CN106410893A - Automatic charging control method for lithium battery spacecraft - Google Patents
Automatic charging control method for lithium battery spacecraft Download PDFInfo
- Publication number
- CN106410893A CN106410893A CN201610844474.3A CN201610844474A CN106410893A CN 106410893 A CN106410893 A CN 106410893A CN 201610844474 A CN201610844474 A CN 201610844474A CN 106410893 A CN106410893 A CN 106410893A
- Authority
- CN
- China
- Prior art keywords
- voltage
- lithium battery
- charging
- battery group
- out constant
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000007600 charging Methods 0.000 title claims abstract description 73
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 title claims abstract description 58
- 229910052744 lithium Inorganic materials 0.000 title claims abstract description 58
- 238000000034 method Methods 0.000 title claims abstract description 22
- 239000000178 monomer Substances 0.000 claims abstract description 20
- 230000005611 electricity Effects 0.000 claims description 11
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 5
- 238000005259 measurement Methods 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 claims description 3
- 238000010277 constant-current charging Methods 0.000 abstract 2
- 238000007599 discharging Methods 0.000 abstract 1
- 229910001416 lithium ion Inorganic materials 0.000 description 13
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 8
- 230000006870 function Effects 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 2
- 230000007257 malfunction Effects 0.000 description 2
- 206010011906 Death Diseases 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000004069 differentiation Effects 0.000 description 1
- 230000003862 health status Effects 0.000 description 1
- 150000002500 ions Chemical class 0.000 description 1
- 230000006386 memory function Effects 0.000 description 1
Classifications
-
- 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
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0013—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries acting upon several batteries simultaneously or sequentially
- H02J7/0014—Circuits for equalisation of charge between batteries
- H02J7/0016—Circuits for equalisation of charge between batteries using shunting, discharge or bypass circuits
-
- H02J7/0026—
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
- Secondary Cells (AREA)
Abstract
The invention relates to an automatic charging control method for a lithium battery spacecraft. The method comprises the following steps of obtaining a series stage N of a lithium battery pack, a lower limit A of input voltage of a discharging module, and an upper limit U and a lower limit W of voltage of a parallel block battery monomer; measuring total voltage v of the lithium battery pack, carrying out constant current charging when v is not less than N*U and stopping charging when v reaches N*U; measuring voltage v1, vi to vN of each parallel block battery monomer of the lithium battery pack and determining a number t when the voltage is 0; when t=0, carrying out constant current charging at charging reference voltage of N*U; when t is not greater than (formula) and is greater than 0, switching the charging reference voltage to (N-t)*U from N*U, and when the total voltage v of the lithium battery pack reaches (N-t)*U, stopping charging; and when t is greater than (formula), outputting an alarm signal to an aircraft control system. According to the automatic charging control method, the potential safety hazard from overcharging of the lithium battery, which is caused by adopting the single reference source in the conventional aircraft, is avoided; and the occurrence of the phenomenon of long-time overcharging of the lithium battery is effectively prevented.
Description
Technical field
The present invention relates to a kind of spacecraft lithium battery charging controller method, belong to field of batteries.
Background technology
Power-supply system is one of important subsystem of spacecraft.Lithium-ions battery is used in a large number on spacecraft
Group, is used cooperatively with solar array and realizes to aircraft holocyclic function of supplying power.In sunny side, solar array is except supplying for load
Electricity is outer, also unnecessary energy charges for lithium-ions battery group and realizes accumulation of energy function；In the back, lithium-ions battery group is discharged
There is provided electric energy for aircraft.
On Traditional Space aircraft, lithium-ions battery group adopts single charge control method, once lithium-ions battery
After group occurs monomer to lose efficacy, batteries can overcharge phenomenon, leads to battery cyclic life time decay to accelerate, finally due to lithium
The ion accumulator group life-span expires, lead to spacecraft due to short of electricity end-of-life.
How to prevent occur under lithium-ions battery group monomer failure conditions to overcharge phenomenon, need designed in advance pre-
Anti-.
Content of the invention
It is an object of the invention to overcoming the deficiencies in the prior art, provide a kind of spacecraft lithium battery automatic charging control
Method processed, solves the problems, such as that under monomer short-circuit conditions, lithium battery overcharge causes function of supplying power to lose efficacy and the long-time mistake of lithium battery
The problem that the life-span being charged into and leading to significantly decays.
The object of the invention is achieved by following technical solution：
A kind of spacecraft lithium battery charging controller method is provided, comprises the steps：
(1) obtain lithium battery group series connection series N, discharge module input voltage lower limit A, on the voltage of parallel-connected blocks battery cell
Limit U and lower limit W；
(2) measure total voltage v of lithium battery group, as v≤N*U, carry out constant-current charge, when v reaches N*U, stop filling
Electricity；
(3) measure the voltage v of each parallel-connected blocks battery cell of lithium battery group1…vi…vN, determine quantity t wherein for 0；
(4) as t=0, charging reference voltage carries out constant-voltage charge for N*U；When≥t>0, charging base
Quasi- voltage switches to (N-t) * U by N*U, carries out constant-current charge, when total voltage v of lithium battery group reaches (N-t) * U, stops filling
Electricity；WhenWhen, output alarm signal is to flight control system.
Preferably, in step (4) whenWhen, output alarm signal to flight control system, and
It is directly load supplying that charging module is switched to, and no longer charges for lithium battery group.
A kind of spacecraft lithium battery charging controller method is provided, comprises the steps：
(1) obtain lithium battery group series connection series N, discharge module input voltage lower limit A, on the voltage of parallel-connected blocks battery cell
Limit U and lower limit W；
(2) measure total voltage v of lithium battery group, as v≤N*U, carry out constant-current charge, when v reaches N*U, stop filling
Electricity；
(3) the voltage v of total voltage v of measurement lithium battery group and each parallel-connected blocks battery cell1…vi…vN, determine wherein
Meet the voltage value v of monomer simultaneouslyi<W and | vi-v/(N-t)|>Fail battery amount of monomer t of 40% × (U+W)/2, when
During t=0, charging reference voltage carries out constant-voltage charge for N*U；WhenCharging reference voltage is by N*U
Switch to (N-t) * U, carry out constant-current charge, when total voltage v of lithium battery group reaches (N-t) * U, stop charging；WhenWhen, output alarm signal.
Preferably, when charging reference voltage switches to (N-t) * U by N*U, also include monitoring fault parallel-connected piece of battery list
Bulk voltage vi, as fail battery monomer voltage viReturn to W≤viWhen the quantity of≤U is s, 1≤s≤t, will charge reference voltage
(N-t+s) * U is switched to by (N-t) * U.
The present invention compared with prior art has the advantage that：
(1) the charging controller method of the present invention avoids in conventional aircraft and leads to lithium battery using unity reference source
The potential safety hazard that overcharge brings；It is effectively prevented lithium battery and overcharge phenomenon generation for a long time.
(2) the charging controller method of the present invention extends the service life cycle of lithium battery it is ensured that spacecraft is used
The reliability of electricity and security.
(3) the charging controller method of the present invention, it is contemplated that the differentiation of monomer fault mode, improves lithium battery capacity profit
With rate.
(4) the charging controller method of the present invention, had both considered the independent lower limit of monomer voltage, had considered multiple lists
The uniformity of bulk voltage, it is to avoid switch by mistake, further increase the reliability of system.
Brief description
Fig. 1 is the theory diagram of spacecraft lithium battery charging controller of the present invention；
Fig. 2 is (N-1) level charging termination reference voltage state；
Fig. 3 is (N-X) level charging termination reference voltage state.
Specific embodiment
Spacecraft Electrical Power System is made up of Li-ion batteries piles, solar battery array and controller and load, its center
Heart equipment is controller.Wherein Li-ion batteries piles serial number is N, and load number is M.Using multistage charging termination reference voltage
Provisioning Policy, arranges suitable end of charge voltage benchmark.Using the method for voltage automatic interpretation, switching charging termination bar in time
Part, is effectively prevented lithium battery and overcharges phenomenon generation for a long time.
Controller is again by charging module, discharge module, processor module, storage module and automatic interpretation circuit module group
Become：
Charging module realizes the charging control function to lithium-ions battery group, typically adopts constant current or constant-voltage charge to control
Method.With constant-current charge, stop when accumulator battery voltage reaches certain value to battery charging (this magnitude of voltage referred to as charging
Final pressure)；With constant-voltage charge, accumulator battery voltage close to constant voltage value when (charging current close to zero when), stop charging.
Discharge module realizes the control of discharge function to batteries, typically adopts boost step-up discharge circuit, this circuit
Input voltage range be AV to BV between.
Pre- bookbinding software in processor module, realizes the charging strategy execution to lithium-ions battery group and algorithm clearing control
Function processed.
Storage module is typically made up of RAM and ROM, in ROM prevent software program, during execution processor by software program from
ROM is loaded in RAM, realizes the real-time memory function of program code.
Total voltage v of lithium battery group and each parallel-connected blocks battery list that automatic interpretation circuit module foundation A/D chip collects
The voltage v of body1…vi…vN, under the control of a processor, execute charge control strategy, realize the automatic charging to batteries
Control function.
Spacecraft lithium battery charging controller method, comprises the steps：
(1) obtain lithium battery group serial number N, discharge module input voltage lower limit A, on the voltage of parallel-connected blocks battery cell
Limit U and lower limit W；
(2) measure total voltage v of lithium battery group, as v≤N*U, carry out constant-current charge, when v reaches N*U, stop filling
Electricity；
(3) measure the voltage v of each parallel-connected blocks battery cell of lithium battery group1…vi…vN, determine quantity t wherein for 0；
(4) as t=0, charging reference voltage carries out constant-voltage charge for N*U；When≥t>0, charging base
Quasi- voltage switches to (N-t) * U by N*U, carries out constant-current charge, when total voltage v of lithium battery group reaches (N-t) * U, stops filling
Electricity；WhenWhen, output alarm signal is to flight control system, and charging module is switched to is directly
Load supplying, no longer charges for lithium battery group.Represent that the ratio to A and W rounds up.Batteries are less thanSection monomer short-circuit condition, abbreviation subhealthy status, after automatic charging adjusts control, system being capable of normal operating conditions；
When exceedingSection monomer short-circuit condition, then cisco unity malfunction state after automatic charging adjusts and controls, is unhealthy
State；When batteries are in sub-health state, battery status can be made to return to healthy shape by charging controller system
State；When batteries are in unhealthy condition, charging controller system provides prompt alarm, and output alarm signal gives flight
Device control system.
Under N level charging reference voltage state (state one), referring to accompanying drawing 1, charging reference voltage is (U*N) V, the sun
Cell array is (U*N) V for the final voltage that Li-ion batteries piles charge；In (N-1) level charging reference voltage state (state
Two) under, referring to accompanying drawing 2, charging reference voltage is (U*N-U) V, the final voltage that solar battery array charges for Li-ion batteries piles
For (U*N-U) V；As t=X, under (N-X) level charging reference voltage state (state three), referring to accompanying drawing 3, charging benchmark
Voltage is (U*N-U*t) V, and solar battery array is (U*N-U*t) V for the final voltage that Li-ion batteries piles charge, whereinCase above all can realize the charging controller to batteries by controller so that storing
Battery pack returns to health status by sub-health state.
When t is more thanWhen, because the output voltage of batteries is less than the input service voltage of discharge module
Lower limit AV, leads to whole system can not be load normal power supply, therefore no longer switches charging termination reference voltage, provide announcement in advance
Alert prompting, shows system cisco unity malfunction.
Another kind of spacecraft lithium battery charging controller method is provided, comprises the steps：
(1) obtain lithium battery group serial number N, discharge module input voltage lower limit A, upper voltage limit U of battery cell and
Lower limit W；
(2) measure total voltage v of lithium battery group, as v≤N*U, carry out constant-current charge, when v reaches N*U, stop filling
Electricity；
(3) the voltage v of total voltage v of measurement lithium battery group and each battery cell1…vi…vN, determine wherein simultaneously full
The voltage value v of sufficient monomeri<W and | vi-v/(N-t)|>Fail battery amount of monomer t of 40% × (U+W)/2, works as t=0
When, charging reference voltage carries out constant-voltage charge for N*U；WhenCharging reference voltage is switched by N*U
To (N-t) * U, carry out constant-voltage charge, when total voltage v of lithium battery group reaches (N-t) * U, stop charging；WhenWhen, output alarm signal.
When the fault of cell develops into open fault by short trouble, this batteries in parallel connection monomer recovers to use, to
Raise whole reference voltage to charge.When charging reference voltage switches to (N-t) * U by N*U, also include monitoring fail battery monomer
Voltage vi, as fail battery monomer voltage viReturn to W≤viThe quantity of≤U be s when, 1≤s≤t, by charging reference voltage by
(N-t) * U switches to (N-t+s) * U.
By the multistage automatic switchover scheme of end of charge voltage benchmark under monomer short circuit failure mode it is achieved that lithium battery
The matched well of working condition and end of charge voltage benchmark, it is to avoid in conventional aircraft lithium electricity led to using unity reference source
The potential safety hazard that pond overcharge brings.
The above, the only optimal specific embodiment of the present invention, but protection scope of the present invention is not limited thereto,
Any those familiar with the art the invention discloses technical scope in, the change or replacement that can readily occur in,
All should be included within the scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (4)
1. a kind of spacecraft lithium battery charging controller method is it is characterised in that comprise the steps：
(1) lithium battery group series connection series N, discharge module input voltage lower limit A, upper voltage limit U of parallel-connected blocks battery cell are obtained
With lower limit W；
(2) measure total voltage v of lithium battery group, as v≤N*U, carry out constant-current charge, when v reaches N*U, stop charging；
(3) measure the voltage v of each parallel-connected blocks battery cell of lithium battery group1…vi…vN, determine quantity t wherein for 0；
(4) as t=0, charging reference voltage carries out constant-voltage charge for N*U；When≥t>0, charging benchmark electricity
Pressure switches to (N-t) * U by N*U, carries out constant-current charge, when total voltage v of lithium battery group reaches (N-t) * U, stops charging；
WhenWhen, output alarm signal is to flight control system.
2. spacecraft lithium battery charging controller method as claimed in claim 1 is it is characterised in that in step (4)
WhenWhen, output alarm signal is to flight control system, and charging module is switched to is directly negative
Carry power supply, no longer charge for lithium battery group.
3. a kind of spacecraft lithium battery charging controller method is it is characterised in that comprise the steps：
(1) lithium battery group series connection series N, discharge module input voltage lower limit A, upper voltage limit U of parallel-connected blocks battery cell are obtained
With lower limit W；
(2) measure total voltage v of lithium battery group, as v≤N*U, carry out constant-current charge, when v reaches N*U, stop charging；
(3) the voltage v of total voltage v of measurement lithium battery group and each parallel-connected blocks battery cell1…vi…vN, determine wherein simultaneously
Meet the voltage value v of monomeri<W and vi-v/(N-t)|>Fail battery amount of monomer t of 40% × (U+W)/2, works as t=0
When, charging reference voltage carries out constant-voltage charge for N*U；WhenCharging reference voltage is switched by N*U
To (N-t) * U, carry out constant-current charge, when total voltage v of lithium battery group reaches (N-t) * U, stop charging；WhenWhen, output alarm signal.
4. the spacecraft lithium battery charging controller method as described in claim 1 or 3 charges it is characterised in that working as
When reference voltage switches to (N-t) * U by N*U, also include monitoring fault parallel-connected piece of battery cell voltage vi, when fail battery list
Bulk voltage viReturn to W≤viWhen the quantity of≤U is s, 1≤s≤t, charging reference voltage is switched to (N-t+ by (N-t) * U
s)*U.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610844474.3A CN106410893B (en) | 2016-09-22 | 2016-09-22 | A kind of spacecraft lithium battery charging controller method |
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| CN201610844474.3A CN106410893B (en) | 2016-09-22 | 2016-09-22 | A kind of spacecraft lithium battery charging controller method |
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| Publication Number | Publication Date |
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| CN106410893B CN106410893B (en) | 2018-12-21 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113904417A (en) * | 2021-11-04 | 2022-01-07 | 东莞光亚智能科技有限公司 | Constant-voltage component-capacitance system for series battery monomers and control method thereof |
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| JPH10154503A (en) * | 1996-11-26 | 1998-06-09 | Shin Kobe Electric Mach Co Ltd | Battery pack |
| CN200990506Y (en) * | 2006-09-15 | 2007-12-12 | 李鹏 | Circuit for realizing multi-section serial secondary pile protection with unit management |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113904417A (en) * | 2021-11-04 | 2022-01-07 | 东莞光亚智能科技有限公司 | Constant-voltage component-capacitance system for series battery monomers and control method thereof |
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| Publication number | Publication date |
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| CN106410893B (en) | 2018-12-21 |
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