CN203491887U - Voltage withstanding circuit for aviation DC power supply circuit - Google Patents
Voltage withstanding circuit for aviation DC power supply circuit Download PDFInfo
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- CN203491887U CN203491887U CN201320650074.0U CN201320650074U CN203491887U CN 203491887 U CN203491887 U CN 203491887U CN 201320650074 U CN201320650074 U CN 201320650074U CN 203491887 U CN203491887 U CN 203491887U
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Abstract
The utility model discloses a voltage withstanding circuit for an aviation DC power supply circuit. The input end of the voltage withstanding circuit is connected with the output end of the aviation DC power supply circuit. The voltage withstanding circuit comprises a first resistor, a second resistor, a first capacitor, a second capacitor, a first voltage regulator diode, a second voltage regulator diode, a triode, an inductor and an MAX856 boost chip. The first resistor, the first voltage regulator diode and the triode jointly form an overvoltage withstanding voltage limiting circuit, and the second resistor, the first capacitor, the second capacitor, the second voltage regulator diode, the inductor and the MAX856 boost chip jointly form an undervoltage withstanding voltage limiting circuit, wherein the above-mentioned two circuits are in series connection. No matter an overvoltage surge or an undervoltage surge occurs in the aviation DC power supply circuit, a normal operation voltage can be output with processing of the voltage withstanding circuit, so that an aviation DC electronic device is prevented from being damaged due to interference of the surge voltage, the aviation DC electronic device is ensured to be normally operated, and aviation safety is achieved.
Description
Technical field
The utility model relates to a kind of auxiliary circuit of aviation DC power supply circuit, relates in particular to a kind of voltage holding circuit for aviation DC power supply circuit.
Background technology
Avionics system is generally direct current 28V power supply, and electric power system is storage battery, in the course of work, by generator, is constantly its charging.Because aerogenerator operating state is more complicated, so there is unsteadiness, can introduce certain interference, form overvoltage surge or under-voltage surge.In addition, airborne vehicle, in high-altitude flight, is also easily subject to the impact of thunder and lightning, thereby produces overvoltage surge.These surge voltages can affect the stability of aviation DC power supply circuit output voltage, thereby affect the normal operation of DC electronic equipment, and then affect the normal flight of airborne vehicle, even may occur serious security incident.Present aviation DC power supply circuit has some auxiliary circuits for addressing the above problem, but exists effective but with high costs or cost is lower but the problem of function limitation, is difficult to realize the low-cost object comprehensively addressing the above problem.
Utility model content
The purpose of this utility model provides a kind of voltage holding circuit for aviation DC power supply circuit that can low-cost realize overvoltage surge and under-voltage surge protection with regard to being in order to address the above problem.
The utility model is achieved through the following technical solutions above-mentioned purpose:
Voltage holding circuit for aviation DC power supply circuit described in the utility model, its input is connected with the output of described aviation DC power supply circuit, described voltage holding circuit comprises the first resistance, the second resistance, the first electric capacity, the second electric capacity, the first zener diode, the second voltage stabilizing didoe, triode, inductance and the MAX856 chip that boosts, the first end of described the first resistance is connected with the collector electrode of described triode and as the electrode input end of described voltage holding circuit, the second end of described the first resistance is connected with the negative pole of described the first voltage stabilizing didoe with the base stage of described triode respectively, the emitter of described triode is connected with the first end of described inductance, the second end of described inductance is connected with the positive pole of described the second voltage stabilizing didoe with boost the 8th pin of chip of described MAX856 respectively, the negative pole of described the second voltage stabilizing didoe respectively with the first end of described the second resistance, boost the 6th pin of chip and the first end of described the second electric capacity is connected and as the cathode output end of described voltage holding circuit of described MAX856, boost the first pin of chip and the second end of described the second resistance of described MAX856 is connected, boost the 3rd pin of chip of described MAX856 is connected with the first end of described the first electric capacity, boost the 4th pin of chip of described MAX856 is unsettled, the positive pole of described the first voltage stabilizing didoe, boost the second pin of chip of described MAX856, the 5th pin, the 7th pin, the second end of described the first electric capacity and the second end of described the second electric capacity interconnects and simultaneously as negative input and the cathode output end of described voltage holding circuit.
The common pressure limiting circuit that forms resistance to overvoltage of the first resistance, the first voltage stabilizing didoe and triode, the second resistance, the first electric capacity, the second electric capacity, the second voltage stabilizing didoe, inductance and MAX856 boost, and chip is common forms resistance to under-voltage booster circuit, and two circuit are connected in series.
The beneficial effects of the utility model are:
There is overvoltage surge or under-voltage surge in no matter aviation DC power supply circuit, after processing by this voltage holding circuit, can export normal working voltage, avoid aviation DC electronic equipment to be subject to surge voltage and disturb and be damaged, guarantee the normal operation of aviation DC electronic equipment and aviation safety; The utlity model has low, the effective advantage of cost.
Accompanying drawing explanation
Fig. 1 is the circuit diagram of the voltage holding circuit for aviation DC power supply circuit described in the utility model.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in further detail:
As shown in Figure 1, the voltage holding circuit for aviation DC power supply circuit described in the utility model, its input U
ibe connected with the output of aviation DC power supply circuit, described voltage holding circuit comprises the first resistance R 1, the second resistance R 2, the first capacitor C 1, the second capacitor C 2, the first zener diode DZ1, the second voltage stabilizing didoe DZ2, triode VT, inductance and the MAX856 chip IC of boosting, and the collector electrode of the first end of the first resistance R 1 and triode VT is connected and as the input U of described voltage holding circuit
ipositive pole, the second end of the first resistance R 1 is connected with the negative pole of the first voltage stabilizing didoe DZ1 with the base stage of triode VT respectively, the emitter of triode VT is connected with the first end of inductance L, the second end of inductance L is connected with the positive pole of the second voltage stabilizing didoe DZ2 with boost the 8th pin of chip IC of MAX856 respectively, the negative pole of the second voltage stabilizing didoe DZ2 respectively with boost the 6th pin of chip IC and the first end of the second capacitor C 2 is connected and as the output U of described voltage holding circuit of first end, the MAX856 of the second resistance R 2
opositive pole, boost the first pin of chip IC of MAX856 is connected with the second end of the second resistance R 2, boost the 3rd pin of chip IC of MAX856 is connected with the first end of the first capacitor C 1, boost the 4th pin of chip IC of MAX856 is unsettled, the positive pole of the first voltage stabilizing didoe DZ1, MAX856 boost chip IC the second pin, the 5th pin, the 7th pin, the second end of the first capacitor C 1 and the second end of the second capacitor C 2 interconnects and simultaneously as the input U of described voltage holding circuit
inegative pole and output U
onegative pole.
In foregoing circuit, the common pressure limiting circuit that forms resistance to overvoltage of the first resistance R 1, the first voltage stabilizing didoe DZ1 and triode VT, the second resistance R 2, the first capacitor C 1, the second capacitor C 2, the second voltage stabilizing didoe DZ2, inductance L and MAX856 boost, and chip IC is common forms resistance to under-voltage booster circuit, and two circuit are connected in series.There is overvoltage surge or under-voltage surge in no matter aviation DC power supply circuit, after processing by this voltage holding circuit, can export normal working voltage, avoid aviation DC electronic equipment to be subject to surge voltage and disturb and be damaged, guarantee the normal operation of aviation DC electronic equipment and aviation safety.
Claims (1)
1. the voltage holding circuit for aviation DC power supply circuit, its input is connected with the output of described aviation DC power supply circuit, it is characterized in that: described voltage holding circuit comprises the first resistance, the second resistance, the first electric capacity, the second electric capacity, the first zener diode, the second voltage stabilizing didoe, triode, inductance and the MAX856 chip that boosts, the first end of described the first resistance is connected with the collector electrode of described triode and as the electrode input end of described voltage holding circuit, the second end of described the first resistance is connected with the negative pole of described the first voltage stabilizing didoe with the base stage of described triode respectively, the emitter of described triode is connected with the first end of described inductance, the second end of described inductance is connected with the positive pole of described the second voltage stabilizing didoe with boost the 8th pin of chip of described MAX856 respectively, the negative pole of described the second voltage stabilizing didoe respectively with the first end of described the second resistance, boost the 6th pin of chip and the first end of described the second electric capacity is connected and as the cathode output end of described voltage holding circuit of described MAX856, boost the first pin of chip and the second end of described the second resistance of described MAX856 is connected, boost the 3rd pin of chip of described MAX856 is connected with the first end of described the first electric capacity, boost the 4th pin of chip of described MAX856 is unsettled, the positive pole of described the first voltage stabilizing didoe, boost the second pin of chip of described MAX856, the 5th pin, the 7th pin, the second end of described the first electric capacity and the second end of described the second electric capacity interconnects and simultaneously as negative input and the cathode output end of described voltage holding circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320650074.0U CN203491887U (en) | 2013-10-22 | 2013-10-22 | Voltage withstanding circuit for aviation DC power supply circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320650074.0U CN203491887U (en) | 2013-10-22 | 2013-10-22 | Voltage withstanding circuit for aviation DC power supply circuit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203491887U true CN203491887U (en) | 2014-03-19 |
Family
ID=50262687
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320650074.0U Expired - Fee Related CN203491887U (en) | 2013-10-22 | 2013-10-22 | Voltage withstanding circuit for aviation DC power supply circuit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203491887U (en) |
-
2013
- 2013-10-22 CN CN201320650074.0U patent/CN203491887U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140319 Termination date: 20141022 |
|
| EXPY | Termination of patent right or utility model |