CN108390454B - Satellite-borne power conversion circuit - Google Patents
Satellite-borne power conversion circuit Download PDFInfo
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- CN108390454B CN108390454B CN201810215257.7A CN201810215257A CN108390454B CN 108390454 B CN108390454 B CN 108390454B CN 201810215257 A CN201810215257 A CN 201810215257A CN 108390454 B CN108390454 B CN 108390454B
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- power supply
- interface
- main circuit
- positive
- auxiliary
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- 238000006243 chemical reaction Methods 0.000 title claims description 11
- 239000003990 capacitor Substances 0.000 claims description 26
- 230000000087 stabilizing effect Effects 0.000 claims description 8
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 239000003292 glue Substances 0.000 claims description 2
- 238000001914 filtration Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
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Classifications
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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
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H9/00—Emergency protective circuit arrangements for limiting excess current or voltage without disconnection
- H02H9/02—Emergency protective circuit arrangements for limiting excess current or voltage without disconnection responsive to excess current
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- H02J3/005—
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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
- H02M1/00—Details of apparatus for conversion
- H02M1/42—Circuits or arrangements for compensating for or adjusting power factor in converters or inverters
- H02M1/4208—Arrangements for improving power factor of AC input
- H02M1/4266—Arrangements for improving power factor of AC input using passive elements
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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
- H02M1/00—Details of apparatus for conversion
- H02M1/0067—Converter structures employing plural converter units, other than for parallel operation of the units on a single load
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
- Y02B70/00—Technologies for an efficient end-user side electric power management and consumption
- Y02B70/10—Technologies improving the efficiency by using switched-mode power supplies [SMPS], i.e. efficient power electronics conversion e.g. power factor correction or reduction of losses in power supplies or efficient standby modes
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Direct Current Feeding And Distribution (AREA)
Abstract
The invention designs a satellite-borne power switching circuit, a satellite platform power supply positive interface of which is connected with a positive input end of a filter, a satellite platform power supply negative interface of which is connected with a negative input end of the filter, a positive output end of the filter is connected with a positive input end of a main circuit power module through a main circuit fuse, a negative output end of the filter is grounded, a satellite platform control signal communication interface is connected with a base B of a triode, a collector C of the triode is grounded, and an emitter E of the triode is connected with a negative input end of the main circuit power module; the positive output end of the filter is also connected with the positive input end of the auxiliary power supply module through an auxiliary fuse, and the base B of the triode is also connected with the negative input end of the auxiliary power supply module; the main circuit output positive power interface of the main circuit power module is also connected with the input end of a photoelectric coupler, and the output end of the photoelectric coupler is connected with the negative electrode input end of the auxiliary circuit power module. The invention improves the power supply reliability of the satellite system.
Description
Technical Field
The invention relates to the technical field of satellite-borne power supply circuits, in particular to a satellite-borne power supply conversion circuit.
Technical Field
In the process of the in-orbit operation period of the satellite, the satellite not only needs to bear a complex irradiation environment, but also needs to bear severe environmental conditions such as a great temperature difference, and the like.
The power supply in the traditional satellite-borne power supply system has no backup design, the power supply has no main and auxiliary power supply switching capacity, and the fuse is not connected to the bus, so that the traditional satellite-borne power supply system cannot carry out current-limiting protection on the bus, the reliability is poor, and the anti-irradiation capacity is weak.
Disclosure of Invention
The invention aims to provide a satellite-borne power conversion circuit, which solves the problem that the traditional satellite-borne power conversion circuit has no main and auxiliary power supply switching capability.
In order to achieve the purpose, the invention designs a satellite-borne power conversion circuit, which comprises a satellite platform communication end, a filter, a main circuit fuse, a main circuit power module, a triode, a photoelectric coupler, an auxiliary circuit fuse and an auxiliary circuit power module, wherein the satellite platform communication end is provided with a satellite platform power supply positive interface, a satellite platform power supply negative interface and a satellite platform control signal communication interface;
the star platform power supply positive interface is connected with the positive input end of the filter, the star platform power supply negative interface is connected with the negative input end of the filter, the positive output end of the filter is connected with the positive input end of the main circuit power module through a main circuit fuse, the negative output end of the filter is grounded, the star platform control signal communication interface is connected with the base B of the triode, the collector C of the triode is grounded, the emitter E of the triode is connected with the negative input end of the main circuit power module, and the main circuit power module is further provided with a main circuit output positive power interface and a main circuit output negative power interface;
the positive output end of the filter is also connected with the positive input end of the auxiliary power supply module through an auxiliary fuse, the emitter E of the triode is also connected with the negative input end of the auxiliary power supply module, and the auxiliary power supply module is also provided with an auxiliary output positive power supply interface and an auxiliary output negative power supply interface;
the main circuit output positive power interface of the main circuit power module is also connected with the input end of a photoelectric coupler, and the output end of the photoelectric coupler is connected with the negative electrode input end of the auxiliary circuit power module.
The invention is arranged in the satellite load when in use, and is used for completing power supply conversion of the satellite load in the operation process and providing power supply input for other subsystems. The invention adopts two paths of power supplies of the main power supply module and the auxiliary power supply module, has the capability of switching the failure of the main power supply into the auxiliary power supply, and simultaneously adds fuses on the buses of the main power supply and the auxiliary power supply for current limiting protection, thereby further improving the power supply reliability of the satellite system. And the power supply backup design of the satellite-borne power supply system is realized.
Drawings
FIG. 1 is a block diagram of the present invention.
Wherein, 1-shell, 2-second resistance, 3-star platform communication end, 4-star platform power supply positive interface, 5-star platform power supply negative interface, 6-star platform control signal communication interface, 7-first diode, 8-voltage stabilizing diode, 9-filter, 10-main circuit fuse, 11-main circuit power module, 12-main circuit output positive power interface, 13-main circuit output negative power interface, 14-second diode, 15-triode, 16-third diode, 17-photoelectric coupler, 18-fourth diode, 19-auxiliary circuit fuse, 20-auxiliary circuit power module, 21-fifth diode, 22-auxiliary circuit output anode power interface, 23-auxiliary circuit output cathode power interface, 24-first capacitor, 25-second capacitor, 26-third capacitor, 27-fourth capacitor, 28-fifth capacitor and 29-first resistor.
Detailed Description
The invention is described in further detail below with reference to the following figures and specific examples:
the invention designs a satellite-borne power supply switching circuit, which comprises a satellite platform communication end 3, a filter 9, a main circuit fuse 10, a main circuit power supply module 11, a triode 15, a photoelectric coupler 17, an auxiliary circuit fuse 19 and an auxiliary circuit power supply module 20, wherein the satellite platform communication end 3 is provided with a satellite platform power supply positive interface 4, a satellite platform power supply negative interface 5 and a satellite platform control signal communication interface 6 (the satellite platform communication end 3 is connected with a corresponding power supply and control interface of a satellite platform when in use);
the star platform power supply positive interface 4 is connected with a positive input end of a filter 9(EMI filter), the star platform power supply negative interface 5 is connected with a negative input end of the filter 9, a positive output end of the filter 9 is connected with a positive input end of a main circuit power module 11 through a main circuit fuse 10, a negative output end of the filter 9 is grounded, the star platform control signal communication interface 6 is connected with a base B of a triode 15, a collector C of the triode 15 is grounded, an emitter E of the triode 15 is connected with a negative input end of the main circuit power module 11, and the main circuit power module 11 is further provided with a main circuit output positive power interface 12 and a main circuit output negative power interface 13;
the positive output end of the filter 9 is further connected with the positive input end of the auxiliary power module 20 through an auxiliary fuse 19, the emitter E of the triode 15 is further connected with the negative input end of the auxiliary power module 20, and the auxiliary power module 20 is further provided with an auxiliary output positive power interface 22 and an auxiliary output negative power interface 23;
the main circuit output positive power interface 12 of the main circuit power module 11 is further connected to the input end of a photoelectric coupler 17, and the output end of the photoelectric coupler 17 is connected to the negative input end of the auxiliary circuit power module 20.
The invention further comprises a first diode 7, a second diode 14, a third diode 16, a fourth diode 18 and a fifth diode 21, the positive electrode of the first diode 7 is connected with the star platform power supply positive interface 4, the negative electrode of the first diode 7 is connected with the positive electrode input end of the filter 9, the positive electrode of the second diode 14 is connected with the star platform control signal communication interface 6, the negative electrode of the second diode 14 is connected with the base electrode B of the triode 15, the positive electrode of the third diode 16 is connected with the emitter electrode E of the triode 15, the negative electrode of the third diode 16 is connected with the negative electrode input end of the main circuit power module 11, the positive electrode of the fourth diode 18 is connected with the output end of the photoelectric coupler 17, the negative electrode of the fourth diode 18 is connected with the negative electrode input end of the auxiliary circuit power module 20, the positive electrode of the fifth diode 21 is connected with the emitter electrode E of the triode 15, and the negative electrode of the fifth diode 21 is. The diode is used for controlling the current signal flow direction.
The invention also comprises a voltage stabilizing diode 8, wherein the anode of the voltage stabilizing diode 8 is connected with the star platform power supply positive interface 4, and the cathode of the voltage stabilizing diode 8 is connected with the star platform power supply negative interface 5.
In the above technical solution, the main power supply module 11 and the auxiliary power supply module 20 have a function of converting a bus voltage of the satellite platform into a power supply voltage required by other subsystems of the satellite load. The input is bus voltage and control signal for receiving satellite load, and the output is supply voltage required by other subsystems of satellite load.
The invention further comprises a first capacitor 24(10uF), a second capacitor 25(1uF), a third capacitor 26(1uF), a fourth capacitor 27(0.1uF) and a fifth capacitor 28(0.1uF), wherein the first capacitor 24 is connected between the satellite platform power supply positive interface 4 and the satellite platform power supply negative interface 5, the second capacitor 25 and the third capacitor 26 are connected in parallel between the main output positive power interface 12 and the main output negative power interface 13 of the main power module 11, and the fourth capacitor 27 and the fifth capacitor 28 are connected in parallel between the auxiliary output positive power interface 22 and the auxiliary output negative power interface 23 of the auxiliary power module 20. The capacitor is used for realizing power supply filtering.
The main circuit output positive power interface 12 of the main circuit power module 11 is connected with the input end of the photoelectric coupler 17 through the first resistor 29, and the emitter E of the triode 15 is connected with the positive output end of the filter 9 through the second resistor 2. The resistor is used for line protection.
In the above technical solution, the satellite platform communication terminal 3, the filter 9, the main circuit fuse 10, the main circuit power module 11, the triode 15, the photoelectric coupler 17, the auxiliary circuit fuse 19, and the auxiliary circuit power module 20 are disposed in the housing 1. The shell 1 is composed of three layers of metal, an inner layer and an outer layer are aluminum layers with the thickness of 1.3-1.6 mm (the irradiation resistance is strong, the rigidity is strong, the deformation is prevented), and a middle layer is a lead layer with the thickness of 0.8-1.1 mm (the irradiation resistance is strong, but the density is large, and the thickness cannot be too large). And heat-conducting filling glue (such as GF-1000) is filled between adjacent metal layers of the shell 1, so that the radiation resistance of the invention is improved.
In the technical scheme, after the star platform power supply positive interface 4 and the star platform power supply negative interface 5 are stabilized by the voltage stabilizing diode 8, power supply filtering is carried out by the filter 9, input power supply ripples are reduced, and the stability of power supply voltage is improved.
In the above technical solution, the main circuit fuse 10 and the auxiliary circuit fuse 19 respectively perform current limiting protection on the current passing through the main power module and the auxiliary power module.
In the above technical solution, the satellite platform control signal (the signal comes from the satellite platform to control the on/off of the triode 15) output by the satellite platform control signal communication interface 6 is output by the open circuit of the collector, and after passing through the second diode 14, the on/off of the triode 15 is controlled, and the low level is effective.
In the above technical solution, the photocoupler 17 is controlled to be on/off by the signal output by the main circuit output positive power interface 12 of the main circuit power module 11, the high level is active, and when the output signal of the main circuit power module 11 is high (the satellite bus voltage is input and the triode 15 is not turned on), the photocoupler 17 is turned on, so that the control end of the auxiliary circuit power module 20 is pulled low and turned off; when the output signal of the main circuit power module 11 is low (the damage of the main power module causes the output signal to be low), the photoelectric coupler 17 is turned off, so that the control end of the auxiliary circuit power module 20 is pulled high to work, and the switching between the main power supply and the auxiliary power supply is realized.
Details not described in this specification are within the skill of the art that are well known to those skilled in the art.
Claims (4)
1. A satellite-borne power conversion circuit is characterized by comprising a satellite platform communication end (3), a filter (9), a main circuit fuse (10), a main circuit power module (11), a triode (15), a photoelectric coupler (17), an auxiliary circuit fuse (19) and an auxiliary circuit power module (20), wherein the satellite platform communication end (3) is provided with a satellite platform power supply positive interface (4), a satellite platform power supply negative interface (5) and a satellite platform control signal communication interface (6);
the star platform power supply positive interface (4) is connected with the positive input end of the filter (9), the star platform power supply negative interface (5) is connected with the negative input end of the filter (9), the positive output end of the filter (9) is connected with the positive input end of the main circuit power module (11) through the main circuit fuse (10), the negative output end of the filter (9) is grounded, the star platform control signal communication interface (6) is connected with the base B of the triode (15), the collector C of the triode (15) is grounded, the emitter E of the triode (15) is connected with the negative input end of the main circuit power module (11), and the main circuit power module (11) is further provided with a main circuit output positive power interface (12) and a main circuit output negative power interface (13);
the positive output end of the filter (9) is also connected with the positive input end of the auxiliary power supply module (20) through an auxiliary fuse (19), the emitter E of the triode (15) is also connected with the negative input end of the auxiliary power supply module (20), and the auxiliary power supply module (20) is also provided with an auxiliary output positive power supply interface (22) and an auxiliary output negative power supply interface (23);
the main circuit output positive power interface (12) of the main circuit power module (11) is also connected with the input end of a photoelectric coupler (17), and the output end of the photoelectric coupler (17) is connected with the negative electrode input end of the auxiliary circuit power module (20);
the main circuit power supply module further comprises a first capacitor (24), a second capacitor (25), a third capacitor (26), a fourth capacitor (27) and a fifth capacitor (28), wherein the first capacitor (24) is connected between the star platform power supply positive interface (4) and the star platform power supply negative interface (5), the second capacitor (25) and the third capacitor (26) are connected in parallel between the main circuit output positive power interface (12) and the main circuit output negative power interface (13) of the main circuit power module (11), and the fourth capacitor (27) and the fifth capacitor (28) are connected in parallel between the auxiliary circuit output positive power interface (22) and the auxiliary circuit output negative power interface (23) of the auxiliary circuit power module (20);
the power supply device also comprises a first diode (7), a second diode (14), a third diode (16), a fourth diode (18) and a fifth diode (21), wherein the anode of the first diode (7) is connected with the star platform power supply positive interface (4), the cathode of the first diode (7) is connected with the anode input end of the filter (9), the anode of the second diode (14) is connected with the star platform control signal communication interface (6), the cathode of the second diode (14) is connected with the base B of the triode (15), the anode of the third diode (16) is connected with the emitter E of the triode (15), the cathode of the third diode (16) is connected with the cathode input end of the main circuit power module (11), the anode of the fourth diode (18) is connected with the output end of the photoelectric coupler (17), the cathode of the fourth diode (18) is connected with the cathode input end of the auxiliary circuit power module (20), the positive electrode of the fifth diode (21) is connected with the emitter E of the triode (15), and the negative electrode of the fifth diode (21) is connected with the negative electrode input end of the auxiliary power supply module (20);
the main circuit output positive power interface (12) of the main circuit power module (11) is connected with the input end of the photoelectric coupler (17) through the first resistor (29), and the emitter E of the triode (15) is connected with the positive output end of the filter (9) through the second resistor (2);
the star platform communication end (3), the filter (9), the main circuit fuse (10), the main circuit power module (11), the triode (15), the photoelectric coupler (17), the auxiliary circuit fuse (19) and the auxiliary circuit power module (20) are arranged in the shell (1), the shell (1) is composed of three layers of metal, the inner layer and the outer layer are aluminum layers with the thickness of 1.3-1.6 mm, and the middle layer is a lead layer with the thickness of 0.8-1.1 mm;
heat conduction filling glue is filled between adjacent metal layers of the shell (1);
when the output signal of the main circuit power supply module (11) is high, the photoelectric coupler (17) is switched on, so that the control end of the auxiliary circuit power supply module (20) is pulled low and is switched off; when the output signal of the main circuit power supply module (11) is low, the photoelectric coupler (17) is turned off, so that the control end of the auxiliary circuit power supply module (20) is pulled high to work, and the switching between main power supply and auxiliary power supply is realized.
2. The on-board power conversion circuit of claim 1, wherein: the star platform power supply system further comprises a voltage stabilizing diode (8), wherein the anode of the voltage stabilizing diode (8) is connected with the star platform power supply positive interface (4), and the cathode of the voltage stabilizing diode (8) is connected with the star platform power supply negative interface (5).
3. The on-board power conversion circuit of claim 1, wherein: the star platform control signal output by the star platform control signal communication interface (6) is output by an open collector, and is controlled to be switched on and off by a triode (15) after passing through a second diode (14).
4. The on-board power conversion circuit of claim 1, wherein: the photoelectric coupler (17) is controlled to be switched on and off by a signal output by a main circuit output positive power interface (12) of the main circuit power module (11), and the high level is effective.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810215257.7A CN108390454B (en) | 2018-03-15 | 2018-03-15 | Satellite-borne power conversion circuit |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810215257.7A CN108390454B (en) | 2018-03-15 | 2018-03-15 | Satellite-borne power conversion circuit |
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| Publication Number | Publication Date |
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| CN108390454A CN108390454A (en) | 2018-08-10 |
| CN108390454B true CN108390454B (en) | 2020-07-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810215257.7A Active CN108390454B (en) | 2018-03-15 | 2018-03-15 | Satellite-borne power conversion circuit |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111668916A (en) * | 2020-05-26 | 2020-09-15 | 中国科学院西安光学精密机械研究所 | Satellite load power supply backup system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4281278A (en) * | 1979-12-05 | 1981-07-28 | Rca Corporation | Redundant battery protection system |
| CN201142593Y (en) * | 2007-11-30 | 2008-10-29 | 唐云雄 | Low-electromagnetic interference power supply circuit |
| CN105406699B (en) * | 2015-11-26 | 2018-01-05 | 北京卫星制造厂 | A kind of cold standby modular power source |
| CN105730718B (en) * | 2016-05-10 | 2016-11-16 | 中国人民解放军国防科学技术大学 | Spacecraft multifunction structure lithium battery system Power Management Unit |
| CN106549487B (en) * | 2016-12-08 | 2019-02-19 | 北京卫星制造厂 | A kind of master backup power failure monitor and automatic switching control circuit |
| CN107196403B (en) * | 2017-05-19 | 2020-09-04 | 上海宇航系统工程研究所 | Solar cell array driver suitable for long-term continuous work |
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