CN107015151A - A kind of magnetic valve priming system battery parameter optimization method based on rocket flight state - Google Patents
A kind of magnetic valve priming system battery parameter optimization method based on rocket flight state Download PDFInfo
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- CN107015151A CN107015151A CN201710127256.2A CN201710127256A CN107015151A CN 107015151 A CN107015151 A CN 107015151A CN 201710127256 A CN201710127256 A CN 201710127256A CN 107015151 A CN107015151 A CN 107015151A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/36—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
- G01R31/385—Arrangements for measuring battery or accumulator variables
- G01R31/387—Determining ampere-hour charge capacity or SoC
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Abstract
The present invention relates to a kind of magnetic valve priming system battery parameter optimization method based on rocket flight state, comprise the following steps：Calculate the maximum capacity and minimum capacity of battery needed for flight course；Determine electric current needed for each flight time section magnetic valve and priming system；The electric current as needed for magnetic valve and priming system, battery capacity and load resistance make battery sample, and discharge test is carried out to battery sample；The minimum voltage V tested in each flight time section output voltage of battery sampleminWith maximum voltage Vmax；Calculate battery and export to the voltage of load end the electricity function index for whether meeting load；If meeting the electricity function index of load, battery index parameter is exported.Present invention optimizes battery parameter, on the premise of power demands are met, it can accomplish that weight is minimum, improve the carrying capacity of rocket.
Description
Technical field
The present invention relates to a kind of magnetic valve priming system battery parameter optimization method based on rocket flight state, belong to battery
Design field.
Background technology
Current carrier rocket power supply uses silver-colored zinc liquid cell as power supply for engine electromagnetic valve on arrow and firer
Product power supply, battery design is designed generally directed to battery capacity and cell output voltage.At present, in battery capacity design
Use maximum capacity design method, i.e. consider that whole magnetic valves fully open required electric current in flight course is added and ignite fire
Electric current needed for work product carries out estimation design.Cell voltage design aspect relies primarily on estimation constant value current value and combines instantaneous big electricity
Stream impact carries out discharge test and obtains cell output voltage.The above method quickly can enter to required battery capacity and output voltage
Row estimation, shortens and develops and test period, but have the disadvantage that calculating error is larger, especially magnetic valve in flight course according to flying
Row sequential is not to fully open, and causes battery capacity excessive, simultaneously because excessive to cell voltage output performance calculating error
Cause the design of system cable net excessively huge, ultimately result in carrying capacity decline.
New generation's carrier rocket is more harsh to product weight requirement to ensure its carrying capacity, therefore needs in design
Careful design, strict control battery weight and cell output voltage are carried out to battery parameter, it is ensured that carrying capacity is not reduced.Such as
Where ensure to make battery weight minimum while power supply capacity, be this area technical problem urgently to be resolved hurrily
The content of the invention
It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of magnetic valve fire based on rocket flight state
Work product battery parameter optimization method, the situation of change loaded in the case of the live flying with reference to rocket is realized to battery parameter
Accurate estimation.
The object of the invention is achieved by following technical solution：
A kind of magnetic valve priming system battery parameter optimization method based on rocket flight state is provided, comprised the following steps：
(1) according to needed for the running parameter of flight time sequence and magnetic valve, priming system calculates flight course battery maximum
Capacity and minimum capacity；
(2) according to flight time sequence, electric current needed for each flight time section magnetic valve and priming system is determined；
(3) electric current needed for the magnetic valve and priming system that are determined according to step (2), battery capacity and bear that step (1) is determined
Carry resistance and make battery sample, discharge test is carried out to battery sample；
(4) the minimum voltage V in each flight time section output voltage of test battery sampleminWith maximum voltage Vmax；
(5) according to minimum voltage VminWith maximum voltage VmaxAnd rocket cable net resistance, calculate battery and export to load end
Voltage whether meet the electricity function index of load；
(6) if the brownout of load end, changes cable system, its resistance is reduced, if cable system can not be changed,
Increase the quantity of series-connected cell monomer, it is ensured that load terminal voltage meets the electricity function index of load, recalculates battery most
Small voltage VminWith maximum voltage Vmax, return to step (5)；If the overtension of load end, changes cable system, increase its resistance
Value, if cable system can not be changed, reduces the quantity of series-connected cell monomer, it is ensured that load terminal voltage meets the electrical resistance of load
Energy index, recalculates the minimum voltage V of batteryminWith maximum voltage Vmax, return to step (5)；If meeting the electric of load
Performance indications, then maintain the parameter of battery, into step (6)；
(6) battery index parameter, including battery capacity and final battery minimum voltage and maximum voltage are exported.
It is preferred that, the battery according to needed for flight time sequence and magnetic valve, the running parameter of priming system calculate flight course
The specific method of maximum capacity and minimum capacity is：
(1.1) count the quantity n1 of whole rocket magnetic valve according to flight time sequence, n1 electromagnetic valve work time be T1,
T2……Tn1；Count priming system quantity n2；
(1.2) it is I to obtain n1 magnetic valve minimum working currentdmin1、Idmin2…Idmini…Idminn1, maximum operating currenbt
Respectively Idmax1、Idmax2…Idmaxi…Idmaxn1；Priming system operating time t is obtained, n2 roads priming system minimum working current is obtained
For Ihmin1、Ihmin2…Ihmini…Ihminn2, maximum operating currenbt is respectively Ihmax1、Ihmax2…Ihmaxi…Ihmaxn2；
(1.3) battery maximum capacity C needed for full flight course is calculatedmaxWith minimum capacity Cmin：
It is preferred that, the determination method of each flight time section is to have magnetic valve or the change of priming system generating state in step (2)
Then delimit as a new period.
It is preferred that, calculating battery, which is exported to the method for the voltage of load end, in step (5) is：Calculate Vmin-Imax* R and
Vmax-Imin* R, wherein Imin、ImaxFor minimum of all periods, maximum operating currenbt, Vmin-Imax* R and Vmax-Imin* R ensures full
The electricity function index of foot load, then it represents that battery parameter meets load request, Vmin-Imax* R refers to less than the electric property of load
Lower limit is marked, shows the brownout of load end, Vmax-Imin* R shows load end higher than the electricity function index upper limit of load
Overtension.
It is preferred that, Imin、ImaxAcquisition methods be：Imin=MIN (Idmin1、Idmin2…Idmini…Idminn1, Idmax1、
Idmax2…Idmaxi…Idmaxn1、Ihmin1、Ihmin2…Ihmini…Ihminn2、Ihmax1、Ihmax2…Ihmaxi…Ihmaxn2)
Imax=MAX (Idmin1、Idmin2…Idmini…Idminn1, Idmax1、Idmax2…Idmaxi…Idmaxn1、Ihmin1、Ihmin2…
Ihmini…Ihminn2、Ihmax1、Ihmax2…Ihmaxi…Ihmaxn2)。
The present invention has the following advantages that compared with prior art：
(1) present invention is applied on certain model rocket, and this method is by first sample, sample stage, dynamical system examination
The repeatedly large-scale experiment examination such as car experiment, flight test, can accurately be estimated battery capacity.
(2) present invention optimizes battery parameter, on the premise of power demands are met, it can accomplish that weight is minimum, improve
The carrying capacity of rocket.
(3) present invention carries out discharge test by design sample, accurately obtains output voltage parameter, further ensures and is
The correctness of system design input.
(4) present invention make full use of cable system can flexible design the characteristics of, by preferentially change cable system design method
The repeated work of battery design is reduced, design cost has been saved.
Brief description of the drawings
Fig. 1 is battery parameter Optimizing Flow figure of the present invention；
Fig. 2 is rocket flight time diagram.
Embodiment
1st, battery capacity needed for flight course is calculated according to flight time sequence and magnetic valve, the running parameter of priming system.
Assuming that whole rocket has n1 magnetic valve D1, D2 ... Dn1, each electromagnetic valve work time is T1, T2 ... Tn1
Second, each magnetic valve minimum working current is Idmin1、Idmin2……Idminn1Ampere, maximum operating currenbt is respectively Idmax1、
Idmax2……Idmaxn1Ampere；Whole rocket has n2 roads priming system sequential H1, H2 ... Hn2, according to priming system running parameter, per road
Priming system only works 0.1s, is I per road priming system minimum working currenthmin1、Ihmin2……Ihminn2Ampere, maximum operating currenbt
Respectively Ihmax1、Ihmax2……Ihmaxn2Ampere, then (ampere is small for battery maximum capacity and minimum capacity needed for full flight course
When) calculated respectively by formula 1, formula 2.
Because load characteristic has bound operating mode, to ensure that battery capacity is used enough in flight course, selects during design
Battery capacity is estimated with formula 1.
2nd, full inflight phase cell output current curve is counted
According to Fig. 2 flight time sequences, maximum, minimum electricity when counting each magnetic valve and priming system action according to the form of table 1
Flow curve, is used as the input condition of the electric discharge of battery.
The battery discharge current statistical form of table 1
3rd, the current curve and load resistance according to the battery of table 1 make battery sample, carry out discharge test, obtain battery defeated
Go out voltage, referring to table 2.
The cell discharge voltage statistical form of table 2
4th, choose minimum voltage among table 2 and maximum voltage is used as the cell output voltage model in whole rocket flight course
Enclose.
Vmax=MAX (V0max,V1max,V2max,V3max,V0min,V1min,V2min,V3min)
Vmin=MIN (V0max,V1max,V2max,V3max,V0min,V1min,V2min,V3min)
5th, according to minimum voltage VminWith maximum voltage VmaxAnd rocket cable net resistance R, calculate battery and export to load end
Voltage whether meet the electricity function index of load；Computational methods are Vmin-Imax* R and Vmax-Imin* R, wherein Imin、ImaxFor
All periods minimums, maximum operating currenbt, Vmin-Imax* R and Vmax-Imin* R ensures to meet the electricity function index of load, then
Represent that battery parameter meets load request, then maintain the parameter of battery, battery is produced by this parameter.
If the brownout of load end, i.e. Vmin-Imax* R is too low, now needs to change cable system, reduces its resistance, if
Cable system can not be changed, then increases the quantity of series-connected cell monomer, to improve cell output voltage, it is ensured that load terminal voltage is met
The electricity function index of load, recalculates the minimum voltage and maximum voltage of the battery after increase series-connected cell monomer, with electricity
Tankage is together as new battery performance index；
If the overtension of load end, i.e. Vmax-Imin* R is too high, now needs to change cable system, increases its resistance, if
Cable system can not be changed, then the quantity of series-connected cell monomer is reduced, to reduce cell output voltage, it is ensured that load terminal voltage is met
The electricity function index of load, recalculates the minimum voltage and maximum voltage of battery, with battery capacity together as new electricity
Pond performance indications.
It is described above, it is only the optimal embodiment of the present invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can be readily occurred in,
It should all 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 (5)
1. a kind of magnetic valve priming system battery parameter optimization method based on rocket flight state, it is characterised in that including as follows
Step：
(1) according to needed for the running parameter of flight time sequence and magnetic valve, priming system calculates flight course battery maximum capacity
And minimum capacity；
(2) according to flight time sequence, electric current needed for each flight time section magnetic valve and priming system is determined；
(3) electric current needed for the magnetic valve and priming system that are determined according to step (2), battery capacity and load resistance that step (1) is determined
Value makes battery sample, and discharge test is carried out to battery sample；
(4) the minimum voltage V in each flight time section output voltage of test battery sampleminWith maximum voltage Vmax；
(5) according to minimum voltage VminWith maximum voltage VmaxAnd rocket cable net resistance, calculate battery and export to the electricity of load end
Whether pressure meets the electricity function index of load；
(6) if the brownout of load end, changes cable system, its resistance is reduced, if cable system can not be changed, is increased
The quantity of series-connected cell monomer, it is ensured that load terminal voltage meets the electricity function index of load, recalculates the minimum electricity of battery
Press VminWith maximum voltage Vmax, return to step (5)；If the overtension of load end, changes cable system, increase its resistance,
If cable system can not be changed, the quantity of series-connected cell monomer is reduced, it is ensured that load terminal voltage meets the electric property of load
Index, recalculates the minimum voltage V of batteryminWith maximum voltage Vmax, return to step (5)；If meeting the electrical resistance of load
Energy index, then maintain the parameter of battery, into step (6)；
(6) battery index parameter, including battery capacity and final battery minimum voltage and maximum voltage are exported.
2. the magnetic valve priming system battery parameter optimization method as claimed in claim 1 based on rocket flight state, its feature
Be, according to needed for the running parameter of flight time sequence and magnetic valve, priming system calculates flight course the maximum capacity of battery and
The specific method of minimum capacity is：
(1.1) the quantity n1 of whole rocket magnetic valve is counted according to flight time sequence, n1 electromagnetic valve work time is T1, T2 ...
Tn1；Count priming system quantity n2；
(1.2) it is I to obtain n1 magnetic valve minimum working currentdmin1、Idmin2…Idmini…Idminn1, maximum operating currenbt difference
For Idmax1、Idmax2…Idmaxi…Idmaxn1；Priming system operating time t is obtained, obtaining n2 roads priming system minimum working current is
Ihmin1、Ihmin2…Ihmini…Ihminn2, maximum operating currenbt is respectively Ihmax1、Ihmax2…Ihmaxi…Ihmaxn2；
(1.3) battery maximum capacity C needed for full flight course is calculatedmaxWith minimum capacity Cmin：
3. the magnetic valve priming system battery parameter optimization method as claimed in claim 1 based on rocket flight state, its feature
It is, the determination method of each flight time section is to have magnetic valve or the change of priming system generating state then to delimit as one in step (2)
The individual new period.
4. the magnetic valve priming system battery parameter optimization method as claimed in claim 2 based on rocket flight state, its feature
It is, calculating battery, which is exported to the method for the voltage of load end, in step (5) is：Calculate Vmin-Imax* R and Vmax-Imin* R, its
Middle Imin、ImaxFor minimum of all periods, maximum operating currenbt, Vmin-Imax* R and Vmax-Imin* R ensures to meet the electric of load
Performance indications, then it represents that battery parameter meets load request, Vmin-Imax* R shows less than the electricity function index lower limit of load
The brownout of load end, Vmax-Imin* R shows the overtension of load end higher than the electricity function index upper limit of load.
5. the magnetic valve priming system battery parameter optimization method as claimed in claim 4 based on rocket flight state, its feature
It is, Imin、ImaxAcquisition methods be：Imin=MIN (Idmin1、Idmin2…Idmini…Idminn1, Idmax1、Idmax2…Idmaxi…
Idmaxn1、Ihmin1、Ihmin2…Ihmini…Ihminn2、Ihmax1、Ihmax2…Ihmaxi…Ihmaxn2)
Imax=MAX (Idmin1、Idmin2…Idmini…Idminn1, Idmax1、Idmax2…Idmaxi…Idmaxn1、Ihmin1、Ihmin2…
Ihmini…Ihminn2、Ihmax1、Ihmax2…Ihmaxi…Ihmaxn2)。
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| CN201710127256.2A CN107015151B (en) | 2017-03-06 | 2017-03-06 | A kind of solenoid valve priming system battery parameter optimization method based on rocket flight state |
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| CN105785270A (en) * | 2014-12-24 | 2016-07-20 | 国家电网公司 | Measurement method for measuring energy state operation interval of battery string |
| CN106324511A (en) * | 2016-08-11 | 2017-01-11 | 深圳市科比特航空科技有限公司 | Hydrogen-fuel unmanned aerial vehicle and estimation method for endurance time of unmanned aerial vehicle |
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2017
- 2017-03-06 CN CN201710127256.2A patent/CN107015151B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100121587A1 (en) * | 2006-11-30 | 2010-05-13 | The Boeing Company | Health Management of Rechargeable Batteries |
| CN103185863A (en) * | 2011-12-31 | 2013-07-03 | 伊顿制造（格拉斯哥）有限合伙莫尔日分支机构 | Estimation method and system of battery electricity preparation time under condition of varying loading |
| EP3008771A1 (en) * | 2013-06-14 | 2016-04-20 | HRL Laboratories, LLC | Methods and apparatus for sensing the internal temperature of an electrochemical device |
| CN103869255A (en) * | 2014-03-18 | 2014-06-18 | 南京航空航天大学 | Micro-miniature electric unmanned aerial vehicle endurance time estimation method |
| CN105785270A (en) * | 2014-12-24 | 2016-07-20 | 国家电网公司 | Measurement method for measuring energy state operation interval of battery string |
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