CN103427682A - High-performance aviation power supply - Google Patents
High-performance aviation power supply Download PDFInfo
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- CN103427682A CN103427682A CN2013103532119A CN201310353211A CN103427682A CN 103427682 A CN103427682 A CN 103427682A CN 2013103532119 A CN2013103532119 A CN 2013103532119A CN 201310353211 A CN201310353211 A CN 201310353211A CN 103427682 A CN103427682 A CN 103427682A
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Abstract
The invention relates to a high-performance aviation power supply which is characterized by at least comprising a delay EMC (electro magnetic compatibility) filter, a voltage inverter module, an output module, a current feedback circuit, a voltage feedback circuit, a control circuit, a driving circuit and a power supply board. Alternating current input and output are divided into two paths, one path is inputted to an input end of the voltage inverter module through a delay starting unit, an output end of the voltage inverter module is connected with the output module through a first transformer in a coupling manner, the other path is connected with the power supply board through a second transformer in a coupling manner, and the power supply board is electrically connected with the control circuit. The control circuit is divided into two paths, one path is electrically connected with an output end of the output module, and the other path is electrically connected with the voltage inverter module through the driving circuit. The high-performance aviation power supply has output over-voltage protection, internal over-heating protection and output overload protection functions, and is high in safety and reliability.
Description
Technical field
The present invention relates to a kind of airplane power source, particularly a kind of high-performance airplane power source.
Background technology
The airplane power source of traditional scheme generally adopts direct current unit and silicon controlled rectification power source.Its properties of product are subject to the restriction of design itself, can better not adapt to such as Aero-Space the demand of military electronic product.
These series of products adopt the high-frequency power electronic converter technique, special is the direct-current switch power supply that aviation and military electronic electric equipment manufacture and design, can be used for the Military Electronic Equipment such as aircraft and airborne equipment, space flight, navigation, and other needs the occasion of direct-current switch power supply.It is the regeneration product of direct current unit and silicon controlled rectification power source.
Summary of the invention
The purpose of this invention is to provide the high-performance airplane power source that a kind of security reliability is high.
The object of the present invention is achieved like this, a kind of high-performance airplane power source, it is characterized in that: at least comprise time delay EMC filter, voltage inversion module, output, current feedback circuit, voltage feedback circuit, control circuit, drive circuit and power panel, exchange input and output and be divided into two-way, one tunnel is input to voltage inversion module input through the delayed startup unit, voltage inversion module output with output module by the first transformer coupled connection; Another road is of coupled connections by the second transformer and power panel, and power panel is electrically connected to control circuit, the control circuit two-way, and a road is electrically connected to the output of output module, and another road is electrically connected to the voltage inversion module by drive circuit.
Described voltage inversion module comprises one group of diode rectifier bridge heap and two cmos switch pipe BG1 and BG2, the grid of two cmos switch pipe BG1 and BG2 is electrically connected to the drive circuit control end, the source electrode of cmos switch pipe BG1 and BG2 drain electrode are connected in series, between the drain electrode of cmos switch pipe BG1 and BG2 source electrode and be connected to electric capacity c1 and the c2 be connected in series, electric capacity c1 and c2 be connected in series a little and being connected in series a little of cmos switch pipe BG1 and BG2 just extremely is electrically connected to the output module switch transformer by electric capacity c3; Be connected to lc circuit capacitor C 4 two ends of diode rectifier bridge heap output between the drain electrode of cmos switch pipe BG1 and BG2 source electrode.
Described output module comprises: switch transformer, secondary rectification circuit and the 2nd LC filter, and the inferior of switch transformer extremely is electrically connected to the input of secondary rectification circuit, and the output of secondary rectification circuit is electrically connected to the 2nd LC filter input end.
Described output module output is connected with current transformer and voltage transformer, current transformer and voltage transformer are electrically connected to current feedback circuit and voltage feedback circuit input respectively, and current feedback circuit and voltage feedback circuit output are electrically connected to the control circuit input.
Advantage of the present invention: there is output over-voltage protection, when output voltage surpass the adjustable range higher limit 10% the time, overvoltage crowbar is protected immediately, powered-down output.The over-heat inside protection, power supply is in running, and when the power module radiator temperature surpasses 90 ℃, over-temperature circuit is moved immediately, powered-down output.The output overloading protection, when 125% of power supply output overrate electric current, cross current circuit and move immediately, powered-down output.
The accompanying drawing explanation
Below in conjunction with the embodiment accompanying drawing, the invention will be further described:
Fig. 1 is a kind of high-performance airplane power source of the present invention structural front view:
In figure: 1. time delay EMC filter; 2. voltage inversion module; 3. output module; 4. current feedback circuit; 5. voltage feedback circuit; 6. control circuit; 7. drive circuit; 8 power panels; 9. exchange input.
Embodiment
As shown in Figure 1, a kind of high-performance airplane power source, it is characterized in that: at least comprise time delay EMC filter 1, voltage inversion module 2, output module 3, current feedback circuit 4, voltage feedback circuit 5, control circuit 6, drive circuit 7 and power panel 8, exchange input 9 outputs and be divided into two-way, one tunnel is input to voltage inversion module 2 inputs through delayed startup unit 1, voltage inversion module 2 outputs with output module 3 by the first transformer coupled connection; Another road is of coupled connections by the second transformer and power panel 8, and power panel 8 is electrically connected to control circuit 6,6 minutes two-way of control circuit, and a road is electrically connected to the output of output module 3, and another road is electrically connected to voltage inversion module 2 by drive circuit 7.
Voltage inversion module 2 comprises one group of diode rectifier bridge heap and two cmos switch pipe BG1 and BG2, the grid of two cmos switch pipe BG1 and BG2 is electrically connected to the control end of drive circuit 7, the source electrode of cmos switch pipe BG1 and BG2 drain electrode are connected in series, between the drain electrode of cmos switch pipe BG1 and BG2 source electrode and be connected to electric capacity c1 and the c2 be connected in series, electric capacity c1 and c2 be connected in series a little and being connected in series a little of cmos switch pipe BG1 and BG2 just extremely is electrically connected to the switch transformer of output module 3 by electric capacity c3; Be connected to lc circuit capacitor C 4 two ends of diode rectifier bridge heap output between the drain electrode of cmos switch pipe BG1 and BG2 source electrode.The rectifier bridge stack circuit first converts the alternating current of input to direct current, then pass through control circuit, switching tube BG1 and BG2 are alternately turned on and off, thereby DC power supply is transformed into to high-frequency impulse, by high frequency transformer, required voltage is fallen into in this voltage (liter), the DC inverter after soon rectification is high-frequency ac; Industrial-frequency alternating current is through EMC filter and current rectifying and wave filtering circuit, obtain the DC power supply (electrical network nominal line voltage is 220V) of the about 310V of maximum left and right, this direct voltage is applied on the power converting loop be comprised of IGBT pipe BG1～BG2 and high frequency transformer T, and then carries out rectification by secondary rectifier diode UR1.
Described output module 3 comprises: switch transformer, secondary rectification circuit and the 2nd LC filter, the inferior of switch transformer extremely is electrically connected to the input of secondary rectification circuit, the output of secondary rectification circuit is electrically connected to the 2nd LC filter input end, secondary rectification circuit carries out by the high-frequency impulse to switch transformer the square wave that rectification obtains doubling former limit switching frequency, then through the 2nd LC filter, it is smoothed to continuous low ripple DC power supply.
Described output module 3 outputs are connected with current transformer and voltage transformer, current transformer and voltage transformer are electrically connected to current feedback circuit 4 and voltage feedback circuit 5 inputs respectively, and current feedback circuit 4 and voltage feedback circuit 5 outputs are electrically connected to control circuit 6 inputs.Current feedback circuit 4, voltage feedback circuit 5, control circuit 6 and drive circuit 7 all belong to techniques well known, just are not described in detail here.
Control circuit and drive circuit are all to adopt techniques well known, are not described in detail here.
Advantage of the present invention: there is output over-voltage protection, when output voltage surpass the adjustable range higher limit 10% the time, overvoltage crowbar is protected immediately, powered-down output.The over-heat inside protection, power supply is in running, and when the power module radiator temperature surpasses 90 ℃, over-temperature circuit is moved immediately, powered-down output.The output overloading protection, when 125% of power supply output overrate electric current, cross current circuit and move immediately, powered-down output.
The parts that the present embodiment does not describe in detail and structure belong to well-known components and common structure or the conventional means of the industry, here no longer narration.
Claims (4)
1. a high-performance airplane power source, it is characterized in that: at least comprise time delay EMC filter (1), voltage inversion module (2), output (3), current feedback circuit (4), voltage feedback circuit (5), control circuit (6), drive circuit (7) and power panel (8), exchange input (9) output and be divided into two-way, one tunnel through the delayed startup unit (1) be input to voltage inversion module (2) input, voltage inversion module (2) output with output module (3) by the first transformer coupled connection; Another road is of coupled connections by the second transformer and power panel (8), power panel (8) is electrically connected to control circuit (6), control circuit (6) two-way, a road is electrically connected to the output of output module (3), and another road is electrically connected to voltage inversion module (2) by drive circuit (7).
2. a kind of high-performance airplane power source according to claim 1, it is characterized in that: described voltage inversion module (2) comprises one group of diode rectifier bridge heap and two cmos switch pipe BG1 and BG2, the grid of two cmos switch pipe BG1 and BG2 is electrically connected to drive circuit (7) control end, the source electrode of cmos switch pipe BG1 and BG2 drain electrode are connected in series, between the drain electrode of cmos switch pipe BG1 and BG2 source electrode and be connected to electric capacity c1 and the c2 be connected in series, electric capacity c1 and c2 be connected in series a little and being connected in series a little by electric capacity c3 of cmos switch pipe BG1 and BG2 just extremely is electrically connected to output module (3) switch transformer, be connected to lc circuit capacitor C 4 two ends of diode rectifier bridge heap output between the drain electrode of cmos switch pipe BG1 and BG2 source electrode.
3. a kind of high-performance airplane power source according to claim 1, it is characterized in that: described output module (3) comprising: switch transformer, secondary rectification circuit and the 2nd LC filter, the inferior of switch transformer extremely is electrically connected to the input of secondary rectification circuit, and the output of secondary rectification circuit is electrically connected to the 2nd LC filter input end.
4. a kind of high-performance airplane power source according to claim 1, it is characterized in that: described output module (3) output is connected with current transformer and voltage transformer, current transformer and voltage transformer are electrically connected to current feedback circuit (4) and voltage feedback circuit (5) input respectively, and current feedback circuit (4) and voltage feedback circuit (5) output are electrically connected to control circuit (6) input.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013103532119A CN103427682A (en) | 2013-08-14 | 2013-08-14 | High-performance aviation power supply |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013103532119A CN103427682A (en) | 2013-08-14 | 2013-08-14 | High-performance aviation power supply |
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| CN103427682A true CN103427682A (en) | 2013-12-04 |
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| CN2013103532119A Pending CN103427682A (en) | 2013-08-14 | 2013-08-14 | High-performance aviation power supply |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015165107A1 (en) * | 2014-04-30 | 2015-11-05 | 深圳欧陆通电子有限公司 | Electrical device and power supply device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4847746A (en) * | 1987-03-20 | 1989-07-11 | Deutsche Thomson-Brandt Gmbh | Inverter to feed a load having an inductive component |
| CN101618472A (en) * | 2009-08-06 | 2010-01-06 | 唐山松下产业机器有限公司 | Soft switch inversion electric welding machine |
| CN101972881A (en) * | 2010-11-11 | 2011-02-16 | 深圳市华意隆实业发展有限公司 | Asymmetrical half-bridge zero-voltage soft switching inverter type welding and cutting machine |
| CN203482109U (en) * | 2013-08-14 | 2014-03-12 | 西安睿诺新能源有限公司 | High-performance aviation power supply |
-
2013
- 2013-08-14 CN CN2013103532119A patent/CN103427682A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4847746A (en) * | 1987-03-20 | 1989-07-11 | Deutsche Thomson-Brandt Gmbh | Inverter to feed a load having an inductive component |
| CN101618472A (en) * | 2009-08-06 | 2010-01-06 | 唐山松下产业机器有限公司 | Soft switch inversion electric welding machine |
| CN101972881A (en) * | 2010-11-11 | 2011-02-16 | 深圳市华意隆实业发展有限公司 | Asymmetrical half-bridge zero-voltage soft switching inverter type welding and cutting machine |
| CN203482109U (en) * | 2013-08-14 | 2014-03-12 | 西安睿诺新能源有限公司 | High-performance aviation power supply |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015165107A1 (en) * | 2014-04-30 | 2015-11-05 | 深圳欧陆通电子有限公司 | Electrical device and power supply device |
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Application publication date: 20131204 |