CN112003263A - Redundant secondary power supply circuit for combination of satellite-borne fiber-optic gyroscope - Google Patents
Redundant secondary power supply circuit for combination of satellite-borne fiber-optic gyroscope Download PDFInfo
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- CN112003263A CN112003263A CN202010975202.3A CN202010975202A CN112003263A CN 112003263 A CN112003263 A CN 112003263A CN 202010975202 A CN202010975202 A CN 202010975202A CN 112003263 A CN112003263 A CN 112003263A
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- circuit
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- optic gyroscope
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- 239000013307 optical fiber Substances 0.000 claims description 11
- 230000001012 protector Effects 0.000 claims description 7
- 230000001629 suppression Effects 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000000835 fiber Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J1/00—Circuit arrangements for DC mains or DC distribution networks
- H02J1/10—Parallel operation of DC sources
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Dc-Dc Converters (AREA)
Abstract
The invention discloses a redundant secondary power supply circuit for a satellite-borne fiber-optic gyroscope combination, which comprises: fuse protection circuit, anti-surge circuit, EMI wave filter, a plurality of DC/DC converters. The primary power supply is converted into a secondary power supply through a plurality of DC/DC converters after passing through the fuse protection circuit, the anti-surge circuit and the EMI filter in sequence. The fuse protection circuit is connected with the primary power supply positive circuit, the output end of the fuse protection circuit is connected with the input end circuit of the anti-surge circuit, and overvoltage or/and overcurrent protection is performed on the load circuit; the output end of the anti-surge circuit is connected with the input end of the EMI filter, and the EMI filter filters interference frequency signals in the circuit and outputs a primary power supply with stable frequency. The secondary power supply of the power supply is output through the anti-surge circuit and the EMI filter, so that the lower reflection ripple waves output by the fiber-optic gyroscope combination in the load circuit are ensured, and meanwhile, the safety and the reliability of the fiber-optic gyroscope combination are ensured by the fuse protection circuit.
Description
Technical Field
The invention relates to a satellite attitude control system, in particular to a secondary power supply circuit for optical fiber gyroscope combination of a satellite.
Background
The prior optical fiber gyroscope combined secondary power supply circuit used on the satellite has two types, namely full redundancy and main and standby power supply cold backup. The full-redundancy scheme of the secondary power supply circuit adopts an independent EMI filter and a DC/DC converter of each channel to supply power, so that the secondary power supply circuit is complex, the number of the EMI filters and the number of the DC/DC converters are large, and the cost is high. The main and standby power supply cold backup scheme is that the main and standby power supplies are switched by adopting a relay, and a power supply switching circuit and a power supply parallel circuit are connected, so that the design of a backflow prevention circuit is complex, and the miniaturization of the fiber-optic gyroscope combination is not facilitated.
Disclosure of Invention
Aiming at the defects in the prior art, the redundant secondary power supply circuit for the combination of the satellite-borne fiber-optic gyroscope provided by the invention can effectively reduce the using number of the power supply modules of the combination of the fiber-optic gyroscope, reduce the overall power consumption and ensure the service life and the reliability.
In order to solve the above technical problem, the present invention provides a redundant secondary power circuit for a satellite-borne fiber gyroscope assembly, comprising: the protection circuit of the fuse, prevent the surge circuit, EMI electric-wave filter, multiple DC/DC converters;
the primary power supply is converted into a secondary power supply through a plurality of DC/DC converters after passing through a fuse protector circuit, an anti-surge circuit and an EMI filter in sequence to supply power to a load circuit;
the fuse protection circuit is connected with a primary power supply positive circuit, the output end of the fuse protection circuit is connected with the input end circuit of the anti-surge circuit, the fuse protection circuit and the anti-surge circuit perform overvoltage or/and overcurrent protection on a load circuit, the output end of the anti-surge circuit is connected with the input end circuit of the EMI filter, the EMI filter filters interference frequency signals in the circuit, and the primary power supply with stable output frequency is output, and the DC/DC converter converts the primary power supply into a secondary power supply which can be used by the load circuit.
Preferably, the fuse protection circuit includes: the fuse protector comprises a first fuse, a second fuse and a protection resistor; the first fuse and the protection resistor are connected in series to form a series circuit, and the second fuse is connected in parallel to the series circuit.
Preferably, the anti-surge circuit comprises two P-channel MOSFETs connected in parallel, forming a redundant backup structure.
The source electrode of each MOSFET is connected with the input end of the anti-surge circuit, the drain electrode of each MOSFET is connected with the output end of the anti-surge circuit, and the grid electrode of each MOSFET is connected with a voltage division point between two series resistors connected between an input power supply and the ground through a resistor connected with the grid electrode of each MOSFET.
Specifically, the rated power consumption of the EMI filter is larger than the sum of the maximum power consumption of the plurality of DC/DC converters, and the noise suppression frequency of the EMI filter covers the switching frequency of the DC/DC converters.
Preferably, the number of the plurality of DC/DC converters is four, including: the first DC/DC converter, the second DC/DC converter, the third DC/DC converter and the fourth DC/DC converter.
The load circuit includes: the device comprises a main light source, a main communication board, a standby light source, a standby communication board, a fiber-optic gyroscope S, a fiber-optic gyroscope X, a fiber-optic gyroscope Y and a fiber-optic gyroscope Z.
Specifically, the first DC/DC converter outputs +5V voltage to power the main light source, and outputs ± 5V voltage to power the control circuit of the fiber optic gyroscope S; the second DC/DC converter outputs +5V voltage to supply power to the main communication board, and outputs +/-5V voltage to supply power to a control circuit of the fiber-optic gyroscope X; the third DC/DC converter outputs +5V voltage to supply power to the standby light source, and outputs +/-5V voltage to supply power to the control circuit of the fiber-optic gyroscope Y; the fourth DC/DC converter outputs +5V voltage to supply power to the standby communication board, and outputs +/-5V voltage to supply power to the control circuit of the optical fiber gyroscope Z.
Compared with the prior art, the redundancy secondary power supply circuit adopted by the invention has the advantages and beneficial effects that:
1. the fuse protection circuit and the anti-surge circuit which are connected in parallel and redundant are adopted, so that the low reflection ripple waves output by the optical fiber gyroscope combination are ensured, and the safety and the reliability of the optical fiber gyroscope combination are ensured;
2, the EMI filter adopts a four-in-one mode (one circuit is divided into four branches), so that the cost, the volume and the power consumption of the fiber-optic gyroscope combination are effectively reduced;
3. each DC/DC converter is provided with two different loads, so that the use efficiency of the DC/DC converter is effectively improved, and the self dissipation power is reduced. Meanwhile, when any one gyro breaks down, the work of other three gyros is not influenced.
Drawings
FIG. 1 is a circuit block diagram of a redundant secondary power supply of the present invention;
fig. 2 is a diagram of an anti-surge circuit of the present invention.
Detailed Description
The redundant secondary power circuit for the satellite-borne fiber-optic gyroscope combination of the invention is described in detail with reference to the accompanying drawings.
The redundant secondary power supply circuit for the satellite-borne fiber-optic gyroscope combination is shown in fig. 1 and comprises a fuse protector circuit 1, an anti-surge circuit 2, an EMI (electromagnetic interference) filter 3 and a plurality of DC/DC (direct current/direct current) converters which are sequentially connected through circuits.
The primary power supply sequentially passes through the fuse protection circuit 1, the anti-surge circuit 2 and the EMI filter 3 and then is converted into a plurality of paths of secondary power supplies through the plurality of DC/DC converters to supply power to the load circuit 5.
Preferably, the EMI filter is of a model DVMH28F, and the DC/DC converter is of a model DVHF2805 DF/H.
The fuse protection circuit 1 is connected with the positive electrode of a primary power supply through a circuit, the output end of the fuse protection circuit 1 is connected with the input end of the anti-surge circuit 2 through a circuit, and the fuse protection circuit 1 and the anti-surge circuit 2 perform overvoltage or/and overcurrent protection on the load circuit 5; the output end of the anti-surge circuit 2 is connected with the input end of the EMI filter 3 through a circuit, the EMI filter 3 filters interference frequency signals in the circuit and outputs a primary power supply with stable frequency; a plurality of said DC/DC converters convert the primary power supply into a plurality of secondary power supplies usable by the load circuit 5.
Preferably, the fuse protection circuit 1 includes: the fuse comprises a first fuse, a second fuse and a protection resistor, wherein the first fuse and the protection resistor are connected in series to form a series circuit, and the second fuse is connected with the series circuit in parallel.
Preferably, the anti-surge circuit 2 comprises two P-channel MOSFETs connected in parallel, and a redundant backup structure is formed to constitute the anti-surge circuit 2.
Specifically, to ensure the normal operation of the output branch of each DC/DC converter, the rated power consumption of the EMI filter 3 is larger than the sum of the maximum power consumptions of the plurality of DC/DC converters, and the noise suppression frequency of the EMI filter 3 is ensured to cover the switching frequencies of all DC/DC converters.
Specifically, as shown in the anti-surge circuit diagram of fig. 2, the source of each of the MOSFET N1 and the MOSFET N2 is connected to the anti-surge circuit input terminal node a, the drain of each of the MOSFET N1 and the MOSFET N2 is connected to the anti-surge circuit output terminal node B, the gate of the MOSFET N1 is connected to the voltage division point circuit between the two series resistors R2 and R3 between the input power and the ground through the resistor R6, and the gate of the MOSFET N2 is connected to the voltage division point circuit between the two series resistors R4 and R5 between the input power and the ground through the resistor R7.
Preferably, the output end of the EMI filter 3 is divided into a plurality of branches to be connected with the plurality of DC/DC converters, so that the circuit design effectively reduces the usage amount of the EMI filter 3, and reduces the cost, volume and power consumption of the secondary circuit for the fiber-optic gyroscope combination.
Preferably, the number of the DC/DC converters is four, including: a first DC/DC converter 41, a second DC/DC converter 42, a third DC/DC converter 43, and a fourth DC/DC converter 44.
Preferably, the load circuit 5 includes: a main light source 51, a main communication board 53, a spare light source 55, a spare communication board 57, a fiber-optic gyroscope S52, a fiber-optic gyroscope X54, a fiber-optic gyroscope Y56 and a fiber-optic gyroscope Z58.
Specifically, the first DC/DC converter 41 outputs +5V voltage to power the main light source 51, and outputs ± 5V voltage to power the control circuit of the fiber optic gyroscope S52; the second DC/DC converter 42 outputs +5V voltage to supply power to the main communication board 53, and outputs +/-5V voltage to supply power to the optical fiber gyroscope X54 control circuit; the third DC/DC converter 43 outputs +5V voltage to supply power to the standby light source 55, and outputs +/-5V voltage to supply power to the optical fiber gyroscope Y56 control circuit; the fourth DC/DC converter 44 outputs +5V voltage to supply power to the communication board 57, and outputs ± 5V voltage to supply power to the optical fiber gyro Z58 control circuit.
Through the embodiment, compared with the prior art, the redundant secondary power supply circuit provided by the invention has the advantages that the secondary power supply output ensures lower reflection ripples of the output of the optical fiber gyroscope combination, and simultaneously ensures the safety and reliability of the optical fiber gyroscope combination.
The embodiments of the present invention have been described in detail with reference to the drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the gist of the present invention.
Claims (9)
1. A redundant secondary power supply circuit for a satellite-borne fiber-optic gyroscope combination supplies power to a load circuit (5), and is characterized by comprising: a fuse protection circuit (1), an anti-surge circuit (2), an EMI filter (3), and a plurality of DC/DC converters;
the primary power supply is converted into a multi-path secondary power supply through a plurality of DC/DC converters after passing through a fuse protector circuit (1), an anti-surge circuit (2) and an EMI filter (3) in sequence;
the fuse protector protection circuit (1) is connected with a primary power supply positive circuit, the output end of the fuse protector protection circuit (1) is connected with the input end circuit of the anti-surge circuit (2) in a circuit mode, and overvoltage or/and overcurrent protection is performed on the load circuit (5); the output end of the anti-surge circuit (2) is connected with the input end circuit of the EMI filter (3), the EMI filter (3) filters interference frequency signals in the circuit and outputs a primary power supply with stable frequency, and the plurality of DC/DC converters convert the primary power supply into a plurality of paths of secondary power supplies which can be used by the load circuit (5).
2. The combined redundant secondary power supply circuit for the satellite-borne fiber-optic gyroscope according to claim 1, wherein the fuse protection circuit (1) comprises: the fuse protector comprises a first fuse, a second fuse and a protection resistor; the first fuse and the protection resistor are connected in series to form a series circuit, and the second fuse is connected in parallel to the series circuit.
3. The combined redundant secondary power supply circuit for the satellite-borne fiber-optic gyroscope according to claim 1, wherein the anti-surge circuit (2) comprises two P-channel MOSFETs connected in parallel to form a redundant backup structure.
4. The redundant secondary power supply circuit for the combination of the satellite-borne fiber-optic gyroscope according to claim 3, wherein the source of each of the MOSFETs is connected to the input end of the anti-surge circuit, the drain of each of the MOSFETs is connected to the output end of the anti-surge circuit, and the gate of each of the MOSFETs is connected to a voltage division point between two series resistors connected between the input power supply and the ground through a resistor connected thereto.
5. The combined redundant secondary power supply circuit for the satellite-borne fiber-optic gyroscope according to claim 1, characterized in that the rated power consumption of the EMI filter (3) is larger than the sum of the maximum power consumptions of the plurality of DC/DC converters.
6. The redundant secondary power supply circuit for the satellite-borne fiber-optic gyroscope assembly according to claim 1 or 5, wherein the EMI filter (3) noise suppression frequency covers the switching frequencies of the plurality of DC/DC converters.
7. The redundant secondary power supply circuit for the combination of the satellite-borne fiber-optic gyroscope according to claim 1, wherein the number of the DC/DC converters is four, and the redundant secondary power supply circuit comprises: a first DC/DC converter (41), a second DC/DC converter (42), a third DC/DC converter (43), and a fourth DC/DC converter (44).
8. The combined redundant secondary power supply circuit for the satellite-borne fiber-optic gyroscope according to claim 7, wherein the load circuit (5) comprises: the device comprises a main light source (51), a main communication board (53), a standby light source (55), a standby communication board (57), a fiber-optic gyroscope S (52), a fiber-optic gyroscope X (54), a fiber-optic gyroscope Y (56) and a fiber-optic gyroscope Z (58).
9. The redundant secondary power circuit for the combination of the satellite-borne fiber-optic gyroscope of claim 8,
the first DC/DC converter (41) outputs +5V voltage to supply power to the main light source (51), and outputs +/-5V voltage to supply power to a control circuit of the fiber-optic gyroscope S (52);
the second DC/DC converter (42) outputs +5V voltage to supply power to the main communication board (53), and outputs +/-5V voltage to supply power to a control circuit of the fiber-optic gyroscope X (54);
the third DC/DC converter (43) outputs +5V voltage to supply power to the standby light source (55), and outputs +/-5V voltage to supply power to a control circuit of the fiber-optic gyroscope Y (56);
the fourth DC/DC converter (44) outputs +5V voltage to supply power to the standby communication board (57), and outputs +/-5V voltage to supply power to the control circuit of the optical fiber gyroscope Z (58).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010975202.3A CN112003263A (en) | 2020-09-16 | 2020-09-16 | Redundant secondary power supply circuit for combination of satellite-borne fiber-optic gyroscope |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010975202.3A CN112003263A (en) | 2020-09-16 | 2020-09-16 | Redundant secondary power supply circuit for combination of satellite-borne fiber-optic gyroscope |
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| Publication Number | Publication Date |
|---|---|
| CN112003263A true CN112003263A (en) | 2020-11-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010975202.3A Pending CN112003263A (en) | 2020-09-16 | 2020-09-16 | Redundant secondary power supply circuit for combination of satellite-borne fiber-optic gyroscope |
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| CN (1) | CN112003263A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112737333A (en) * | 2020-12-28 | 2021-04-30 | 航天东方红卫星有限公司 | Secondary power supply with high conversion efficiency for satellite |
| CN113037082A (en) * | 2021-03-10 | 2021-06-25 | 上海航天测控通信研究所 | Satellite-borne current sampling control power supply device |
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| CN104078940A (en) * | 2014-06-11 | 2014-10-01 | 京东方科技集团股份有限公司 | Secondary power system and power supply device |
| CN104714582A (en) * | 2015-03-09 | 2015-06-17 | 中国科学院长春光学精密机械与物理研究所 | spaceborne camera power supply system based on magnetic latching relay |
| CN106300235A (en) * | 2016-10-09 | 2017-01-04 | 中国电子科技集团公司第三十六研究所 | A kind of power-supply system |
| US20180145595A1 (en) * | 2016-11-23 | 2018-05-24 | Infineon Technologies Austria Ag | Bridgeless Flyback Converter Circuit and Method of Operating Thereof |
| CN209805677U (en) * | 2019-06-12 | 2019-12-17 | 成都宝通天宇电子科技有限公司 | Novel DC-DC switching power supply circuit |
| CN111416331A (en) * | 2020-03-26 | 2020-07-14 | 上海空间电源研究所 | A pre-charge circuit for DC power surge current suppression |
-
2020
- 2020-09-16 CN CN202010975202.3A patent/CN112003263A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104078940A (en) * | 2014-06-11 | 2014-10-01 | 京东方科技集团股份有限公司 | Secondary power system and power supply device |
| CN104714582A (en) * | 2015-03-09 | 2015-06-17 | 中国科学院长春光学精密机械与物理研究所 | spaceborne camera power supply system based on magnetic latching relay |
| CN106300235A (en) * | 2016-10-09 | 2017-01-04 | 中国电子科技集团公司第三十六研究所 | A kind of power-supply system |
| US20180145595A1 (en) * | 2016-11-23 | 2018-05-24 | Infineon Technologies Austria Ag | Bridgeless Flyback Converter Circuit and Method of Operating Thereof |
| CN209805677U (en) * | 2019-06-12 | 2019-12-17 | 成都宝通天宇电子科技有限公司 | Novel DC-DC switching power supply circuit |
| CN111416331A (en) * | 2020-03-26 | 2020-07-14 | 上海空间电源研究所 | A pre-charge circuit for DC power surge current suppression |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112737333A (en) * | 2020-12-28 | 2021-04-30 | 航天东方红卫星有限公司 | Secondary power supply with high conversion efficiency for satellite |
| CN113037082A (en) * | 2021-03-10 | 2021-06-25 | 上海航天测控通信研究所 | Satellite-borne current sampling control power supply device |
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Application publication date: 20201127 |
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