CN103872749B - Topological circuit for satellite power system power adjustments - Google Patents
Topological circuit for satellite power system power adjustments Download PDFInfo
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- CN103872749B CN103872749B CN201210526424.2A CN201210526424A CN103872749B CN 103872749 B CN103872749 B CN 103872749B CN 201210526424 A CN201210526424 A CN 201210526424A CN 103872749 B CN103872749 B CN 103872749B
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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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
- Y02E10/56—Power conversion systems, e.g. maximum power point trackers
Abstract
The topological circuit for satellite power system power adjustments of the present invention, including T-shape integration main circuit topology and logic control circuit topology；Main circuit topology includes three power MOS pipes, three respective body diodes, a power diode and an energy storage inductor；Solar battery array output is powered with loading to be connected by power diode；Three power MOS pipes and three respective body diodes, according to T-shape topological structure layout, are connected with sun battle array, accumulator and ground wire respectively, complete the shunting of sun battle array, three kinds of functions of accumulator charging and discharging according to logic control；Energy storage inductor is directly connected with accumulator.The present invention can effectively solve the problem that satellite power system mass-power ratio cannot meet load-carrying ability, be simultaneously realize the lightweight of satellite power system, integrated and integrated design provides technical foundation, have a wide range of applications in satellite power system field.
Description
Technical field
The invention belongs to satellite power system power adjustments topologies field, be specifically related to a kind of topological circuit for satellite power system power adjustments.
Background technology
The power that solar battery array is sent by the power conditioning module of satellite power system is converted by certain technology requirement, it is adjusted to the voltage required for bus, it is directly load supplying, and controls the discharge and recharge of accumulator, to maintain the stability of power-supply system busbar voltage.
Compare existing S3R, mixed type and S4R power adjustments topologies, T-shape integration power adjustments topologies has that components and parts used are few, integrated level is high, volume and weight is little and the high-power advantage of mass ratio, additionally, it is better than the BCDSR power conditioning technology that ESA is studying in the difficulty of control strategy.In BCDSR circuit, often due to the design of control program is the most loaded down with trivial details, so that the shunting of sun battle array, accumulator charging and three kinds of functions of battery discharging cannot conservative control and conversions；And in this T-shape integration power adjustments topological circuit, control logical AND S4R is similar, simply at S4Control discharging function is added on the basis of R.Therefore, in T-shape integration power conditioning circuitry, shunting, three kinds of functions of charging and discharging control rationally, to convert each other conveniently.
Dividing on periodical " Space Dynamic " at the 6th nd Annual Meeting collection of 2002ESA (European Space Agency), " AnEfficientLowCostModularPowerSystemForFullyRegulatedBus InLowEarthObritApplicationsOr " Theregulatedbus " " has carried out detailed elaboration to BCDSR power adjustments topological circuit and control program thereof.But BCDSR power adjustments topological circuit disadvantageously, control strategy is considerably complicated, the controlling of charge function and diverter function converts the dutycycle by changing switch S2 and realizes, and this control design case is unreasonable, and reliability is low；Converting between charge function and discharging function and need switch S1 and S2 mutually to switch, this control design case is very inconvenient.
Existing power adjustments topologies, it is impossible to meet the quality requirements at the higher level than power.It is true that the quality of power-supply system the most seriously constrains the lifting of load-carrying ability on satellite than power, therefore, power adjustments topological circuit that quality than power big and easy to control high in the urgent need to a kind of integrated level and control method.
Currently without finding the domestic explanation having technology similar to the present invention or report, the most not yet collect similar data.
Summary of the invention
It is contemplated that propose a kind of topological circuit for satellite power system power adjustments and control method, low and the problem of application demand of high-quality power ratio cannot be met in order to solve existing satellite power system power adjustments topologies integrated level.
In order to realize object above, a kind of topological circuit for satellite power system power adjustments that the present invention proposes, including: T-shape integration main circuit topology and logic control circuit topology；
Described T-shape integration main circuit topology includes three power MOS pipes Q1, Q2 and Q3, three respective body diode D1, D2 and D3, a power diode D4 and an energy storage inductor L；
In described T-shape integration main circuit topology, solar battery array output is connected with load by power diode D4, is powered it；Described three power MOS pipes Q1, Q2 and Q3 and three respective body diode D1, D2 and D3 are according to T-shape topological structure layout, it is connected with sun battle array, accumulator and ground wire respectively, completes the shunting of sun battle array, three kinds of functions of accumulator charging and discharging according to logic control；Described energy storage inductor L is directly connected with accumulator, completes energy storage function during accumulator charging and discharging；
Described control logic circuit topology includes four NAND gate, two diodes, filter capacitor and several stabilivolts.
Further, the control logic of described T-shape integration topological circuit is:
The shade phase, accumulator carrys out powering load by electric discharge, and at this moment metal-oxide-semiconductor Q1, Q3 is in off state, and Q2 is in PWM state；
Illumination period, solar battery array passes through power diode powering load；
Illumination period, when load operation is in peak power, solar battery array and accumulator combine power supply, and at this moment metal-oxide-semiconductor Q2 is in PWM state, and Q1, Q3 are in off state；
Illumination period, when the output of solar battery array is more than load power demand, accumulator is charged by solar battery array, and at this moment metal-oxide-semiconductor Q1 is in PWM state, and Q2, Q3 are in off state；
Illumination period, when solar battery array output meets loading demands, and accumulator fills with, and solar battery array carries out shunt regulating, and at this moment metal-oxide-semiconductor Q1, Q2 is in PWM state, and Q3 is in off state.
Relative to existing satellite power system power adjustments topologies, the present invention proposes a kind of novel T-shape integration power adjustments topologies, and shunting, three kinds of functions of charging and discharging are integrated in a circuit topology by it, and the integrated level of circuit is high；Further, greatly reducing and realize the quantity of components and parts used by shunting, three kinds of functions of charging and discharging, the quality of circuit is bigger than power；Additionally, the control logic of circuit is by S4The control logic improvement of R circuit obtains, and shunting, three kinds of functions of charging and discharging control rationally, convert conveniently.This T-shape integration power adjustments topologies can effectively solve the problem that satellite power system mass-power ratio cannot meet load-carrying ability, simultaneously, also be realize the lightweight of satellite power system, integrated and integrated design provides technical foundation, have a wide range of applications in satellite power system field.
Accompanying drawing explanation
The present invention is described in further detail with detailed description of the invention below in conjunction with the accompanying drawings.
Fig. 1 is the topological circuit theory diagram for satellite power system power adjustments;
Fig. 2 is for controlling logical topology circuit theory diagrams;
Fig. 3 is charging circuit schematic diagram;
Fig. 4 is discharge circuit schematic diagram;
Fig. 5 is shunt circuit schematic diagram.
Detailed description of the invention
See the accompanying drawing illustrating the embodiment of the present invention, the present invention is described in more detail.But, the present invention can realize in many different forms, and should not be construed as the embodiment by herein proposing and limited.On the contrary, proposing these embodiments is to reach fully and complete disclosure, and makes those skilled in the art understand the scope of the present invention completely.
Being the present invention topological circuit theory diagram for satellite power system power adjustments refering to Fig. 1, Fig. 2 is for controlling logical topology circuit theory diagrams, and Fig. 3 is charging circuit schematic diagram, and Fig. 4 is discharge circuit schematic diagram, and Fig. 5 is shunt circuit schematic diagram.
In Fig. 1, Isa is solar battery array, and Load is load, Vbus is busbar voltage, and Vbattery is battery tension, and Vbus_sample is busbar voltage sampling, Vbattery_sample is battery tension sampling, Q1, Q2 and Q3 are metal-oxide-semiconductor, and wherein, Q1, Q3 are P pipe, Q2 is N pipe, D1, D2 and D3 are respective body diode, and D4 is power diode, and L is energy storage inductor.
Metal-oxide-semiconductor Q1, Q2 and Q3 and respective body diode D1, D2 and D3, according to T-shape topological structure layout, are connected with sun battle array, accumulator and ground wire respectively.In T-shape integration power adjustments topological circuit, Isa passes through power tube D4, powers Load.
When power tube Q1 is in PWM state, time at Q2, Q3 in off position, T-shape integration power adjustments topological circuit is operated in battery state of charge, and its circuit equivalent is Buck reduction voltage circuit.
When power tube Q2 is in PWM state, when Q1, Q3 are in off state, T-shape integration power adjustments topological circuit is operated in battery discharging state, and its circuit equivalent is Boost circuit.
When power tube Q1, Q2 are in PWM adjustment state, time at Q3 in off position, T-shape integration power adjustments topological circuit is operated in sun battle array SHUNT state.
In Fig. 2, A, B are the level that bus sampled voltage compares with reference voltage, and C is the level that accumulator sampled voltage compares with reference voltage, and M1, M2, M3 and M4 are NAND gate, and K1, K2 and K3 are the control signal of power tube Q1, Q2 and Q3.
When A is high level, K3 is high level, makes switching tube K3 turn off, and K1 is low level, and switching tube K1 is open-minded.
When B is low level, Q2 is by the co-controlling of A and C, and when A or C is high level, when Q2 is low level, switching tube Q2 turns off.
When B is high level, A is inoperative to Q2, and Q2 is only controlled by C.
In Fig. 3, Isa, Q1, D2, D3, L and battery collectively constitute Buck reduction voltage circuit, and Buck reduction voltage circuit is divided into inductive energy storage and two stages of diode continuousing flow.
Isa, Q1, D3, L and battery collectively constitute inductive energy storage circuit, and the energy of Isa is stored in inductance L by Q1, D3.
D2, D3, L and battery collectively constitute diode continuousing flow circuit, and the energy stored in inductance L is charged to battery battery by D2, D3.
In Fig. 4, battery, D1, D4, Q3, Q2, L and load collectively constitute Boost circuit, and Boost circuit is divided into inductive energy storage and energy two stages of release.
Q2, Q3, L and battery collectively constitute inductive energy storage circuit, and the energy stored in battery is stored in inductance L by Q2, Q3.
Battery, Q3, D1, D4, L and load collectively constitute energy release circuit, and the energy stored in inductance L is powered to load by Q3, D1 and D4.
In Fig. 5, Isa, Q1, Q2, D4 and load collectively constitute sun battle array shunt circuit, and sun battle array shunt circuit is divided into the shunting of sun battle array and sun battle array to power two stages.
Isa, Q1 and Q2 collectively constitute sun battle array shunt circuit, and energy unnecessary in Isa is shunted to ground by Q1, Q2.
Isa, D4 and load collectively constitute sun battle array power supply circuits, and the energy in Isa is powered to load by D4.
The scope of the present invention is limited by claims rather than described above, it is intended that all changes fallen in the implication of equivalency and scope of claim included in the present invention.Should not be considered as limiting involved claim by any reference in claim.
Claims (2)
1. the topological circuit for satellite power system power adjustments, it is characterised in that including: T-shape integration main circuit topology and logic control circuit topology；
Described T-shape integration main circuit topology includes three power MOS pipes Q1, Q2 and Q3, three respective body diode D1, D2 and D3, a power diode D4 and an energy storage inductor L；
In described T-shape integration main circuit topology, solar battery array output is connected with load by power diode D4, is powered it；Described three power MOS pipes Q1, Q2 and Q3 and three respective body diode D1, D2 and D3 are according to T-shape topological structure layout, it is connected with solar battery array, accumulator and ground wire respectively, completes solar battery array shunting, three kinds of functions of accumulator charging and discharging according to logic control；Described energy storage inductor L is directly connected with accumulator, completes energy storage function during accumulator charging and discharging；
Described control logic circuit topology includes four NAND gate, two diodes, filter capacitor and several stabilivolts；The positive input termination B of NAND gate M1, its negative input end is connected with the outfan of NAND gate M3；Positive input terminal and the negative input end parallel connection of NAND gate M3 are followed by C；It is connected with the outfan of NAND gate M1 after the positive input terminal of NAND gate M2 and negative input end parallel connection；It is connected with the positive input terminal of NAND gate M1 after the positive input terminal of NAND gate M4 and negative input end parallel connection；The outfan of NAND gate M2 connects the positive pole of the first diode, and the positive pole of the second diode connects A, as control signal K1 of power tube Q1 after the negative pole of the second diode and the negative pole parallel connection of the first diode；The outfan of NAND gate M4 is as control signal K2 of power tube Q2；As control signal K3 of power tube Q3 after the positive input terminal of NAND gate M4 and negative input end parallel connection, wherein, A, B are the level that bus sampled voltage compares with reference voltage, and C is the level that accumulator sampled voltage compares with reference voltage.
Topological circuit for satellite power system power adjustments the most according to claim 1, it is characterised in that the control logic of described T-shape integration main circuit topology is:
The shade phase, accumulator carrys out powering load by electric discharge, and at this moment metal-oxide-semiconductor Q1, Q3 is in off state, and Q2 is in PWM state；
Illumination period, solar battery array passes through power diode powering load；
Illumination period, when load operation is in peak power, solar battery array and accumulator combine power supply, and at this moment metal-oxide-semiconductor Q2 is in PWM state, and Q1, Q3 are in off state；
Illumination period, when the output of solar battery array is more than load power demand, accumulator is charged by solar battery array, and at this moment metal-oxide-semiconductor Q1 is in PWM state, and Q2, Q3 are in off state；
Illumination period, when solar battery array output meets loading demands, and accumulator fills with, and solar battery array carries out shunt regulating, and at this moment metal-oxide-semiconductor Q1, Q2 is in PWM state, and Q3 is in off state.
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| CN201210526424.2A CN103872749B (en) | 2012-12-10 | 2012-12-10 | Topological circuit for satellite power system power adjustments |
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| CN103872749B true CN103872749B (en) | 2016-08-03 |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104821782B (en) * | 2015-05-06 | 2017-01-18 | 上海空间电源研究所 | Software-hardware combined shunting control device and method |
| CN105529766B (en) * | 2015-12-07 | 2019-05-28 | 上海空间电源研究所 | A kind of anti-overcharge device applied to S4R type circuit |
| CN106410936B (en) * | 2016-08-31 | 2018-08-31 | 航天东方红卫星有限公司 | A kind of large power high efficiency satellite power system based on high-low pressure double-bus |
| CN106428637B (en) * | 2016-10-14 | 2019-03-26 | 深圳航天科技创新研究院 | A kind of full electric propulsion power system |
| CN107360648A (en) * | 2017-07-28 | 2017-11-17 | 株洲麦格米特电气有限责任公司 | A kind of two paths of LED of Buck topologys flows drive circuit |
| CN109710019B (en) * | 2019-01-10 | 2020-09-25 | 深圳航天东方红海特卫星有限公司 | Output power shunt control circuit of satellite-borne solar cell array |
| CN109904853B (en) * | 2019-04-19 | 2022-12-06 | 四川长虹电源有限责任公司 | Direct-current power supply system and electric device |
| CN111030077B (en) * | 2019-12-23 | 2021-08-13 | 中国电子科技集团公司第十八研究所 | Shunt regulation circuit for solar cell array switch and regulation method based on shunt regulation circuit |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN2773976Y (en) * | 2004-10-27 | 2006-04-19 | 新疆新能源股份有限公司 | Self-recognition intelligent solar charging controller with 50W |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN2773976Y (en) * | 2004-10-27 | 2006-04-19 | 新疆新能源股份有限公司 | Self-recognition intelligent solar charging controller with 50W |
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