CN2684452Y - Moulding board type static power converter for aviation - Google Patents
Moulding board type static power converter for aviation Download PDFInfo
- Publication number
- CN2684452Y CN2684452Y CN 200420025705 CN200420025705U CN2684452Y CN 2684452 Y CN2684452 Y CN 2684452Y CN 200420025705 CN200420025705 CN 200420025705 CN 200420025705 U CN200420025705 U CN 200420025705U CN 2684452 Y CN2684452 Y CN 2684452Y
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- inverter
- circuit
- control circuit
- converter
- power
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Abstract
The utility model discloses a moulding board type static power converter for aviation including a backing stage direct current converter connecting to a next cascade inverter. The utility model is characterized in that the backing stage direct current converter is the direct current power supply modular construction which is composed of four completely independent and isolated direct current converters, the next cascade inverter comprises a power circuit, a control circuit and an output filter circuit. Wherein, the inverter power circuit is connected into a tandem type structure by four single phase inverters, each single phase inverter is formed into an inversion bridge type circuit by four power switch tubes. The control circuit comprises a voltage electric current bicyclo control circuit and a four-way inversion signal generator. The voltage ripple outputting from each inversion bridge is two times as big as the frequency of the power switch tubes, the voltage ripple frequency outputting from four inversion bridges is eight times as big as the frequency of the power switch tubes, the feedback signal of a double closed-loop control circuit takes from the voltage and the electric current of a filtration capacitance. Compared with prior art, the static power converter has the advantages of high circuit modularity degree, low voltage stress of interior heat-source distribution and power device, high efficiency, reliable operation, hard external characteristic, favorable load characteristic, strong non-linear load capacity and simply control.
Description
Technical field
The utility model relates to a kind of Aviation Static Inverter
Background technology
1. the problem that traditional Aviation Static Inverter exists
Aviation Static Inverter has experienced three developing stage: 1. low frequency isolation technology mainly contains square-wave inverter formula circuit structure, Boost converter and the synthetic inverter bridge combined electrical line structure of staircase waveform boost; 2. single-ended reverse exciting FLYBACK converter and Sine Pulse Width Modulation inverter combined electrical line structure; 3. the box-like circuit structure of soft switches set.
The low frequency isolation static converter has square wave formula static converter and two kinds of patterns of multipleization static converter.Square wave formula static converter mainly is made up of push-pull circuit, output low frequency transformer and alternating current filter, have simple in structure and the reliability advantages of higher, but low pressure input and square wave output, make the back must add heavy alternating current filter and low-frequency transformer, this will inevitably strengthen the volume weight of system, reduces conversion efficiency.Shortcomings such as multipleization static converter is made of boost inverter and the synthetic inverter of staircase waveform, and the low frequency output transformer is arranged equally, and volume weight is big.
Sinusoidal pulse width modulation (SPWM) static converter is made up of prime DC converter and back level SPWM inverter.This circuit will be imported the isolation of boosting of the high frequency dc to dc converter of 28V voltage by prime earlier, will export the high voltage direct current direct inverse then and become 115V/400Hz and exchange output.This current transformer has following advantage: utilize high frequency transformer to realize electrical isolation, back level inverter is operated in the SPWM mode, and the output waveform harmonic content is little, can more significantly reduce the volume of output filter, thereby reduces the volume weight of system.The prime of system and back level adopt independent closed-loop control respectively, have improved the response speed of system.But the inverter power device of sort circuit is operated in the high-voltage switch state, and electromagnetic interference is serious, and is subjected to the restriction of power device, is difficult to further improve the switching frequency and the overall efficiency of system.
The box-like static converter of soft switches set also is to be made of high-frequency isolation DC converter and high-frequency inverter, the prime DC converter adopts soft switch solution, the output pulse direct current, back level power device of inverter switch transition during the zero passage of pulse direct current, therefore also be soft switch, this static converter switching frequency is than preceding a kind of increasing, and the current transformer overall performance also increases, but circuit and control are complicated.
Take a broad view of several static converter schemes of introducing previously, though adopt different circuit topologies, different transformation of electrical energy modes is not all broken away from the concentration of energy processing mode, and this causes: the thermal losses of circuit is concentrated relatively, and thermal design difficulty, system are difficult to optimize; The power density of circuit is low; Any power component damage system is a cisco unity malfunction in the circuit; Can not use the technology manufacturing of chip module technology and integrated circuit as the DC/DC module.
2. domestic and international solution of the above problems
The Aviation Static Inverter that realizes having the distribution type electric energy transform characteristics can adopt the parallel technology of inverter, the parallel connection of inverter (as Fig. 1) can reduce the power device current stress, realize the energy distributions conversion to a certain extent, and can realize more high-power output and redundancy properties easily.
3. the limitation of such scheme
The parallel connection of inverter can realize the conversion of static converter energy distributions, but its control is complicated, and the parallel technology of inverter is at present still among research and development.
The utility model content
The purpose of this utility model is to develop and a kind ofly can overcomes the defective that above-mentioned prior art exists, and it is simple and convenient to have control, and the voltage stress of power device is low, efficient is high, the Aviation Static Inverter of internal structure modularization, reliable operation.
Realize that above-mentioned purpose templating Aviation Static Inverter is connected in back level cascaded inverter by the prime DC converter and is formed, the prime DC converter is independently of one another fully by four, isolate mutually, the DC power supplier that DC converter constituted of specification unanimity constitutes, and each DC converter all has separately an independently cover closed control circuit; Back level cascaded inverter is made up of inverter power circuit, control circuit and output filter, and wherein the inverter power circuit is connected into the tandem type structure by four single-phase inverters, and each single-phase inverter constitutes the inversion bridge circuit by four power switch pipes; Control circuit comprises the electric current and voltage dual-loop control circuit, and wherein current regulator output links to each other with the inverter signal generator that comprises baseline sinusoidal wave generation circuit and four tunnel phase shift triangle wave circuits that is connected in four single-phase inverters respectively.
Description of drawings
Fig. 1 is the schematic diagram of two inverter parallel connections.
Fig. 2 is a templating Aviation Static Inverter structured flowchart of the present utility model.
Fig. 3 is of the present utility model four unit cascaded inverter circuit schematic diagrams.
Fig. 4 is the control circuit block diagram.
Fig. 5 is that baseline sinusoidal wave produces circuit theory diagrams.
Fig. 6 is four tunnel phase shift triangle wave generating circuits, and wherein figure (a) is a square wave triangular wave change-over circuit,
Figure (b) is the circuit and square-wave of four tunnel phase shifts, 45 degree.
Fig. 7 electric current and voltage dual-loop control circuit
Fig. 8 relatively hands over and cuts and dead-zone circuit.
Fig. 9 auxiliary power circuit.
Designation among Fig. 3: S
11～S
14, S
21～S
24, S
31～S
34, S
41～S
44Be power switch pipe.Designation among Fig. 4: k
If---current feedback coefficient, k
Vf---the Voltage Feedback coefficient.Other symbol is conventional sign among the above-mentioned figure.
Embodiment
By Fig. 2 and Fig. 3 as can be known, concrete composition of the present utility model comprises prime DC converter, back level cascaded inverter, control circuit, output filter, accessory power supply and protective circuit.The DC link of prime is connected in the single-phase inverter of four cascades of back level inversion link separately by four DC converter fully independent, that isolate mutually, each single-phase inverter by two power switch pipes (as switching tube S
11, S
14) partner brachium pontis and two other power switch pipe be (as switching tube S
13, S
12) form another brachium pontis is constituted the inversion bridge circuit.
Control circuit comprises that being connected in the electric current and voltage dual-loop control circuit that current regulator forms by voltage regulator is connected in four road inverter signal generation circuit that link to each other with four single-phase inverters respectively.Four road inverter signal generators comprise baseline sinusoidal wave generator and four tunnel phase shift triangle wave generating circuits.It is 400Hz baseline sinusoidal wave generation circuit that baseline sinusoidal wave shown in Figure 5 produces circuit, four tunnel phase shift triangle wave generating circuits shown in Figure 6 comprise the circuit and square-wave of four tunnel phase shifts, 45 degree of the square wave triangular wave change-over circuit of figure (a) and figure (b), promptly generate phase shift 45 degree four road square waves by figure (b) and obtain four tunnel phase shift triangular carriers by the square wave triangular wave change-over circuit of scheming (a) again.
Electric current and voltage dual-loop control circuit shown in Figure 7 in dual-loop control circuit, is handed over output voltage and filter capacitor current feedback to intercept out the inverter control signal through the opposite modulating wave of closed-loop adjustment output two-way phase place and triangular wave.
Auxiliary power circuit shown in Figure 8, utilize the LT1076 chip 18～32V input is converted to ± output of 15V two-way uses for control circuit.
What above Fig. 5～Fig. 9 adopted is prior art.
By Fig. 2～Fig. 9 as seen, can realize the circuit boardization of static converter internal structure on the utility model patent working, its inside by four independent direct current conversion modules, be connected in four inverter bridge module, one separately and constitute with control circuit board and output filter plate that four inverter bridge module link to each other respectively.
The course of work of the present utility model is:
After input contactor closure, four DC converter of prime and the accessory power supply of inverter are started working, after accessory power supply is working properly, each inverter bridge converts the direct current of the output of DC converter to SPWM output, cascade stack back is by output AC filter elimination high order harmonic component wherein, obtain sine wave output, output voltage then passes through the voltage and current double closed-loop control stabilization of inverter at 115V.
Claims (5)
1, a kind of templating Aviation Static Inverter comprises that the prime DC converter is connected in back level cascaded inverter, it is characterized in that described prime DC converter is independently of one another by four, isolate mutually, the direct current modular structure that DC converter constituted of specification unanimity, described back level cascaded inverter comprises inverter power circuit and the control circuit and the output filter circuit that link to each other with the inverter power circuit, wherein the inverter power circuit is connected into the tandem type structure by four single-phase inverters, and each single-phase inverter is formed another brachium pontis is constituted the inversion bridge circuit by partner brachium pontis and two other power switch pipe of two power switch pipes.
2, templating Aviation Static Inverter according to claim 1, it is characterized in that its inside by four independent direct current conversion modules, be connected in four inverter bridge module, one separately and constitute with control circuit board and output filter plate that four inverter bridge module link to each other respectively.
3, templating Aviation Static Inverter according to claim 1 and 2 is characterized in that control circuit comprises that being connected in the electric current and voltage dual-loop control circuit that current regulator forms by voltage regulator is connected in four road inverter signal generation circuit that link to each other with four single-phase inverters respectively.
4, templating Aviation Static Inverter according to claim 3 is characterized in that four road inverter signal generation circuit comprise baseline sinusoidal wave generator and four tunnel phase shift triangle wave circuits.
5, templating Aviation Static Inverter according to claim 3 is characterized in that four tunnel phase shift triangle wave circuits comprise that generating phase shift 45 spends four tunnel circuit and square-wave and square wave triangular wave change-over circuits.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420025705 CN2684452Y (en) | 2004-03-25 | 2004-03-25 | Moulding board type static power converter for aviation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420025705 CN2684452Y (en) | 2004-03-25 | 2004-03-25 | Moulding board type static power converter for aviation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2684452Y true CN2684452Y (en) | 2005-03-09 |
Family
ID=34607083
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200420025705 Expired - Fee Related CN2684452Y (en) | 2004-03-25 | 2004-03-25 | Moulding board type static power converter for aviation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2684452Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101847939A (en) * | 2009-03-26 | 2010-09-29 | Abb研究有限公司 | Method for controlling single-phase dc/ac converters and converter arrangement |
| CN102788906A (en) * | 2012-07-24 | 2012-11-21 | 江苏省科学技术情报研究所 | High-frequency impedance tester |
-
2004
- 2004-03-25 CN CN 200420025705 patent/CN2684452Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101847939A (en) * | 2009-03-26 | 2010-09-29 | Abb研究有限公司 | Method for controlling single-phase dc/ac converters and converter arrangement |
| CN101847939B (en) * | 2009-03-26 | 2012-12-19 | Abb研究有限公司 | Method for controlling single-phase dc/ac converters and converter arrangement |
| CN102788906A (en) * | 2012-07-24 | 2012-11-21 | 江苏省科学技术情报研究所 | High-frequency impedance tester |
| CN102788906B (en) * | 2012-07-24 | 2014-05-28 | 江苏省科学技术情报研究所 | High-frequency impedance tester |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |