CN112054684A - Ultrahigh-voltage aerospace switch power supply circuit topological structure - Google Patents
Ultrahigh-voltage aerospace switch power supply circuit topological structure Download PDFInfo
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- CN112054684A CN112054684A CN202010808264.5A CN202010808264A CN112054684A CN 112054684 A CN112054684 A CN 112054684A CN 202010808264 A CN202010808264 A CN 202010808264A CN 112054684 A CN112054684 A CN 112054684A
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M3/00—Conversion of dc power input into dc power output
- H02M3/22—Conversion of dc power input into dc power output with intermediate conversion into ac
- H02M3/24—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters
- H02M3/28—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac
- H02M3/325—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal
- H02M3/335—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
- H02M3/33507—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of the output voltage or current, e.g. flyback converters
- H02M3/33523—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of the output voltage or current, e.g. flyback converters with galvanic isolation between input and output of both the power stage and the feedback loop
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M1/00—Details of apparatus for conversion
- H02M1/14—Arrangements for reducing ripples from dc input or output
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M7/00—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output
- H02M7/02—Conversion of ac power input into dc power output without possibility of reversal
- H02M7/04—Conversion of ac power input into dc power output without possibility of reversal by static converters
- H02M7/06—Conversion of ac power input into dc power output without possibility of reversal by static converters using discharge tubes without control electrode or semiconductor devices without control electrode
- H02M7/10—Conversion of ac power input into dc power output without possibility of reversal by static converters using discharge tubes without control electrode or semiconductor devices without control electrode arranged for operation in series, e.g. for multiplication of voltage
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Dc-Dc Converters (AREA)
Abstract
The invention belongs to the technical field of aerospace power supplies and power supply and distribution, and relates to a circuit topology structure of an ultrahigh-voltage aerospace switch power supply. The invention is composed of a forward and reverse exciting circuit and a voltage-multiplying rectifying circuit. The circuit topology of the ultrahigh-voltage aerospace switch power supply can realize kilovolt output voltage, has the advantages of simple topological structure and small volume, and reduces the volume and weight of the transformer. The circuit topology is suitable for a switching power supply with kilovolt-level output voltage and milliampere-level output current.
Description
Technical Field
The invention relates to a circuit topology structure of an ultrahigh-voltage aerospace switch power supply, belonging to the technical field of aerospace power supplies and power supply and distribution.
Background
With the technical progress of military aerospace, the battle principle of 'integration of land, sea, air and day' in the future war is further developed, and 'control of the sky' and 'control of the information' are the key for winning the future war. On the basis, various reconnaissance and communication satellites are rapidly developed. The spacecraft height control device realizes the control of the ground height of the spacecraft in the lift-off process through the ultrahigh-voltage aerospace power supply. The commercial aerospace small satellite electric propulsion system has the characteristics of small power, light weight and high performance, and the development of a low-power ultrahigh-voltage aerospace power supply is urgently needed. The traveling wave tube power amplifier is an important high power amplifier element in a reconnaissance and communication satellite-borne system. The traveling wave tube is widely applied to the fields of radar, electronic countermeasure, communication, aerospace and the like, and is a core device for microwave power amplification.
The aerospace high-voltage power supply has the advantages that the aerospace high-voltage power supply is high in output voltage, the transformer is adopted for boosting, the size is large, the distributed capacitance is large, the insulation problem is obvious, and the development of the aerospace high-voltage power supply is limited. At present, most of ultrahigh voltage power supply modules in the aerospace field of China adopt imported thick film power supplies, and the risks of uncontrollable technical process and the like exist.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects in the prior art are overcome, the topological structure of the circuit of the ultra-high voltage aerospace switch power supply is provided, the problem of large stress of a high-voltage direct-current power supply switch is solved, the feasibility of an isolated aerospace high-voltage power supply is realized, and the ultra-high voltage aerospace switch power supply is suitable for a high-performance low-current high-voltage direct-current power supply.
The technical solution of the invention is as follows: a topological structure of an ultrahigh-voltage aerospace switch power supply circuit comprises a forward and backward excitation circuit and a voltage doubling rectifying circuit;
the positive and negative excitation circuit is used for generating positive and negative alternate pulse waveforms and realizing the transmission of positive and negative alternate pulse energy in a magnetic isolation mode;
the voltage-multiplying rectification circuit is used for increasing the voltage at two ends of the isolation transformer T1, reducing the electrical stress of the isolation transformer T1 and components through the voltage multiplication of a capacitor and a diode, realizing the pumping of output voltage and achieving the voltage output of kilovolt level.
Further, the forward and reverse excitation circuit comprises an input power Vin, a power switch tube Q1 and an isolation transformer T1; the positive stage of the input power Vin is connected with the dotted terminal of the isolation transformer T1, the negative pole of the input voltage Vin is connected with the source terminal of the power switch tube Q1, and the drain of the power switch tube Q1 is connected with the non-dotted terminal of the isolation transformer T1.
Further, the voltage-multiplying rectification circuit comprises a plurality of voltage-multiplying units connected in parallel; each voltage doubling unit comprises two capacitors and two diodes.
Further, the dotted terminal of the secondary winding of the isolating converter T1 is connected to one terminal of the capacitor C1, and the non-dotted terminal of the secondary winding is connected to the cathode of the diode D1 and one terminal of the capacitor C2.
Further, the voltage-doubling rectifying circuit comprises a diode D1, a diode D2, a diode D3, a diode D4, a diode D5, a diode D6, a capacitor C1, a capacitor C2, a capacitor C3, a capacitor C4, a capacitor C5 and a capacitor C6; the other end of the capacitor C1 is connected with an anode of the diode D1, a cathode of the diode D2 and one end of the capacitor C3, the other end of the capacitor C2 is connected with an anode of the diode D2, a cathode of the diode D3 and one end of the capacitor C4, the other end of the capacitor C3 is connected with an anode of the diode D3, a cathode of the diode D4 and one end of the capacitor C5, the other end of the capacitor C4 is connected with an anode of the diode D4, a cathode of the diode D5 and one end of the capacitor C6, the other end of the capacitor C5 is connected with an anode of the diode D5 and a cathode of the diode D6, the other end of the capacitor C6 is connected with an anode of the diode D6, and so on untiln+1And diode Dn+1And n is an odd number.
Further, a switching tube Q1 in the forward and flyback circuit is a high-frequency power switching device with anti-radiation characteristic, specifically an N-channel field effect transistor or an N-type triode.
Furthermore, the positive end of the output voltage is connected with the non-dotted terminal of the isolation transformer T1, and the negative end of the output voltage is connected with the capacitor Cn+1And a diode Dn+1The anode of the power supply is connected, and the output voltage is positive voltage output; negative end of output voltage and non-homonymous end of isolation transformer T1Connected to output voltage positive terminal and capacitor Cn+1And a diode Dn+1The anode of the power supply is connected, and the output voltage is negative voltage output.
Further, the magnetic reset circuit is not included in the forward and reverse excitation circuit.
Further, the output voltage is a voltage difference value of several hundreds volts to several tens of thousands volts.
Compared with the prior art, the invention has the advantages that:
(1) the invention adopts a forward and reverse excitation circuit topology of a primary circuit topology of a transformer. The forward and backward exciting converter is a converter with high efficiency and high power density, is derived on the basis of a forward exciting or flyback converter, has the characteristics of simple circuit and few components, does not need to increase a complex magnetic circuit, and can reduce output voltage ripples. Compared with a forward circuit, the topology does not need a magnetic reset circuit; compared with a flyback circuit, the topology has the advantages of large output power and small output current ripple.
(2) The secondary side circuit topology of the transformer adopted by the invention is a voltage doubling rectifying circuit, and the topology can effectively reduce the volume of the transformer and is suitable for a low-current high-voltage direct-current power supply.
(3) Compared with the optical coupling isolation adopted in the traditional sense, the electromagnetic isolation adopted by the invention is influenced by space effects such as space irradiation and single particles, and larger drift can occur in the photoelectric conversion process.
Drawings
FIG. 1 is a schematic circuit diagram of the present invention;
FIG. 2 is a schematic diagram of the circuit of the present invention showing the operation of the switch tube;
FIG. 3 is a schematic diagram of the circuit of the present invention with the switching tube disconnected;
Detailed Description
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
The invention relates to a circuit topology of an extra-high voltage aerospace switch power supply, which adopts a magnetic isolation technology, namely the input and the output (positive or negative output and ground) of a power supply module are completely isolated electrically, the isolation is realized by adopting a magnetic field, and the power supply adopting the magnetic isolation technology is basically not influenced by a space effect.
The circuit topology structure of the ultra-high voltage aerospace switching power supply provided by the embodiment of the application is further described in detail with reference to the drawings in the specification, and the specific implementation manner may include (as shown in fig. 1): a forward and reverse exciting circuit and a voltage doubling rectifying circuit.
In the scheme provided by the embodiment of the application, the forward and reverse excitation circuit is used for generating a positive and negative alternate pulse waveform, and the transmission of positive and negative alternate pulse energy is realized in a magnetic isolation mode.
Further, in a possible implementation scheme, the flyback converter includes an input power Vin, an isolation transformer T1, and a power switch Q1, where a positive stage of the input power Vin is connected to a dotted terminal of the isolation transformer T1, a negative terminal of the input voltage Vin is connected to a source terminal of the power switch Q1, and a drain of the power switch Q1 is connected to a non-dotted terminal of the isolation transformer T1.
Optionally, in a possible implementation scheme, the switching tube Q1 in the flyback circuit is a high-frequency power switching device with an anti-radiation characteristic, specifically, an N-channel field effect transistor or an N-type triode.
Further, the magnetic reset circuit is not included in the forward and reverse excitation circuit.
In the scheme provided by the embodiment of the application, the voltage-multiplying rectification circuit is used for increasing the voltage at two ends of the isolation transformer T1, and reducing the electrical stress of the isolation transformer T1 and components through the voltage multiplication of the capacitor and the diode, so that the pumping of the output voltage is realized, and the voltage output of kilovolt level is achieved.
In one possible implementation scheme, the voltage-doubling rectifying circuit comprises a plurality of voltage-doubling units connected in parallel; each voltage doubling unit comprises two capacitors and two diodes.
Optionally, the dotted terminal of the secondary winding of the isolating converter T1 is connected to one terminal of the capacitor C1, and the non-dotted terminal of the secondary winding is connected to the cathode of the diode D1 and one terminal of the capacitor C2.
Further, the voltage-doubling rectifying circuit of the secondary side of the isolation transformer T comprises a diode D, a capacitor C and a capacitor C, wherein the dotted terminal of the secondary side of the isolation transformer T is connected with one end of the capacitor C, the non-dotted terminal of the secondary side of the isolation transformer T is connected with the cathode of the diode D and one end of the capacitor C, the other end of the capacitor C is connected with the anode of the diode D, the cathode of the diode, the other end of the capacitor C5 is connected with the anode of the diode D5 and the cathode of the diode D6, the other end of the capacitor C6 is connected with the anode of the diode D6, and so on until the capacitor Cn +1 and the diode Dn +1(n is an odd number).
Further, in a possible implementation scheme, the positive output voltage terminal is connected with the non-dotted terminal of the isolation transformer T1, and the negative output voltage terminal is connected with the capacitor Cn+1And a diode Dn+1The anode of the power supply is connected, and the output voltage is positive voltage output; the negative end of the output voltage is connected with the non-dotted terminal of the isolation transformer T1, and the positive end of the output voltage is connected with the capacitor Cn+1And a diode Dn+1The anode of the power supply is connected, and the output voltage is negative voltage output.
Further, the output voltage is a voltage difference value of several hundreds volts to several tens of thousands volts.
As shown in fig. 1, a half-wave rectifier circuit composed of a diode and a capacitor is connected in series, and each half-wave rectifier circuit is connected in series, so that the voltage pump can be doubled. The alternating current repeatedly charges and discharges the capacitor through the diode in each half cycle, and the direct current output voltage which is several times of the input voltage can be obtained after several cycles.
The working principle of the invention is as follows:
when the alternating current works in the positive half cycle, as shown in fig. 2, the power supply charges the C1 through D1; in the next half cycle, as shown in fig. 3, D1 is turned off and the power supply charges C2 through D2 simultaneously with the voltage on C1, and if the capacitance in the circuit is large enough, the voltage on C2 may rise to twice the supply voltage after several cycles. In the next positive half cycle, C3 charges to twice the supply voltage under the combined action of the power supply, C1 and C2. By this, the charging voltage of each capacitor is twice the power supply voltage, so the output voltage is the sum of the series connection of C2, C4 and C6, i.e. 6 times the input power supply voltage, and so on.
The invention provides a circuit topology of an ultrahigh-voltage aerospace switch power supply, which greatly reduces the electrical stress of an isolation converter and components, realizes the output of the ultrahigh-voltage aerospace power supply, and has the characteristics of high power density, high output voltage, low output ripple waves and the like. The method has wide application prospect in devices such as spacecraft height control devices, commercial space small satellite electric propulsion systems, traveling wave tubes and the like.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (9)
1. The utility model provides a super high voltage aerospace switching power supply circuit topological structure which characterized in that: the voltage doubling rectifier circuit comprises a forward flyback circuit and a voltage doubling rectifier circuit;
the positive and negative excitation circuit is used for generating positive and negative alternate pulse waveforms and realizing the transmission of positive and negative alternate pulse energy in a magnetic isolation mode;
the voltage-multiplying rectification circuit is used for increasing the voltage at two ends of the isolation transformer T1, reducing the electrical stress of the isolation transformer T1 and components through the voltage multiplication of a capacitor and a diode, realizing the pumping of output voltage and achieving the voltage output of kilovolt level.
2. The circuit topology structure of the extra-high voltage aerospace switching power supply of claim 1, wherein: the forward and reverse excitation circuit comprises an input power source Vin, a power switch tube Q1 and an isolation transformer T1; the positive stage of the input power Vin is connected with the dotted terminal of the isolation transformer T1, the negative pole of the input voltage Vin is connected with the source terminal of the power switch tube Q1, and the drain of the power switch tube Q1 is connected with the non-dotted terminal of the isolation transformer T1.
3. The circuit topology structure of the extra-high voltage aerospace switching power supply of claim 2, wherein: the voltage-multiplying rectification circuit comprises a plurality of voltage-multiplying units which are connected in parallel; each voltage doubling unit comprises two capacitors and two diodes.
4. The circuit topology structure of the extra-high voltage aerospace switching power supply of claim 3, wherein: the dotted terminal of the secondary winding of the isolation converter T1 is connected with one end of a capacitor C1, and the non-dotted terminal of the secondary winding is connected with the cathode of a diode D1 and one end of a capacitor C2.
5. The circuit topology structure of the extra-high voltage aerospace switching power supply of claim 4, wherein: the voltage-multiplying rectification circuit comprises a diode D1, a diode D2, a diode D3, a diode D4, a diode D5, a diode D6, a capacitor C1, a capacitor C2, a capacitor C3, a capacitor C4, a capacitor C5 and a capacitor C6; the other end of the capacitor C1 is connected with an anode of the diode D1, a cathode of the diode D2 and one end of the capacitor C3, the other end of the capacitor C2 is connected with an anode of the diode D2, a cathode of the diode D3 and one end of the capacitor C4, the other end of the capacitor C3 is connected with an anode of the diode D3, a cathode of the diode D4 and one end of the capacitor C5, and the other end of the capacitor C4 is connected with an anode of the diode D4, a cathode of the diode D5 and electricityOne end of a capacitor C6 is connected, the other end of a capacitor C5 is connected with the anode of the diode D5 and the cathode of the diode D6, the other end of a capacitor C6 is connected with the anode of the diode D6, and so on until the capacitor C6 is connectedn+1And diode Dn+1And n is an odd number.
6. The circuit topology structure of the extra-high voltage aerospace switching power supply of claim 2, wherein: the switching tube Q1 in the forward and reverse excitation circuit is a high-frequency power switching device with anti-irradiation characteristic, specifically an N-channel field effect tube or an N-type triode.
7. The circuit topology structure of the extra-high voltage aerospace switching power supply of claim 2, wherein: the positive end of the output voltage is connected with the non-dotted terminal of the isolation transformer T1, and the negative end of the output voltage is connected with the capacitor Cn+1And a diode Dn+1The anode of the power supply is connected, and the output voltage is positive voltage output; the negative end of the output voltage is connected with the non-dotted terminal of the isolation transformer T1, and the positive end of the output voltage is connected with the capacitor Cn+1And a diode Dn+1The anode of the power supply is connected, and the output voltage is negative voltage output.
8. The circuit topology structure of the extra-high voltage aerospace switching power supply of claim 1, wherein: the positive and negative excitation circuit does not comprise a magnetic reset circuit.
9. The circuit topology structure of the extra-high voltage aerospace switching power supply of claim 1, wherein: the output voltage is a voltage difference value of several hundred volts to several ten thousand volts.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010808264.5A CN112054684A (en) | 2020-08-12 | 2020-08-12 | Ultrahigh-voltage aerospace switch power supply circuit topological structure |
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| CN202010808264.5A CN112054684A (en) | 2020-08-12 | 2020-08-12 | Ultrahigh-voltage aerospace switch power supply circuit topological structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113612384A (en) * | 2021-01-05 | 2021-11-05 | 青岛鼎信通讯股份有限公司 | Negative pressure and voltage-multiplying power supply solution applied to products in power industry |
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