power supply are carried out the parallel connection of short time, Ran Houzai
Disconnect former power supply, whole power supply tasks are undertaken by new power, as long as ensure that circuit design is correct, control logic tight, just
Power failure phenomenon in normal power source transformation process can be completely eliminated.But realizing the parallel operation between conversion electric power
When, two power supplys must simultaneously meet: voltage waveform, phase sequence, frequency, magnitude of voltage are with the phase contrast putting into moment in parallel all in regulation
Within the scope of, the dash current that such guarantee produced in moment in parallel is less than allowed band with percussion power, and ensures
Can normally run after parallel connection.If condition in parallel is not being met, aircraft electrical network can produce very big electric current, voltage and
Power rush, leads to electromotor off-the-line in parallel on electrical network, exits parallel connection, causes failure in parallel.It is necessary for this to set in end
For taking corresponding protective measure, to solve the problems such as impact, surge and interruption of being likely to occur above.
[content of the invention]
The present invention is the power failure phenomenon according to normal power source transformation process of the prior art, and is directed to main power supply
Between moment produces when switching electric current, voltage and power rush be easily caused the feelings of impact, surge and interruption in parallel on electrical network
Condition, design is a kind of to connect airborne computer power interruptions protection system reliable, that structure is novel.
To achieve these goals, design a kind of airborne computer power interruptions protection system, described power interruptions are protected
Protecting system includes emi power-supply filter, interrupts switching circuit, backup power supply circuits, is provided with emi electricity in the input end of incoming cables of power supply
Source filter makees power supply emi protection, and the DC source 28v through emi power-supply filter connects to interruption switching circuit, and connects simultaneously
Connect backup power supply circuits to be charged, described interruption switching circuit is responsible for the main power supply of monitor in real time, interrupts switching circuit once
Find that the DC source 28v of input interrupts or declines, powering and switching to backup of DC source 28v is closed by mos pipe
Power supply circuits, the outfan of described backup power supply circuits connects to the input interrupting switching circuit, interrupts switching circuit
Outfan be connected to respectively+12v power supply circuits ,+5v power supply circuits and+3.3v power supply circuits for output to computer system confession
Electricity.
By chip u16 as main control chip, No. 2 pin e1 ends of described chip u16 connect described interruption switching circuit
Meet DC source 28v, connecting between No. 2 pin e1 ends of chip u16 and No. 3 pin gnd ends is connected to resistance r119 and resistance
The two ends parallel connection of r120, resistance r120 is connected to electric capacity c95, is connected between No. 4 pin e2 ends of chip u16 and No. 5 pin h2 ends
No. 4 pin e2 ends of resistance r121, chip u16 are another to extract the junction point that an end is connected between resistance r119 and resistance r120, core out
No. 6 pin g2 ends of piece u16 are divided into two-way to be respectively connected to No. 1 pin of mos pipe q26 and No. 1 pin of mos pipe q23, and mos manages
No. 3 pins of q26 and mos pipe q23 are connected, and No. 4 pins of mos pipe q26 connect backup power supply circuits, in No. 7 pipes of chip u16
Foot v2 end extraction one end is grounded after connecting electric capacity c93, and extracts No. 4 pins that an end is connected to mos pipe q26 out, No. 8 of chip u16
Pin vs end is respectively connecting to+12v power supply circuits ,+5v power supply circuits and+3.3v as the out outfan interrupting switching circuit
Power supply circuits, No. 8 pin vs ends of chip u16 are separately extracted out after one end connects electric capacity c94 and are grounded, No. 9 pin v1 ends of chip u16
It is grounded after meeting electric capacity c97, No. 10 pin g1 ends of chip u16 are connected to No. 1 pin of mos pipe q24, No. 4 pins of mos pipe q24
Merge with No. 9 pin v1 ends of chip u16 and be followed by DC source 28v, No. 3 pins of mos pipe q24 and No. 4 of mos pipe q23
Pin connects the out outfan being followed by interrupting switching circuit.
By chip u15 as main control chip, No. 20 pin vin of chip u15 are terminated with directly described backup power supply circuits
Stream voltage 28v is as chip power, and is connected to electric capacity c80 filtering, and electricity is passed through at No. 1 pin en/uvlo end of described chip u15
Resistance r103 connects DC voltage 28v, and in resistance r103 and ground terminal parallel resistance r104 and Zener diode d7 respectively, chip
No. 12 pin rt of u15 are grounded after being terminated with resistance r105, and No. 13 pin sync of chip u15 are terminated with resistance r108 and are followed by
Ground, is connected to resistance r110, No. 5 pins of chip u15 between No. 2 pin vref ends of chip u15 and No. 5 pin ctrl1 ends
Ctrl1 end is another extract out one be terminated with resistance r111 after be grounded, No. 2 pin vref ends of chip u15 and No. 3 pin ctrl2 ends it
Between be connected to resistance r109, No. 3 pin ctrl2 ends of chip u15 are another extract out one be terminated with resistance r114 after be grounded, the 2 of chip u15
Number pin vref end is another extract termination capacitor c87 out after be grounded, be grounded after No. 6 pin ss termination capacitors c89 of chip u15, core
No. 10 pin vc ends of piece u15 are grounded after connecting resistance r116, electric capacity c90 successively, and No. 15 pin hg ends of chip u15 are connected to mos
No. 4 pins of pipe q19, No. 5 pins of mos pipe q19 meet DC voltage 28v, and tap one terminates electric capacity c81 and the electric capacity of parallel connection
No. 17 pin cboot ends of c82, chip u15 are sequentially connected resistance r106, electric capacity c83, inductance l6, resistance r107, voltage stabilizing two pole
Pipe d4, between resistance r106 and electric capacity c83, extraction one end is connected Zener diode d5 and is followed by No. 19 pins of chip u15
Vcc_int end, No. 19 pin vcc_int ends of chip u15 are separately extracted one end out and are connected ground connection, electric capacity c83 and inductance after electric capacity c86
Extract a line between l6 out to connect to No. 16 pin sw ends of chip u15, No. 18 pin lg ends of chip u15 connect to mos pipe q20
No. 4 pins, No. 5 pins of mos pipe q20 are connected to No. 16 pin sw ends of chip u15, in No. 5 pins of mos pipe q20 and No. 3
Between pin, parallel connection is connected to Zener diode d6, and No. 8 pin sensep ends of chip u15 are indirectly with No. 9 pin sensen ends
Have electric capacity c88, the two ends of electric capacity c88 connect resistance r112 respectively, resistance r115 is followed by resistance r107 two ends, resistance r107 with
It is connected to electric capacity c92, electric capacity c84, electric capacity c85 over the ground, the positive pole of Zener diode d4 extracts one end out even between Zener diode d4
Connecting resistance r113 is followed by No. 7 pin fb ends of chip u15, and extracts ground connection after a terminating resistor r117, Zener diode d4 out
Negative pole as backup power supply circuits outfan, output be terminated with electrochemical capacitor ct8 after be grounded to output signal filter.
The present invention compared with the existing technology, has an advantage in that: during the system is once find that power supply interrupts or drops to
Disconnected switching circuit arranges value, that is, within 15us, action switching supplies power to backup power supply circuits, is powered with+the 12v ensureing rear end
The power supply seamless switching of circuit ,+5v power supply circuits and+3.3v power supply circuits is powered, and backup power switching speed is fast, coordinates rear class
Filter circuit, handoff procedure smooth steady, realize efficiency high；Realize interrupt operation and electricity using the electronic devices and components of only a few
Source switches, and control method is succinct, and reliability is high；Can according to resistance flexible configuration interrupt switching circuit switching electrical voltage point and
The charging voltage of backup power supply circuits, to meet actual demand so that protecting power and break period controllable precise；With emi
Power-supply filter is protected as end, strengthens protected effect.
[brief description]
Fig. 1 is the structure connection diagram of the present invention；
Fig. 2 is the schematic diagram of the interruption switching circuit in the present invention；
Fig. 3 is the schematic diagram of the backup power supply circuits in the present invention.
[specific embodiment]
The invention will be further described below in conjunction with the accompanying drawings, for the structure of this device and the principle people professional to this
It is very clearly.It should be appreciated that specific embodiment described herein, only in order to explain the present invention, is not used to limit this
Invention.
Embodiment 1
Fig. 1 is the system structure diagram of airborne computer power interruptions protection system in the present invention, and power interruptions are protected
System includes emi power-supply filter, interrupts switching circuit, backup power supply circuits, is provided with emi power supply in the input end of incoming cables of power supply
Power supply emi protection made by wave filter, and the DC source 28v through emi power-supply filter connects to interruption switching circuit, and is simultaneously connected with
Backup power supply circuits are charged, and interrupt switching circuit and are responsible for the main power supply of monitor in real time, interrupt switching circuit and once find to input
DC source 28v interrupt or decline, the powering and switching to backup power supply circuits of DC source 28v is closed by mos pipe,
Backup power supply circuits outfan connect to interrupt switching circuit input, interrupt switching circuit outfan be connected to respectively+
12v power supply circuits ,+5v power supply circuits and+3.3v power supply circuits are used for output to computer system power supply.
Interrupt switching circuit by chip u16 as main control chip, No. 2 pin e1 ends of chip u16 connect DC source
28v, connects between No. 2 pin e1 ends of chip u16 and No. 3 pin gnd ends and is connected to resistance r119 and resistance r120, resistance
The two ends parallel connection of r120 is connected to electric capacity c95, is connected to resistance r121 between No. 4 pin e2 ends of chip u16 and No. 5 pin h2 ends,
No. 4 pin e2 ends of chip u16 are another to extract the junction point that an end is connected between resistance r119 and resistance r120 out, No. 6 of chip u16
Pin g2 end is divided into two-way to be respectively connected to No. 1 pin of mos pipe q26 and No. 1 pin of mos pipe q23, and mos pipe q26 and mos manages
No. 3 pins of q23 are connected, and No. 4 pins of mos pipe q26 connect backup power supply circuits, draw at No. 7 pin v2 ends of chip u16
One end is grounded after connecting electric capacity c93, and extracts No. 4 pins that an end is connected to mos pipe q26 out, and No. 8 pin vs ends of chip u16 are made
Out outfan for interrupting switching circuit is respectively connecting to+12v power supply circuits ,+5v power supply circuits and+3.3v power supply circuits, core
No. 8 pin vs ends of piece u16 are separately extracted out after one end connects electric capacity c94 and are grounded, after No. 9 pin v1 termination capacitors c97 of chip u16
Ground connection, No. 10 pin g1 ends of chip u16 are connected to No. 1 pin of mos pipe q24, No. 4 pins of mos pipe q24 and the 9 of chip u16
Number pin v1 end merges and is followed by DC source 28v, and No. 4 pins of No. 3 pins of mos pipe q24 and mos pipe q23 connect and are followed by
To the out outfan interrupting switching circuit.
The power input interrupting switching circuit is dc28v and backup, is output as out outfan, chip u16 real-time monitoring
Electric dc28v and backup of input, once dc28v occurs interrupting or voltage is less than setting value, control chip u16 action, mos is managed
Q24 closes, and opens mos pipe q23 and mos pipe q26 simultaneously, will power switching to backing up current supply circuit, to ensure interrupting cutting
The power supply changing circuit output is uninterrupted.Interrupt switching circuit and can change resistance value therein as needed, flexible configuration interrupts cutting
Changing the switching electrical voltage point of circuit, interrupting switching circuit once finding that the DC source 28v of input interrupts or drops to interruption switching 1
Circuit arranges value, switches to backup power supply circuits in 15us.
Backup power supply circuits class needs the charging voltage flexibly adjusting backup to charge according to actual power, in order to meet when main electricity
Required energy when interrupting in source and time.Backup power supply circuits are shown in Fig. 3 by chip u15 as main control chip, chip u15's
No. 20 pin vin are terminated with DC voltage 28v as chip power, and are connected to electric capacity c80 filtering, No. 1 pin of chip u15
En/uvlo end connects DC voltage 28v by resistance r103, and in resistance r103 and ground terminal parallel resistance r104 and voltage stabilizing respectively
No. 12 pin rt of diode d7, chip u15 are grounded after being terminated with resistance r105, and No. 13 pin sync of chip u15 are terminated with
It is grounded after resistance r108, between No. 2 pin vref ends of chip u15 and No. 5 pin ctrl1 ends, be connected to resistance r110, chip
The another extraction one in No. 5 pin ctrl1 ends of u15 is grounded after being terminated with resistance r111, and No. 2 pin vref ends of chip u15 are managed with No. 3
It is connected to resistance r109, the another extraction one in No. 3 pin ctrl2 ends of chip u15 is terminated with resistance r114 and is followed by between foot ctrl2 end
Ground, No. 2 pin vref ends of chip u15 are another to extract ground connection after termination capacitor c87, No. 6 pin ss termination capacitors of chip u15 out
It is grounded after c89, No. 10 pin vc ends of chip u15 are grounded after connecting resistance r116, electric capacity c90 successively, No. 15 pins of chip u15
Hg end is connected to No. 4 pins of mos pipe q19, and No. 5 pins of mos pipe q19 meet DC voltage 28v, and tap one terminates the electricity of parallel connection
Hold c81 and electric capacity c82, No. 17 pin cboot ends of chip u15 are sequentially connected resistance r106, electric capacity c83, inductance l6, resistance
R107, Zener diode d4, between resistance r106 and electric capacity c83, extraction one end is connected Zener diode d5 and is followed by chip
No. 19 pin vcc_int ends of u15, No. 19 pin vcc_int ends of chip u15 are separately extracted out after one end connects electric capacity c86 and are grounded,
Extract a line between electric capacity c83 and inductance l6 out to be connected to No. 16 pin sw ends of chip u15, No. 18 pin lg ends of chip u15
Connect to No. 4 pins of mos pipe q20, No. 5 pins of mos pipe q20 are connected to No. 16 pin sw ends of chip u15, in mos pipe q20
No. 5 pins and No. 3 pins between in parallel be connected to Zener diode d6,1/2/3 pin of mos pipe q20 welds together, and thinks
Prevent rush of current, between No. 8 pin sensep ends of chip u15 and No. 9 pin sensen ends, be connected to electric capacity c88, electric capacity c88
Two ends connect resistance r112 respectively, resistance r115 is followed by resistance r107 two ends, between resistance r107 and Zener diode d4
Be connected to electric capacity c92, electric capacity c84, electric capacity c85 over the ground, the positive pole of Zener diode d4 extract out one end connect resistance r113 be followed by
No. 7 pin fb ends of chip u15, and extract ground connection after a terminating resistor r117 out, the negative pole of Zener diode d4 supplies as backup
The outfan of circuit, output is grounded after being terminated with electrochemical capacitor ct8 and output signal is filtered.Wherein, mos pipe q20 and mos pipe
No. 1 of q19, No. 2, the internal short circuits of No. 3 pins, prevent that electric current is excessive to cause mos pipe to damage or overheated.
Claims (3)
1. a kind of airborne computer power interruptions protection system is it is characterised in that described power interruptions protection system includes emi
Power-supply filter, interruption switching circuit, backup power supply circuits, are provided with emi power-supply filter in the input end of incoming cables of power supply and make electricity
Source emi protects, and the DC source 28v through emi power-supply filter connects to interruption switching circuit, and is simultaneously connected with backup power supply electricity
Road is charged, and described interruption switching circuit is responsible for the main power supply of monitor in real time, interrupts switching circuit once finding the straight of input
Stream power supply 28v interrupts or declines, and closes powering and switching to backup power supply circuits of DC source 28v by mos pipe, described
Backup power supply circuits outfan connect to interrupt switching circuit input, interrupt switching circuit outfan be connected to respectively
+ 12v power supply circuits ,+5v power supply circuits and+3.3v power supply circuits are used for output to computer system power supply.
2. as claimed in claim 1 a kind of airborne computer power interruptions protection system it is characterised in that described interruption is cut
Change electric router chip u16 as main control chip, No. 2 pin e1 ends of described chip u16 connect DC source 28v, in chip
Connect between No. 2 pin e1 ends of u16 and No. 3 pin gnd ends and be connected to resistance r119 and resistance r120, the two ends of resistance r120 are simultaneously
Connection has electric capacity c95, is connected to resistance r121 between No. 4 pin e2 ends of chip u16 and No. 5 pin h2 ends, No. 4 of chip u16
Pin e2 end is another to extract the junction point that an end is connected between resistance r119 and resistance r120 out, and No. 6 pin g2 ends of chip u16 are divided into
Two-way is respectively connected to No. 1 pin of mos pipe q26 and No. 1 pin of mos pipe q23, No. 3 pins of mos pipe q26 and mos pipe q23
It is connected, No. 4 pins of mos pipe q26 connect backup power supply circuits, connect electric capacity in No. 7 pin v2 ends extraction one end of chip u16
It is grounded after c93, and extracts No. 4 pins that an end is connected to mos pipe q26 out, No. 8 pin vs ends of chip u16 are electric as interrupting switching
The out outfan on road is respectively connecting to+12v power supply circuits ,+5v power supply circuits and+3.3v power supply circuits, No. 8 pipes of chip u16
Foot vs separately extracts out at end after one end connects electric capacity c94 and is grounded, and is grounded, chip u16 after No. 9 pin v1 termination capacitors c97 of chip u16
No. 10 pin g1 ends be connected to No. 1 pin of mos pipe q24, No. 4 pins of mos pipe q24 are closed with No. 9 pin v1 ends of chip u16
And be followed by DC source 28v, No. 4 pins connections of No. 3 pins of mos pipe q24 and mos pipe q23 are followed by interruption switching electricity
The out outfan on road.
3. as claimed in claim 1 a kind of airborne computer power interruptions protection system it is characterised in that described backup supplies
Electricity electricity router chip u15 is terminated with DC voltage 28v as chip electricity as main control chip, No. 20 pin vin of chip u15
Source, and it is connected to electric capacity c80 filtering, No. 1 pin en/uvlo end of described chip u15 connects DC voltage by resistance r103
28v, and in resistance r103 and ground terminal parallel resistance r104 and Zener diode d7 respectively, No. 12 pin rt terminations of chip u15
It is grounded after having resistance r105, No. 13 pin sync of chip u15 are grounded, in No. 2 pins of chip u15 after being terminated with resistance r108
It is connected to resistance r110, the another extraction one in No. 5 pin ctrl1 ends of chip u15 is terminated between vref end and No. 5 pin ctrl1 ends
It is grounded after resistance r111, between No. 2 pin vref ends of chip u15 and No. 3 pin ctrl2 ends, be connected to resistance r109, chip u15
No. 3 pin ctrl2 ends another extract out one be terminated with resistance r114 after be grounded, one end is separately extracted at No. 2 pin vref ends of chip u15 out
It is grounded after meeting electric capacity c87, be grounded after No. 6 pin ss termination capacitors c89 of chip u15, No. 10 pin vc ends of chip u15 are successively
It is grounded after connecting resistance r116, electric capacity c90, No. 15 pin hg ends of chip u15 are connected to No. 4 pins of mos pipe q19, mos pipe q19
No. 5 pins meet DC voltage 28v, and tap one terminates the electric capacity c81 and electric capacity c82 of parallel connection, No. 17 pins of chip u15
Cboot end is sequentially connected resistance r106, electric capacity c83, inductance l6, resistance r107, Zener diode d4, in resistance r106 and electric capacity
Extract one end between c83 out and connect Zener diode d5 and be followed by No. 19 pin vcc_int ends of chip u15, No. 19 of chip u15
Pin vcc_int separately extracts out at end after one end connects electric capacity c86 and is grounded, and extracts a line out and be connected to core between electric capacity c83 and inductance l6
No. 16 pin sw ends of piece u15, No. 18 pin lg ends of chip u15 connect to No. 4 pins of mos pipe q20, and the 5 of mos pipe q20
Number pin is connected to No. 16 pin sw ends of chip u15, in parallel between No. 5 pins and No. 3 pins of mos pipe q20 is connected to voltage stabilizing
It is connected to electric capacity c88 between No. 8 pin sensep ends of diode d6, chip u15 and No. 9 pin sensen ends, the two of electric capacity c88
End connects resistance r112, resistance r115 respectively and is followed by resistance r107 two ends, between resistance r107 and Zener diode d4 over the ground
It is connected to electric capacity c92, electric capacity c84, electric capacity c85, the positive pole of Zener diode d4 is extracted one end connection resistance r113 out and is followed by chip
No. 7 pin fb ends of u15, and extract ground connection after a terminating resistor r117 out, the negative pole of Zener diode d4 is as backup power supply electricity
The outfan on road, output is grounded after being terminated with electrochemical capacitor ct8 and output signal is filtered.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610966729.3A CN106371544B (en) | 2016-11-04 | 2016-11-04 | Power interruption protection system of airborne computer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610966729.3A CN106371544B (en) | 2016-11-04 | 2016-11-04 | Power interruption protection system of airborne computer |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106371544A true CN106371544A (en) | 2017-02-01 |
| CN106371544B CN106371544B (en) | 2023-12-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610966729.3A Active CN106371544B (en) | 2016-11-04 | 2016-11-04 | Power interruption protection system of airborne computer |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11677234B2 (en) | 2021-08-20 | 2023-06-13 | Hamilton Sundstrand Corporation | Power input source detection in aircraft LRU |
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| CN103746444A (en) * | 2013-11-28 | 2014-04-23 | 苏州长风航空电子有限公司 | Dual-power bus cold standby power supply architecture and method |
| WO2015032126A1 (en) * | 2013-09-09 | 2015-03-12 | 惠州市蓝微电子有限公司 | Electric tool control circuit |
| WO2015074471A1 (en) * | 2013-11-25 | 2015-05-28 | 广东美的制冷设备有限公司 | Electrostatic protection device, intelligent power module and frequency-conversion home appliance |
| CN204559536U (en) * | 2014-12-30 | 2015-08-12 | 深圳市兰丁科技有限公司 | Commutation circuit and charging device |
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2016
- 2016-11-04 CN CN201610966729.3A patent/CN106371544B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015032126A1 (en) * | 2013-09-09 | 2015-03-12 | 惠州市蓝微电子有限公司 | Electric tool control circuit |
| WO2015074471A1 (en) * | 2013-11-25 | 2015-05-28 | 广东美的制冷设备有限公司 | Electrostatic protection device, intelligent power module and frequency-conversion home appliance |
| CN103746444A (en) * | 2013-11-28 | 2014-04-23 | 苏州长风航空电子有限公司 | Dual-power bus cold standby power supply architecture and method |
| CN204559536U (en) * | 2014-12-30 | 2015-08-12 | 深圳市兰丁科技有限公司 | Commutation circuit and charging device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11677234B2 (en) | 2021-08-20 | 2023-06-13 | Hamilton Sundstrand Corporation | Power input source detection in aircraft LRU |
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| CN106371544B (en) | 2023-12-15 |
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