CN201440168U - E-load machine - Google Patents
E-load machine Download PDFInfo
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- CN201440168U CN201440168U CN 200920133487 CN200920133487U CN201440168U CN 201440168 U CN201440168 U CN 201440168U CN 200920133487 CN200920133487 CN 200920133487 CN 200920133487 U CN200920133487 U CN 200920133487U CN 201440168 U CN201440168 U CN 201440168U
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Abstract
The utility model is suitable for the technology field of power supply testing, which provides an E-load machine; the E-load machine comprises: a reference voltage generating circuit which is connected with standby voltage output circuit of the tested power; a comparative voltage adjusting circuit which is respectively connected with the standby voltage output circuit of the tested power and the reference voltage generating circuit; an amplifying circuit which is respectively connected with the standby voltage output circuit of the tested power and the comparative voltage adjusting circuit; and a feedback circuit which is respectively connected with the amplifying circuit and the comparative voltage adjusting circuit. In the utility model, the E-load machine provides the constant load current for the tested power under standby state, in order to simulate the actual use state of the tested power; the E-load machine has the advantages of small power, small size, low cost and simple operation, and can effectively reduce the testing cost for enterprise.
Description
Technical field
The utility model belongs to the technical field of power supply test, relates in particular to a kind of Electronic Negative carrier aircraft.
Background technology
In order to understand the energy-conservation situation of power supply, the test of a check power supply stand-by power consumption is arranged, its method of testing is to adopt the Electronic Negative carrier aircraft that the constant load electric current of 0.3A is provided for the standby 5V voltage follower circuit of power supply under the holding state, actual user mode with analog power, use the power input of power meter testing power supply then, whether to observe its power input,, show this power supply energy-conserving and environment-protective if less than 3W less than 3W.
But existing Electronic Negative carrier aircraft generally is many groups, and power also has Electronic Negative carrier aircrafts of some single groups all greater than 300W, but its power is all greater than 100W, and simultaneously, these instrument volumes are big, cost an arm and a leg, complicated operation, has increased the testing cost of enterprise.
The utility model content
The purpose of this utility model is to provide a kind of Electronic Negative carrier aircraft, is intended to solve existing Electronic Negative carrier aircraft and has that power is big, volume big, costs an arm and a leg and the problem of complicated operation.
The utility model is achieved in that a kind of Electronic Negative carrier aircraft, and described Electronic Negative carrier aircraft comprises main circuit, and described main circuit comprises:
The reference voltage generating circuit that is connected with the standby voltage output circuit of tested power supply;
The comparative voltage regulating circuit that is connected with reference voltage generating circuit with the standby voltage output circuit of described tested power supply respectively is according to the reference voltage that described reference voltage generating circuit produces, output drive signal;
The amplifying circuit that is connected with the comparative voltage regulating circuit with the standby voltage output circuit of described tested power supply respectively according to described drive signal, amplifies the electric current of the standby voltage output circuit output of tested power supply; And
The feedback circuit that is connected with the comparative voltage regulating circuit with described amplifying circuit is given described comparative voltage regulating circuit with the current fluctuation condition feedback of described amplifying circuit respectively, keeps current stabilization.
In the said structure, described Electronic Negative carrier aircraft also comprises:
The voltage table that is connected with ground with the positive pole of the standby voltage output circuit of described tested power supply respectively;
Be serially connected in the shunt between described feedback circuit and the ground;
The reometer that is connected with the two ends of described shunt;
The blower fan that is used to dispel the heat; And
Be respectively described voltage table, reometer and blower fan the power circuit of power supply is provided.
In the said structure, described reference voltage generating circuit comprises first comparer, first resistance, second resistance, the 3rd resistance, the 4th resistance and accurate stabilivolt, the in-phase input end of described first comparer connects the positive pole of the standby voltage output circuit of tested power supply, the inverting input of described first comparer is leaded up to first resistance and is connect the output terminal of first comparer, another road of the inverting input of described first comparer is by second resistance eutral grounding, the output terminal of described first comparer is by the 3rd resistance and the 4th resistance negative electrode that connects accurate stabilivolt and the control utmost point of serial connection, the negative electrode of described accurate stabilivolt and the control utmost point also connect the in-phase input end of described first comparer simultaneously, the plus earth of described accurate stabilivolt, the tie point of described the 4th resistance and accurate stabilivolt negative electrode connects described comparative voltage regulating circuit.
In the said structure, described comparative voltage regulating circuit comprises the 5th resistance, the 6th adjustable resistance, the 7th adjustable resistance and second comparer, the tie point of described the 4th resistance of first termination of described the 5th resistance and accurate stabilivolt negative electrode, the in-phase input end of described second comparer of second termination of described the 5th resistance, the tie point of second end of described the 5th resistance and the in-phase input end of second comparer is by the 6th adjustable resistance and the 7th adjustable resistance ground connection of serial connection, the positive pole of described second comparer connects the positive pole of the standby voltage output circuit of described tested power supply, the minus earth of described second comparer, the described amplifying circuit of output termination of described second comparer, the inverting input of described second comparer connects described feedback circuit.
In the said structure, described amplifying circuit comprises first triode and second triode, the base stage of described first triode connects the output terminal of described second comparer, the collector of described first triode connects the positive pole of standby voltage output circuit of described tested power supply and the collector of second triode simultaneously, the emitter of described first triode connects the base stage of described second triode, and the emitter of described second triode connects described feedback circuit.
In the said structure, described feedback circuit comprises the 8th resistance and the 9th resistance, first end one tunnel of described the 8th resistance connects the emitter of described second triode, another road connects the inverting input of described second comparer, and second end of described the 8th resistance connects described shunt by described the 9th resistance.
In the utility model, this Electronic Negative carrier aircraft provides the constant load electric current for the tested power supply under the holding state, to simulate the actual user mode of tested power supply, these electronic load facility have the characteristics that power is little, volume is little, cheap and simple to operate, and can reduce the testing cost of enterprise effectively.
Description of drawings
Fig. 1 is the structural drawing of the Electronic Negative carrier aircraft that provides of the utility model embodiment;
Fig. 2 is the examples of circuits figure of the Electronic Negative carrier aircraft that provides of the utility model embodiment.
Embodiment
In order to make the purpose of this utility model, technical scheme and advantage clearer,, the utility model is further elaborated below in conjunction with drawings and Examples.Should be appreciated that specific embodiment described herein only in order to explanation the utility model, and be not used in qualification the utility model.
Fig. 1 shows the structure of the Electronic Negative carrier aircraft that the utility model embodiment provides.
The Electronic Negative carrier aircraft comprises main circuit 100, and main circuit 100 comprises reference voltage generating circuit 101 and comparative voltage regulating circuit 102, amplifying circuit 103 and the feedback circuit 104 that is connected with the standby voltage output circuit of tested power supply.
Wherein, comparative voltage regulating circuit 102 is connected with reference voltage generating circuit 101 with the standby voltage output circuit of tested power supply respectively, according to the reference voltage that reference voltage generating circuit 101 produces, output drive signal; Amplifying circuit 103 is connected with comparative voltage regulating circuit 102 with the standby voltage output circuit of tested power supply respectively, and according to drive signal, the electric current that the standby voltage output circuit of tested power supply is exported amplifies; Feedback circuit 104 is connected with comparative voltage regulating circuit 102 with amplifying circuit 103 respectively, gives comparative voltage regulating circuit 102 with the current fluctuation condition feedback of amplifying circuit 103, keeps current stabilization.
The Electronic Negative carrier aircraft also comprises: the voltage table 200 that is connected with ground with the positive pole of the standby voltage output circuit of tested power supply respectively, and the negative pole of the standby voltage output circuit of tested power supply is ground connection also; Be serially connected in the shunt 300 between feedback circuit 104 and the ground; The reometer 400 that is connected with the two ends of shunt 300; The blower fan 500 that is used to dispel the heat; Be respectively voltage table 200, reometer 400 and blower fan 500 power circuit 600 of power supply is provided.
Fig. 2 shows the examples of circuits structure of the Electronic Negative carrier aircraft that the utility model embodiment provides.
Reference voltage generating circuit 101 comprises the first comparer U1, first resistance R 1, second resistance R 2, the 3rd resistance R 3, the 4th resistance R 4 and accurate stabilivolt D1, the in-phase input end of the first comparer U1 connects the positive pole of the standby voltage output circuit of tested power supply, the inverting input of the first comparer U1 is leaded up to first resistance R 1 and is connect the output terminal of the first comparer U1, another road of the inverting input of the first comparer U1 is by second resistance R, 2 ground connection, the output terminal of the first comparer U1 is by the 3rd resistance R 3 and the 4th resistance R 4 negative electrode that meets accurate stabilivolt D1 and the control utmost point of serial connection, the negative electrode of accurate stabilivolt D1 and the control utmost point also connect the in-phase input end of the first comparer U1 simultaneously, the plus earth of accurate stabilivolt D1, the tie point A of the 4th resistance R 4 and accurate stabilivolt D1 negative electrode connects comparative voltage regulating circuit 102.
Comparative voltage regulating circuit 102 comprises the 5th resistance R 5, the 6th adjustable resistance R6, the 7th adjustable resistance R7 and the second comparer U2, first termination the 4th resistance R 4 of the 5th resistance R 5 and the tie point A of accurate stabilivolt D1 negative electrode, the in-phase input end of second termination, the second comparer U2 of the 5th resistance R 5, the tie point of second end of the 5th resistance R 5 and the in-phase input end of the second comparer U2 is by the 6th adjustable resistance R6 and the 7th adjustable resistance R7 ground connection of serial connection, the positive pole of the second comparer U2 connects the positive pole of the standby voltage output circuit of tested power supply, the minus earth of the second comparer U2, the inverting input of output termination amplifying circuit 103, the second comparer U2 of the second comparer U2 connects feedback circuit 104.
Amplifying circuit 103 comprises the first triode Q1 and the second triode Q2, the base stage of the first triode Q1 connects the output terminal of the second comparer U2, the collector of the first triode Q1 connects the positive pole of standby voltage output circuit of tested power supply and the collector of the second triode Q2 simultaneously, the emitter of the first triode Q1 connects the base stage of the second triode Q2, and the emitter of the second triode Q2 connects feedback circuit 104.
Divide three the tunnel to enter main circuit 100 from the voltage of the positive pole output of the standby voltage output circuit of tested power supply, the first via provides bias voltage for the collector of the first triode Q1 and the second triode Q2, the second the tunnel is the positive pole power supply of the second comparer U2, Third Road is the in-phase input end power supply of the first comparer U1 through resistance, produce the reference voltage of 2.5V at the tie point A of the 4th resistance R 4 and accurate stabilivolt D1 negative electrode by accurate stabilivolt D1 voltage stabilizing, when the 2.5V reference voltage is added to the in-phase input end of the second comparer U2, the output terminal output high level of the second comparer U2, drive the first triode Q1 conducting, the first triode Q1 amplifies the electric current of the positive pole output of the standby voltage output circuit of tested power supply, to drive the second triode Q2 conducting, the second triode Q2 amplifies the electric current of the positive pole output of the standby voltage output circuit of tested power supply again, electric current is through the collector of the second triode Q2, the radiation utmost point, the 8th resistance R 8, the 9th resistance R 9 forms the loop to ground, when output current increases, the dividing potential drop at the 8th resistance R 8 two ends rises, feed back to the inverting input of the second comparer U2, because the voltage that A is ordered is stabilized in 2.5V, as the 6th adjustable resistance R6 and the 7th adjustable resistance R7 fixedly the time, the voltage of the in-phase input end of the second comparer U2 is also fixing, thereby make the output voltage of the second comparer U2 reduce, control the conducting degree of the first triode Q1 and the second triode Q2, make electric current descend, thereby for the tested power supply under the holding state provides the constant load electric current, to simulate the actual user mode of tested power supply.When output current reduced, principle of work repeated no more here with above-mentioned the same.And by regulating the 6th adjustable resistance R6 and the 7th adjustable resistance R7, the load current range that can regulate tested power supply makes in its scope that is controlled at setting.
In the utility model embodiment, this Electronic Negative carrier aircraft provides the constant load electric current for the tested power supply under the holding state, to simulate the actual user mode of tested power supply, these electronic load facility have the characteristics that power is little, volume is little, cheap and simple to operate, and can reduce the testing cost of enterprise effectively.
The above only is preferred embodiment of the present utility model; not in order to restriction the utility model; all any modifications of within spirit of the present utility model and principle, being done, be equal to and replace and improvement etc., all should be included within the protection domain of the present utility model.
Claims (6)
1. an Electronic Negative carrier aircraft is characterized in that, described Electronic Negative carrier aircraft comprises main circuit, and described main circuit comprises:
The reference voltage generating circuit that is connected with the standby voltage output circuit of tested power supply;
The comparative voltage regulating circuit that is connected with reference voltage generating circuit with the standby voltage output circuit of described tested power supply respectively is according to the reference voltage that described reference voltage generating circuit produces, output drive signal;
The amplifying circuit that is connected with the comparative voltage regulating circuit with the standby voltage output circuit of described tested power supply respectively according to described drive signal, amplifies the electric current of the standby voltage output circuit output of tested power supply; And
The feedback circuit that is connected with the comparative voltage regulating circuit with described amplifying circuit is given described comparative voltage regulating circuit with the current fluctuation condition feedback of described amplifying circuit respectively, keeps current stabilization.
2. Electronic Negative carrier aircraft as claimed in claim 1 is characterized in that, described Electronic Negative carrier aircraft also comprises:
The voltage table that is connected with ground with the positive pole of the standby voltage output circuit of described tested power supply respectively;
Be serially connected in the shunt between described feedback circuit and the ground;
The reometer that is connected with the two ends of described shunt;
The blower fan that is used to dispel the heat; And
Be respectively described voltage table, reometer and blower fan the power circuit of power supply is provided.
3. Electronic Negative carrier aircraft as claimed in claim 2, it is characterized in that, described reference voltage generating circuit comprises first comparer, first resistance, second resistance, the 3rd resistance, the 4th resistance and accurate stabilivolt, the in-phase input end of described first comparer connects the positive pole of the standby voltage output circuit of tested power supply, the inverting input of described first comparer is leaded up to first resistance and is connect the output terminal of first comparer, another road of the inverting input of described first comparer is by second resistance eutral grounding, the output terminal of described first comparer is by the 3rd resistance and the 4th resistance negative electrode that connects accurate stabilivolt and the control utmost point of serial connection, the negative electrode of described accurate stabilivolt and the control utmost point also connect the in-phase input end of described first comparer simultaneously, the plus earth of described accurate stabilivolt, the tie point of described the 4th resistance and accurate stabilivolt negative electrode connects described comparative voltage regulating circuit.
4. Electronic Negative carrier aircraft as claimed in claim 3, it is characterized in that, described comparative voltage regulating circuit comprises the 5th resistance, the 6th adjustable resistance, the 7th adjustable resistance and second comparer, the tie point of described the 4th resistance of first termination of described the 5th resistance and accurate stabilivolt negative electrode, the in-phase input end of described second comparer of second termination of described the 5th resistance, the tie point of second end of described the 5th resistance and the in-phase input end of second comparer is by the 6th adjustable resistance and the 7th adjustable resistance ground connection of serial connection, the positive pole of described second comparer connects the positive pole of the standby voltage output circuit of described tested power supply, the minus earth of described second comparer, the described amplifying circuit of output termination of described second comparer, the inverting input of described second comparer connects described feedback circuit.
5. Electronic Negative carrier aircraft as claimed in claim 4, it is characterized in that, described amplifying circuit comprises first triode and second triode, the base stage of described first triode connects the output terminal of described second comparer, the collector of described first triode connects the positive pole of standby voltage output circuit of described tested power supply and the collector of second triode simultaneously, the emitter of described first triode connects the base stage of described second triode, and the emitter of described second triode connects described feedback circuit.
6. Electronic Negative carrier aircraft as claimed in claim 5, it is characterized in that, described feedback circuit comprises the 8th resistance and the 9th resistance, first end one tunnel of described the 8th resistance connects the emitter of described second triode, another road connects the inverting input of described second comparer, and second end of described the 8th resistance connects described shunt by described the 9th resistance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200920133487 CN201440168U (en) | 2009-07-01 | 2009-07-01 | E-load machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200920133487 CN201440168U (en) | 2009-07-01 | 2009-07-01 | E-load machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201440168U true CN201440168U (en) | 2010-04-21 |
Family
ID=42544831
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200920133487 Expired - Fee Related CN201440168U (en) | 2009-07-01 | 2009-07-01 | E-load machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201440168U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102749592A (en) * | 2012-07-04 | 2012-10-24 | 尚艳燕 | Electron loading machine |
| CN115185326A (en) * | 2021-04-07 | 2022-10-14 | 炬芯科技股份有限公司 | Active load circuit and active load module |
-
2009
- 2009-07-01 CN CN 200920133487 patent/CN201440168U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102749592A (en) * | 2012-07-04 | 2012-10-24 | 尚艳燕 | Electron loading machine |
| CN102749592B (en) * | 2012-07-04 | 2015-07-15 | 尚艳燕 | Electron loading machine |
| CN115185326A (en) * | 2021-04-07 | 2022-10-14 | 炬芯科技股份有限公司 | Active load circuit and active load module |
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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 |
Granted publication date: 20100421 Termination date: 20150701 |
|
| EXPY | Termination of patent right or utility model |