CN106410893B - A kind of spacecraft lithium battery charging controller method - Google Patents

A kind of spacecraft lithium battery charging controller method Download PDF

Info

Publication number
CN106410893B
CN106410893B CN201610844474.3A CN201610844474A CN106410893B CN 106410893 B CN106410893 B CN 106410893B CN 201610844474 A CN201610844474 A CN 201610844474A CN 106410893 B CN106410893 B CN 106410893B
Authority
CN
China
Prior art keywords
voltage
lithium battery
charging
battery group
carries out
Prior art date
Application number
CN201610844474.3A
Other languages
Chinese (zh)
Other versions
CN106410893A (en
Inventor
李海伟
杨友超
张翔
徐海运
赵岩
潘江江
姜爽
陈玉坤
张声艳
曾贵明
王健康
欧连军
王国庆
胡倩
Original Assignee
中国运载火箭技术研究院
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 中国运载火箭技术研究院 filed Critical 中国运载火箭技术研究院
Priority to CN201610844474.3A priority Critical patent/CN106410893B/en
Publication of CN106410893A publication Critical patent/CN106410893A/en
Application granted granted Critical
Publication of CN106410893B publication Critical patent/CN106410893B/en

Links

Abstract

The present invention relates to a kind of spacecraft lithium battery charging controller method, include the following steps: to obtain lithium battery group series connection series N, discharge module input voltage lower limit A, the upper voltage limit U and lower limit W of parallel-connected blocks battery cell;The total voltage v for measuring lithium battery group carries out constant-current charge as v≤N*U, when v reaches N*U, stops charging;Measure the voltage v of each parallel-connected blocks battery cell of lithium battery group1…vi…vN, determine the quantity t wherein for 0;As t=0, charging reference voltage is that N*U carries out constant-voltage charge;WhenCharging reference voltage switches to (N-t) * U by N*U, carries out constant-voltage charge, when the total voltage v of lithium battery group reaches (N-t) * U, stops charging;WhenWhen, alarm signal is exported to flight control system.Charging controller method of the invention, which avoids in conventional aircraft, leads to lithium battery overcharge bring security risk using unity reference source;It is effectively prevented lithium battery and overcharges phenomenon for a long time.

Description

A kind of spacecraft lithium battery charging controller method

Technical field

The present invention relates to a kind of spacecraft lithium battery charging controller methods, belong to field of batteries.

Background technique

Power-supply system is one of important subsystem of spacecraft.Lithium-ions battery is largely used on spacecraft Group, with solar array with the use of the function of supplying power realized to the aircraft complete period.In sunny side, solar array for load in addition to supplying It is electric outer, it is also that accumulation of energy function is realized in the charging of lithium-ions battery group by extra energy;In the back, the electric discharge of lithium-ions battery group Electric energy is provided for aircraft.

Lithium-ions battery group uses single charge control method on Traditional Space aircraft, once lithium-ions battery After monomer failure occurs for group, battery group can overcharge phenomenon, cause battery cyclic life time decay to accelerate, finally due to lithium The ion accumulator group service life expires, cause spacecraft due to short of electricity end-of-life.

How to prevent what is occurred under lithium-ions battery group monomer failure conditions to overcharge phenomenon, needs to design in advance pre- It is anti-.

Summary of the invention

It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of spacecraft lithium battery automatic charging controls Method processed solves the problems, such as under monomer short-circuit conditions that lithium battery overcharge causes function of supplying power to fail and lithium battery long-time mistake The problem of service life substantially decays caused by being charged into.

The object of the invention is achieved by following technical solution:

A kind of spacecraft lithium battery charging controller method is provided, is included the following steps:

(1) it obtains lithium battery group to connect 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) the total voltage v for measuring lithium battery group carries out constant-current charge and stops filling when v reaches N*U as v≤N*U Electricity;

(3) the voltage v of each parallel-connected blocks battery cell of lithium battery group is measured1…vi…vN, determine the quantity t wherein for 0;

(4) as t=0, charging reference voltage is that N*U carries out constant-voltage charge;When>=t > 0, charge base Quasi- voltage switches to (N-t) * U by N*U, carries out constant-current charge and stops filling when the total voltage v of lithium battery group reaches (N-t) * U Electricity;WhenWhen, alarm signal is exported to flight control system.

Preferably, in step (4) whenWhen, alarm signal is exported to flight control system, and Charging module is switched to directly for load supplying, is no longer lithium battery group charging.

A kind of spacecraft lithium battery charging controller method is provided, is included the following steps:

(1) it obtains lithium battery group to connect 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) the total voltage v for measuring lithium battery group carries out constant-current charge and stops filling when v reaches N*U as v≤N*U Electricity;

(3) the total voltage v of lithium battery group and the voltage v of each parallel-connected blocks battery cell are measured1…vi…vN, determine wherein Meet the voltage value v of monomer simultaneouslyi< W and | vi- v/ (N-t) | the fail battery amount of monomer t of > 40% × (U+W)/2, when When t=0, charging reference voltage is that N*U carries out constant-voltage charge;WhenReference voltage charge by N*U (N-t) * U is switched to, constant-current charge is carried out, when the total voltage v of lithium battery group reaches (N-t) * U, stops charging;WhenWhen, export alarm signal.

It preferably, further include fault parallel-connected piece of battery list of monitoring when the reference voltage that charges switches to (N-t) * U by N*U Bulk voltage vi, as fail battery monomer voltage viIt is restored to W≤viWhen the quantity of≤U is s, 1≤s≤t, by the reference voltage that charges (N-t+s) * U is switched to by (N-t) * U.

The invention has the following advantages over the prior art:

(1) charging controller method of the invention, which avoids in conventional aircraft, leads to lithium battery using unity reference source Overcharge bring security risk;It is effectively prevented lithium battery and overcharges phenomenon for a long time.

(2) charging controller method of the invention extends the service life cycle of lithium battery, guarantees that spacecraft is used The reliability and safety of electricity.

(3) charging controller method of the invention, it is contemplated that the differentiation of monomer fault mode improves lithium battery capacity benefit With rate.

(4) charging controller method of the invention had both considered the independent lower limit of monomer voltage, and had considered multiple lists The consistency of bulk voltage avoids and accidentally switches, further improves the reliability of system.

Detailed description of the invention

Fig. 1 is the functional block diagram of spacecraft lithium battery charging controller of the present invention;

Fig. 2 is (N-1) grade charging termination reference voltage state;

Fig. 3 is (N-X) grade charging termination reference voltage state.

Specific embodiment

Spacecraft Electrical Power System is made of Li-ion batteries piles, solar battery array and controller and load, center Heart equipment is controller.Wherein Li-ion batteries piles serial number is N, load number M.Using multistage charging termination reference voltage Suitable end of charge voltage benchmark is arranged in Provisioning Policy.Using the method for voltage automatic interpretation, switch charging termination item in time Part is effectively prevented lithium battery and overcharges phenomenon for a long time.

Controller is again by charging module, discharge module, processor module, storage module and automatic interpretation circuit module group At:

Charging module realizes the charging control function to lithium-ions battery group, is generally controlled using constant current or constant-voltage charge Method.With constant-current charge, stop when accumulator battery voltage reaches certain value to the battery charging (voltage value referred to as charging Final pressure);With constant-voltage charge, when accumulator battery voltage is close to constant pressure value (charging current close to zero when), stop charging.

Discharge module realizes the control of discharge function to battery group, generally uses boost step-up discharge circuit, the circuit Input voltage range between AV to BV.

Software is bound in processor module in advance, realizes charging strategy execution and algorithm clearing control to lithium-ions battery group Function processed.

Storage module is generally made of RAM and ROM, prevents software program in ROM, when execution processor by software program from ROM is loaded into RAM, realizes the real-time storage function of program code.

Total voltage v and each parallel-connected blocks battery list of the automatic interpretation circuit module according to the collected lithium battery group of A/D chip The voltage v of body1…vi…vN, under the control of a processor, charge control strategy is executed, realizes the automatic charging to battery group Control function.

Spacecraft lithium battery charging controller method, includes the following steps:

(1) lithium battery group serial number N, discharge module input voltage lower limit A are obtained, on the voltage of parallel-connected blocks battery cell Limit U and lower limit W;

(2) the total voltage v for measuring lithium battery group carries out constant-current charge and stops filling when v reaches N*U as v≤N*U Electricity;

(3) the voltage v of each parallel-connected blocks battery cell of lithium battery group is measured1…vi…vN, determine the quantity t wherein for 0;

(4) as t=0, charging reference voltage is that N*U carries out constant-voltage charge;When>=t > 0, charge base Quasi- voltage switches to (N-t) * U by N*U, carries out constant-current charge and stops filling when the total voltage v of lithium battery group reaches (N-t) * U Electricity;WhenWhen, alarm signal is exported to flight control system, and charging module is switched to and is directly Load supplying is no longer lithium battery group charging.Expression rounds up to the ratio of A and W.Battery group is no more thanMonomer short-circuit condition is saved, abbreviation subhealthy status, system being capable of normal operating conditions after automatic charging adjusts control; When being more thanMonomer short-circuit condition is saved, then automatic charging adjusts cisco unity malfunction state after control, is unhealthy State;When battery group is in sub-health state, battery status can be made to be restored to healthy shape by charging controller system State;When battery group is in unhealthy condition, charging controller system provides prompt alarm, exports alarm signal to flight Device control system.

Under N grades of charging reference voltage states (state one), referring to attached drawing 1, charging reference voltage is (U*N) V, the sun Cell array is that the final voltage of Li-ion batteries piles charging is (U*N) V;In (N-1) grade charging reference voltage state (state Two) under, referring to attached drawing 2, charging reference voltage is (U*N-U) V, and solar battery array is the final voltage of Li-ion batteries piles charging For (U*N-U) V;It as t=X, charges under reference voltage state (state three) in (N-X) grade, referring to attached drawing 3, charge benchmark Voltage be (U*N-U*t) V, solar battery array be Li-ion batteries piles charging final voltage be (U*N-U*t) V, whereinAbove situation can realize the charging controller to battery group by controller, so that storing Battery pack is restored to health status by sub-health state.

When t is greater thanWhen, since the output voltage of battery group is lower than the input service voltage of discharge module Lower limit AV, leading to whole system cannot be load normal power supply, therefore no longer switch charging termination reference voltage, provide announcement in advance Alert prompt, shows system cisco unity malfunction.

Another spacecraft lithium battery charging controller method is provided, is included the following steps:

(1) obtain lithium battery group serial number N, discharge module input voltage lower limit A, the upper voltage limit U of battery cell and Lower limit W;

(2) the total voltage v for measuring lithium battery group carries out constant-current charge and stops filling when v reaches N*U as v≤N*U Electricity;

(3) the total voltage v of lithium battery group and the voltage v of each battery cell are measured1…vi…vN, determine wherein full simultaneously The voltage value v of sufficient monomeri< W and | vi- v/ (N-t) | the fail battery amount of monomer t of > 40% × (U+W)/2 works as t=0 When, charging reference voltage is that N*U carries out constant-voltage charge;WhenCharging reference voltage is switched by N*U To (N-t) * U, constant-voltage charge is carried out, when the total voltage v of lithium battery group reaches (N-t) * U, stops charging;WhenWhen, export alarm signal.

When the failure of single battery develops into open-circuit fault by short trouble, which restores to use, to Raise whole reference voltage charging.It further include monitoring fail battery monomer when the reference voltage that charges switches to (N-t) * U by N*U Voltage vi, as fail battery monomer voltage viIt is restored to W≤viThe quantity of≤U be s when, 1≤s≤t, will 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, lithium battery is realized The matched well of working condition and end of charge voltage benchmark, avoid in conventional aircraft causes lithium electric using unity reference source Pond overcharge bring security risk.

The above, optimal specific embodiment only of the invention, but scope of protection of the present invention is not limited thereto, In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art, It should be covered by the protection scope of the present invention.

The content that description in the present invention is not described in detail belongs to the well-known technique of professional and technical personnel in the field.

Claims (4)

1. a kind of spacecraft lithium battery charging controller method, which comprises the steps of:
(1) lithium battery group includes N number of concatenated parallel-connected blocks battery cell, and discharge module carries out control of discharge to lithium battery group, obtains Take lithium battery group series connection series N, discharge module input voltage lower limit A, the upper voltage limit U and lower limit W of parallel-connected blocks battery cell;
(2) the total voltage v for measuring lithium battery group carries out constant-current charge as v < N*U, when v reaches N*U, stops charging;
(3) the voltage v of each parallel-connected blocks battery cell of lithium battery group is measured1…vi…vN, determine the voltage of parallel-connected blocks battery cell In be 0 quantity t;
(4) as t=0, charging reference voltage is that N*U carries out constant-voltage charge;When Charge benchmark electricity Pressure switches to (N-t) * U by N*U, carries out constant-current charge, when the total voltage v of lithium battery group reaches (N-t) * U, stops charging; WhenWhen, alarm signal is exported to flight control system.
2. spacecraft lithium battery charging controller method as described in claim 1, which is characterized in that in step (4) WhenWhen, alarm signal is exported to flight control system, and charging module is switched to and is directly negative Power supply is carried, is no longer lithium battery group charging.
3. a kind of spacecraft lithium battery charging controller method, which comprises the steps of:
(1) lithium battery group includes N number of concatenated parallel-connected blocks battery cell, and discharge module carries out control of discharge to lithium battery group, obtains Take lithium battery group series connection series N, discharge module input voltage lower limit A, the upper voltage limit U and lower limit W of parallel-connected blocks battery cell;
(2) the total voltage v for measuring lithium battery group carries out constant-current charge as v < N*U, when v reaches N*U, stops charging;
(3) the total voltage v of lithium battery group and the voltage v of each parallel-connected blocks battery cell are measured1…vi…vN, determine parallel-connected blocks electricity Meet the voltage value v of monomer in the voltage of pond monomer simultaneouslyi< W and | vi- v/ (N-t) | the failure electricity of > 40% × (U+W)/2 Pond amount of monomer t, as t=0, charging reference voltage is that N*U carries out constant-voltage charge;WhenIt fills Electrical reference voltage switches to (N-t) * U by N*U, carries out constant-current charge and stops when the total voltage v of lithium battery group reaches (N-t) * U Only charge;WhenWhen, export alarm signal.
4. spacecraft lithium battery charging controller method as claimed in claim 1 or 3, which is characterized in that work as charging It further include fault parallel-connected piece of battery cell voltage v of monitoring when reference voltage switches to (N-t) * U by N*Ui, when fail battery list Bulk voltage viIt is restored to W≤viWhen the quantity of≤U is s, charging reference voltage is switched to (N-t+ by (N-t) * U by 1≤s≤t s)*U。
CN201610844474.3A 2016-09-22 2016-09-22 A kind of spacecraft lithium battery charging controller method CN106410893B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201610844474.3A CN106410893B (en) 2016-09-22 2016-09-22 A kind of spacecraft lithium battery charging controller method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201610844474.3A CN106410893B (en) 2016-09-22 2016-09-22 A kind of spacecraft lithium battery charging controller method

Publications (2)

Publication Number Publication Date
CN106410893A CN106410893A (en) 2017-02-15
CN106410893B true CN106410893B (en) 2018-12-21

Family

ID=57997900

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201610844474.3A CN106410893B (en) 2016-09-22 2016-09-22 A kind of spacecraft lithium battery charging controller method

Country Status (1)

Country Link
CN (1) CN106410893B (en)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN200990506Y (en) * 2006-09-15 2007-12-12 李鹏 Circuit for realizing multi-section serial secondary pile protection with unit management
CN102148395A (en) * 2010-02-05 2011-08-10 日立车辆能源株式会社 Battery control device and battery system
CN102640382A (en) * 2010-03-24 2012-08-15 株式会社杰士汤浅国际 Secondary battery system

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3915151B2 (en) * 1996-11-26 2007-05-16 新神戸電機株式会社 Battery pack manufacturing method
US8193778B2 (en) * 2007-07-13 2012-06-05 Sanyo Electric Co., Ltd. Method of charging a battery array
US20090079390A1 (en) * 2007-09-26 2009-03-26 Kai-Wai Alexander Choi Rechargeable battery array
JP4591560B2 (en) * 2008-06-24 2010-12-01 ソニー株式会社 Battery pack and control method
JP5593849B2 (en) * 2009-06-12 2014-09-24 日産自動車株式会社 Battery monitoring device
JP5537992B2 (en) * 2010-02-24 2014-07-02 三洋電機株式会社 Secondary battery charging method, secondary battery charging control device, and battery pack
US9735592B2 (en) * 2012-02-29 2017-08-15 Nec Energy Devices, Ltd. Battery control system, battery pack, electronic device

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN200990506Y (en) * 2006-09-15 2007-12-12 李鹏 Circuit for realizing multi-section serial secondary pile protection with unit management
CN102148395A (en) * 2010-02-05 2011-08-10 日立车辆能源株式会社 Battery control device and battery system
CN102640382A (en) * 2010-03-24 2012-08-15 株式会社杰士汤浅国际 Secondary battery system

Also Published As

Publication number Publication date
CN106410893A (en) 2017-02-15

Similar Documents

Publication Publication Date Title
WO2002060030A1 (en) Power supply device
CN104052087B (en) Electric vehicle intelligent lithium ion battery management system and balance control method thereof
TW201103220A (en) Apparatus and method for managing plural secondary batteries
DE102005011081A1 (en) Accumulator and method for its operation
US10153651B2 (en) Systems and methods for series battery charging
CN104348234A (en) Battery management system with active equalization system
KR101483129B1 (en) Battery system, and energy storage system
CN102969749A (en) Cell balancing method, cell balancing device, and energy storage system including the cell balancing device
EP2629388A1 (en) Power management system
RU2324263C2 (en) Accumulator battery
WO2010091583A1 (en) Self-adjusting hybrid battery composed of lead acid batteries and lithium iron phosphate batteries
CN101651239B (en) Charging method of a plurality of groups of storage batteries and control system thereof
US20110181245A1 (en) Unitized charging and discharging battery management system and programmable battery management module thereof
CN101232110B (en) Method and apparatus for charging batteries
CN103560548A (en) Novel battery pack, battery pack connecting method and battery pack charge and discharge management method
US8952663B2 (en) Battery charge and discharge control apparatus and method for controlling battery charge and discharge
JP6329755B2 (en) Battery management device and energy storage system
CN102856612B (en) Mixed power source system
CN104079056B (en) The direct-current grid charge-discharge system of the multiple batteries being connected in series
WO2008137764A1 (en) Fine-controlled battery-charging system
CN105518924B (en) Battery apparatus and electric vehicle
Kim et al. A series-connected self-reconfigurable multicell battery capable of safe and effective charging/discharging and balancing operations
EP2085268B1 (en) Electronic system for battery
US9045047B2 (en) Storage battery
CN103855748B (en) The charging system and its charging method of a kind of vehicle

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant