CN107482611A - A kind of restructural double-bus spacecraft power supply system - Google Patents
A kind of restructural double-bus spacecraft power supply system Download PDFInfo
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- CN107482611A CN107482611A CN201710608290.1A CN201710608290A CN107482611A CN 107482611 A CN107482611 A CN 107482611A CN 201710608290 A CN201710608290 A CN 201710608290A CN 107482611 A CN107482611 A CN 107482611A
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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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- Direct Current Feeding And Distribution (AREA)
Abstract
A kind of restructural double-bus spacecraft power supply system, diode D1 anodes connect voltage stabilizing bus, negative electrode connects diode D2 negative electrodes, voltage regulation load R1 one end, the voltage regulation load R1 other ends are grounded, diode D2 anodes connect grid-connection control device output end, net-connected controller input terminating diode D3 negative electrodes, highpowerpulse load R2 one end, highpowerpulse load R2 other end ground connection, diode D3 anodes connect Low ESR bus；Grid-connection control device output end voltage is provided to voltage regulation load R1 burning voltage no more than voltage regulation load R1.The present invention realizes that high-quality adjusts bus and low output impedance and do not adjust the reconstruct of bus double-bus entirely by grid-connecting apparatus, realizes that voltage stabilizing bus backs up, enhances reliability, improve solar battery array power utilization；Using independent double-bus, steady load and pulse load are separately powered, broad power band, highpowerpulse loading demand can be met, there is good using effect.
Description
Technical field
The present invention relates to spacecraft design for power supply and distribution field, particularly a kind of restructural double-bus spacecraft power supply system.
Background technology
Current main-stream spacecraft power supply system uses single busbar power-supply system, and single busbar power supply system is that primary power source list is female
Line exports, and steady load and pulse load share a power supply buses, and advantage is that the number of devices of power-supply system is less, volume weight
Amount it is smaller, can abundant reasonable energy utilization, advantage of lower cost；But there is the frequency that pulse load is brought to power supply buses in it
Domain and noise in time domain interference are big, and the filtering technique of antijamming capability and power-supply system to electrical equipment on bus is exigent
Problem, it is therefore desirable to propose a kind of new spacecraft power supply power supply technique.
The content of the invention
Present invention solves the technical problem that it is：A kind of overcome the deficiencies in the prior art, there is provided restructural double-bus space flight
Device power-supply system, solve the problems, such as that interference and double-bus of the highpowerpulse load to bus can not reconstruct, ensureing stabilization
Load high-quality power demands in the case of, can meet broad power band, it is long when highpowerpulse load supplying demand, improve
Spacecraft power supply system power supply reliability and power utilization.
The present invention technical solution be：A kind of restructural double-bus spacecraft power supply system, including diode D1, two
Pole pipe D2, diode D3, voltage regulation load R1, highpowerpulse load R2, grid-connection control device, voltage stabilizing bus, Low ESR bus；
Diode D1 anodes connect voltage stabilizing bus, and negative electrode connects diode D2 negative electrodes, voltage regulation load R1 one end, another terminations of voltage regulation load R1
Ground, diode D2 anodes connect grid-connection control device output end, net-connected controller input terminating diode D3 negative electrodes, highpowerpulse
R2 one end, highpowerpulse load R2 other end ground connection are loaded, diode D3 anodes connect Low ESR bus；Grid-connection control device is defeated
It is VoutF to go out terminal voltage, and VoutF is provided to voltage regulation load R1 burning voltage VoutP no more than voltage regulation load R1.
Described grid-connection control device includes DCDC1, DCDC2, DCDC3 ..., DCDCn, diode D1, D2, D3 ...,
Dn, switch K1, K2, accessory power supply；DCDC1, DCDC2, DCDC3 ..., DCDCn is in parallel to form DCDC groups, and DCDC groups one end passes through
Switch K1 is connected to Low ESR bus, another terminating diode Di anodes of DCDCi in DCDC groups, diode D1, D2, D3 ..., and Dn is cloudy
Pole connects voltage stabilizing bus by switching K2, and accessory power supply is the power supply of DCDC groups, makes switch K2 output voltages VoutF to voltage stabilizing bus,
Wherein, i=1,2,3 ..., n, n are positive integer.
Described accessory power supply is redundancy backup.
Described accessory power supply is that the voltage of DCDC groups power supply is 12V.
The present invention compared with prior art the advantages of be：
(1) present invention gives steady load and highpowerpulse load supplying respectively using two mutual independent buses, solves
The interference problem of highpowerpulse of having determined load, it is not required to carry out particularly filtering and Anti-interference Design, system design is simply, stably
Reliably；
(2) present invention realizes that high-quality adjusts bus and low output impedance and do not adjust bus double-bus entirely by grid-connecting apparatus
Reconstruct, realize that voltage stabilizing bus backs up, enhance reliability, improve solar battery array power utilization；
(3) present invention uses independent double-bus, and steady load and pulse load are separately powered, can meet wide power model
Enclose, highpowerpulse loading demand, and high-quality bus power supply can be provided to steady load.
Brief description of the drawings
Fig. 1 is a kind of restructural double-bus spacecraft power supply system construction drawing；
Fig. 2 is grid-connection control device schematic diagram.
Embodiment
The present invention proposes a kind of restructural double-bus spacecraft power supply system in view of the shortcomings of the prior art, as shown in Figure 1
For a kind of restructural double-bus spacecraft power supply system construction drawing, including diode D1, D2, D3, voltage regulation load R1, high-power arteries and veins
Punching load R2, grid-connection control device, high-quality adjust bus (abbreviation voltage stabilizing bus) entirely, low output impedance does not adjust bus (letter
Claim Low ESR bus).It is all the bus of design fixed value that voltage stabilizing bus, which refers to illumination period and shade phase output voltage, and Low ESR is female
Line refers in illumination period or all unfixed bus of shade phase output voltage.The high-quality of voltage stabilizing bus is relative to low
For impedance bus, output voltage stability and dynamic characteristic are mainly reflected in, in sudden unloading process nominal load, output voltage
Change no more than design load 2%, voltage recovery time is less than 5ms.Low ESR bus, which is embodied in, can meet highpowerpulse
The power reguirements of load, the present invention are realized by lithium-ions battery, i.e., Low ESR bus exports with lithium-ions battery
End connection, so as to realize its low output impedance characteristic.Diode D1 anode connection voltage stabilizing bus, negative electrode connection diode D2's
Negative electrode and voltage regulation load R1 one end, voltage regulation load R1 other ends ground connection.Diode D2 anode and grid-connection control device output end
It is connected, one end that net-connected controller input loads R2 with diode D3 negative electrode and highpowerpulse is connected, highpowerpulse
Load R2 other end ground connection.Diode D3 anode is connected to Low ESR bus.
Power-supply system of the present invention is connected using double independent busbars by grid-connection control device, and voltage stabilizing bus is to steady
Fixed load is powered, it is ensured that its power supply quality, Low ESR bus give highpowerpulse load supplying, and two buses are separate, no
Interference is produced, meets the power demands of different loads.Voltage stabilizing bus is full regulation bus, and under normal circumstances, voltage stabilizing bus is all the time
Stabilization disclosure satisfy that voltage regulation load requirement in setting value VoutP.Under abnormal conditions, voltage stabilizing bus power deficiency or mistake
After effect, voltage stabilizing bus output voltage VoutP is reduced, and the output of voltage stabilizing bus after isolating diode D1 isolation with cutting-in control by filling
The connection of output end isolating diode D2 negative electrodes is put, forms voltage stabilizing bus powering load.Low ESR bus is does not adjust bus, directly
Accumulator output end is connect in succession, thus there is very low output impedance, can bear big pulse load electric current, and bus output is straight
Connect and be connected with the load of Low ESR bus and grid-connection control device input.
Grid-connected reconstruct device is as shown in Fig. 2 by DCDC groups in parallel DCDC1~DCDCn, (DCDC is by one kind including one group
DC power conversion be another direct current electronics converting means), diode D1~Dn, switch K1 and K2, accessory power supply.
DCDC1~DCDCn inputs link together, and are connected to by switching K1 and do not adjust bus, DCDC1~DCDCn output
End is respectively connecting to the anode of diode D1~Dn for isolation, and the negative electrode of D1~Dn diodes links together, and passes through
Switch K2 connection voltage stabilizing buses.In addition, also including an accessory power supply for having master backup, the input of accessory power supply is not with adjusting
Bus is connected, output end output ± 12V supply voltages.± 12V supply voltages provide power supply to DCDC1~DCDCn control circuits.
Two buses are connected by grid-connected reconstruct device, and grid-connected reconstruct device is one group of controlled dcdc converter.Such as Fig. 2 institutes
Show, Low ESR bus is that dcdc converter group input is connected with grid-connection control device input by controlling switch K1, grid-connected
Control device output end is that DCDC output ends are connected by switching K2 after isolating diode D2 isolation with voltage stabilizing bus.Voltage stabilizing is female
Line stabilization value is that definite value VoutP, DCDC group output voltage stabilization value is definite value VoutF, and VoutP>VoutF.When voltage stabilizing bus
When voltage is more than VoutF, DCDC groups not power output, when voltage stabilizing busbar voltage is less than VoutF, DCDC group power outputs, and
The output voltage for maintaining DCDC is VoutF.During normal work, due to VoutP>VoutF, now voltage stabilizing bus power output can
Meet voltage regulation load requirement, DCDC groups not power output.When the underpower that voltage stabilizing bus provides, cause voltage stabilizing busbar voltage
Decline, when voltage stabilizing busbar voltage is equal to or less than VoutF, DCDC groups begin through Low ESR bus to voltage stabilizing bus output work
Rate, voltage stabilizing bus decline more, and the power that DCDC groups export is bigger, so as to maintain DCDC groups output voltage stabilization in VoutF,
Realize grid-connected.So the backup of voltage stabilizing bus is achieved that, improves the reliability and energy utilization rate of system.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (4)
1. a kind of restructural double-bus spacecraft power supply system, it is characterised in that including diode D1, diode D2, diode
D3, voltage regulation load R1, highpowerpulse load R2, grid-connection control device, voltage stabilizing bus, Low ESR bus；Diode D1 anodes
Voltage stabilizing bus is connect, negative electrode connects diode D2 negative electrodes, voltage regulation load R1 one end, voltage regulation load R1 other ends ground connection, diode D2 sun
Pole connects grid-connection control device output end, and net-connected controller input terminating diode D3 negative electrodes, highpowerpulse load R2 one end, greatly
The power pulse loads R2 other ends are grounded, and diode D3 anodes connect Low ESR bus；Grid-connection control device output end voltage is
VoutF, VoutF are provided to voltage regulation load R1 burning voltage VoutP no more than voltage regulation load R1.
A kind of 2. restructural double-bus spacecraft power supply system according to claim 1, it is characterised in that：Described is grid-connected
Control device includes DCDC1, DCDC2, DCDC3 ..., DCDCn, diode D1, D2, D3 ..., Dn, switchs K1, K2, auxiliary electricity
Source；DCDC1, DCDC2, DCDC3 ..., DCDCn is in parallel to form DCDC groups, and DCDC groups one end is connected to Low ESR mother by switching K1
Line, another terminating diode Di anodes of DCDCi in DCDC groups, diode D1, D2, D3 ..., Dn negative electrodes connect voltage stabilizing by switching K2
Bus, accessory power supply are powered for DCDC groups, make switch K2 output voltages VoutF to voltage stabilizing bus, wherein, i=1,2,3 ..., n,
N is positive integer.
A kind of 3. restructural double-bus spacecraft power supply system according to claim 1 or 2, it is characterised in that：Described
Accessory power supply is redundancy backup.
A kind of 4. restructural double-bus spacecraft power supply system according to claim 1 or 2, it is characterised in that：Described
Accessory power supply is that the voltage of DCDC groups power supply is 12V.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710608290.1A CN107482611A (en) | 2017-07-24 | 2017-07-24 | A kind of restructural double-bus spacecraft power supply system |
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| CN201710608290.1A CN107482611A (en) | 2017-07-24 | 2017-07-24 | A kind of restructural double-bus spacecraft power supply system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111342673A (en) * | 2020-04-08 | 2020-06-26 | 唐山航宇电力电子设备有限公司 | Space dual-redundancy power circuit |
| CN111416335A (en) * | 2020-04-30 | 2020-07-14 | 上海空间电源研究所 | Double-bus solar cell array output power control system |
| CN112636444A (en) * | 2020-12-07 | 2021-04-09 | 上海卫星工程研究所 | Double-star combined spacecraft grid-connected power supply and distribution system with fully-regulated unified bus |
| CN113612253A (en) * | 2021-08-06 | 2021-11-05 | 北京空间飞行器总体设计部 | High-voltage bus spacecraft power grid-connected control device |
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| CN102904278A (en) * | 2012-09-20 | 2013-01-30 | 江苏万丰光伏有限公司 | Distribution type grid connection photovoltaic system power supply |
| CN104638991A (en) * | 2015-01-28 | 2015-05-20 | 江苏大学 | Double-bus power converter for inhibiting torque pulsation of switched reluctance motor and control method thereof |
| CN106410936A (en) * | 2016-08-31 | 2017-02-15 | 航天东方红卫星有限公司 | High-power high-efficiency satellite power supply system based on high voltage and low voltage double buses |
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| CN102904278A (en) * | 2012-09-20 | 2013-01-30 | 江苏万丰光伏有限公司 | Distribution type grid connection photovoltaic system power supply |
| CN102882256A (en) * | 2012-10-12 | 2013-01-16 | 广东易事特电源股份有限公司 | Uninterrupted power supply (UPS) with double-busbar charging circuit |
| CN104638991A (en) * | 2015-01-28 | 2015-05-20 | 江苏大学 | Double-bus power converter for inhibiting torque pulsation of switched reluctance motor and control method thereof |
| CN106410936A (en) * | 2016-08-31 | 2017-02-15 | 航天东方红卫星有限公司 | High-power high-efficiency satellite power supply system based on high voltage and low voltage double buses |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111342673A (en) * | 2020-04-08 | 2020-06-26 | 唐山航宇电力电子设备有限公司 | Space dual-redundancy power circuit |
| CN111416335A (en) * | 2020-04-30 | 2020-07-14 | 上海空间电源研究所 | Double-bus solar cell array output power control system |
| CN111416335B (en) * | 2020-04-30 | 2021-04-06 | 上海空间电源研究所 | Double-bus solar cell array output power control system |
| CN112636444A (en) * | 2020-12-07 | 2021-04-09 | 上海卫星工程研究所 | Double-star combined spacecraft grid-connected power supply and distribution system with fully-regulated unified bus |
| CN113612253A (en) * | 2021-08-06 | 2021-11-05 | 北京空间飞行器总体设计部 | High-voltage bus spacecraft power grid-connected control device |
| CN113612253B (en) * | 2021-08-06 | 2024-02-09 | 北京空间飞行器总体设计部 | High-voltage bus spacecraft power grid-connected control device |
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Application publication date: 20171215 |