CN203104272U - Electromagnetic compatibility filter applicable to aircraft - Google Patents
Electromagnetic compatibility filter applicable to aircraft Download PDFInfo
- Publication number
- CN203104272U CN203104272U CN2013200806146U CN201320080614U CN203104272U CN 203104272 U CN203104272 U CN 203104272U CN 2013200806146 U CN2013200806146 U CN 2013200806146U CN 201320080614 U CN201320080614 U CN 201320080614U CN 203104272 U CN203104272 U CN 203104272U
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- capacitor
- inductance
- diode
- electromagnetic compatibility
- compatibility filter
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Abstract
The utility model discloses an electromagnetic compatibility filter applicable to an aircraft. The electromagnetic compatibility filter comprises an input terminal, an output terminal, a first diode, a second diode, a bidirectional diode, a first inductor, a second inductor, a third inductor, a first capacitor, a second capacitor, a third capacitor and a fourth capacitor, wherein the input terminal comprises a first positive input terminal, a second positive input terminal and a negative input terminal, and the output terminal comprises a positive output terminal and a negative output terminal. The electromagnetic compatibility filter can enable a transient signal to be completely absorbed before entering equipment so as to ensure the safety of electrical equipment; and the electromagnetic compatibility filter has high electromagnetic compatibility, significantly improves the anti-interference performance, and can be used in precision products with high performance requirements.
Description
Technical field
The utility model relates to a kind of filter, relates in particular to a kind of electromagnetic compatibility filter that is applicable to aircraft.
Background technology
The filter that uses in the aviation power supply, having another name called " electromagnetic interface filter ", is a kind of passive bidirectional network, is the frequency of characteristic frequency in a kind of aviation power supply or the electric equipment that the frequency beyond this frequency is carried out effective filtering, its end connects power supply, and the other end connects load.The existing filter of aviation power supply that is applicable to is owing to the variation along with load, aircraft power system will produce spike and power surge, these transient signals are with the power consumption equipment on the serious harm aircraft, even directly cause the damage of power consumption equipment, cause the electromagnetism can not be compatible, can cause the misoperation of equipment because of signal disturbs when in the sophisticated product of high performance requirements, using, even may cause serious security incident.
The utility model content
The purpose of this utility model provides a kind of electromagnetic compatibility filter that is applicable to aircraft with regard to being in order to address the above problem.
The utility model is achieved through the following technical solutions above-mentioned purpose:
The utility model comprises input, output, first diode, second diode, bidirectional diode, first inductance, second inductance, the 3rd inductance, first capacitor, second capacitor, the 3rd capacitor and the 4th capacitor, described input comprises first electrode input end, second electrode input end and negative input, described output comprises cathode output end and cathode output end, described first electrode input end is connected with the positive pole of described first diode, described second electrode input end is connected with the positive pole of described second diode, the negative pole of described first diode respectively with the negative pole of described second diode, first end of described bidirectional diode, first end of described first capacitor is connected with first end of described first inductance, second end of described first capacitor is connected with first end of described second capacitor and ground connection, second end of described first inductance is connected with first end of described second inductance and first end of described the 3rd capacitor respectively, second end of described second inductance is connected with first end of described cathode output end and described the 4th capacitor respectively, described negative input respectively with second end of described bidirectional diode, second end of described second capacitor is connected with first end of described the 3rd inductance, second end of described the 3rd inductance respectively with second end of described the 3rd capacitor, second end of described the 4th capacitor is connected with described cathode output end.
Particularly, the shared toroidal core of described first inductance and described the 3rd inductance.
Described input is arranged at a side of described filter housing.
Described output is arranged at the opposite side of described filter housing.
The beneficial effects of the utility model are:
The utility model can make transient signal before access arrangement, with its whole absorptions, guarantees the safety of power consumption equipment; Electro Magnetic Compatibility of the present utility model is higher, has significantly improved anti-tampering performance, can use in the sophisticated product of high performance requirements.
Description of drawings
Fig. 1 is a kind of circuit diagram that is applicable to the electromagnetic compatibility filter of aircraft described in the utility model.
Fig. 2 is a kind of front view that is applicable to the electromagnetic compatibility filter of aircraft described in the utility model.
Fig. 3 is a kind of left view that is applicable to the electromagnetic compatibility filter of aircraft described in the utility model.
Fig. 4 is a kind of right view that is applicable to the electromagnetic compatibility filter of aircraft described in the utility model.
Embodiment
The utility model is described in further detail below in conjunction with accompanying drawing:
As shown in Figure 1: the utility model comprises input, output, the first diode VD1, the second diode VD2, bidirectional diode VS, first inductance L 1, second inductance L 2, the 3rd inductance L 3, the first capacitor C1, the second capacitor C2, the 3rd capacitor C3 and the 4th capacitor C4, input comprises the first electrode input end A, the second electrode input end B and negative input E, output comprises cathode output end M and cathode output end E ', the first electrode input end A is connected with the positive pole of the first diode VD1, the second electrode input end B is connected with the positive pole of the second diode VD2, the negative pole of the first diode VD1 respectively with the negative pole of the second diode VD2, first end of bidirectional diode VS, first end of the first capacitor C1 is connected with first end of first inductance L 1, second end of the first capacitor C1 is connected with first end of the second capacitor C2 and ground connection, second end of first inductance L 1 is connected with first end of second inductance L 2 and first end of the 3rd capacitor C3 respectively, second end of second inductance L 2 is connected with first end of the 4th capacitor C4 with cathode output end M respectively, negative input E respectively with second end of bidirectional diode VS, second end of the second capacitor C2 is connected with first end of the 3rd inductance L 3, second end of the 3rd inductance L 3 respectively with second end of the 3rd capacitor C3, second end of the 4th capacitor C4 is connected with cathode output end E ', first inductance L 1 and the 3rd inductance L 3 shared toroidal cores.
As Fig. 2, Fig. 3 and shown in Figure 4, the first electrode input end A, the second electrode input end B and negative input E input are arranged at a side of filter housing 1, and cathode output end M and cathode output end E ' are arranged at the opposite side of filter housing 1.
Claims (4)
1. electromagnetic compatibility filter that is applicable to aircraft, comprise input and output, it is characterized in that: also comprise first diode, second diode, bidirectional diode, first inductance, second inductance, the 3rd inductance, first capacitor, second capacitor, the 3rd capacitor and the 4th capacitor, described input comprises first electrode input end, second electrode input end and negative input, described output comprises cathode output end and cathode output end, described first electrode input end is connected with the positive pole of described first diode, described second cathode output end is connected with the positive pole of described second diode, the negative pole of described first diode respectively with the negative pole of described second diode, first end of described bidirectional diode, first end of described first capacitor is connected with first end of described first inductance, second end of described first capacitor is connected with first end of described second capacitor and ground connection, second end of described first inductance is connected with first end of described second inductance and first end of described the 3rd capacitor respectively, second end of described second inductance is connected with first end of described cathode output end and described the 4th capacitor respectively, described negative input respectively with second end of described bidirectional diode, second end of described second capacitor is connected with first end of described the 3rd inductance, second end of described the 3rd inductance respectively with second end of described the 3rd capacitor, second end of described the 4th capacitor is connected with described cathode output end.
2. a kind of electromagnetic compatibility filter that is applicable to aircraft according to claim 1 is characterized in that: the shared toroidal core of described first inductance and described the 3rd inductance.
3. a kind of electromagnetic compatibility filter that is applicable to aircraft according to claim 1, it is characterized in that: described input is arranged at a side of described filter housing.
4. a kind of electromagnetic compatibility filter that is applicable to aircraft according to claim 1, it is characterized in that: described output is arranged at the opposite side of described filter housing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013200806146U CN203104272U (en) | 2013-02-21 | 2013-02-21 | Electromagnetic compatibility filter applicable to aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013200806146U CN203104272U (en) | 2013-02-21 | 2013-02-21 | Electromagnetic compatibility filter applicable to aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203104272U true CN203104272U (en) | 2013-07-31 |
Family
ID=48855647
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013200806146U Expired - Fee Related CN203104272U (en) | 2013-02-21 | 2013-02-21 | Electromagnetic compatibility filter applicable to aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203104272U (en) |
-
2013
- 2013-02-21 CN CN2013200806146U patent/CN203104272U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130731 Termination date: 20190221 |