The interaction, effect, and controllability of the performance parameters of the General Electric 20-ampere-hour, 24-cell nickel cadmium battery are investigated. The battery was cycled under simulated orbit conditions. The acquired data was analyzed and evaluated in terms of battery parameters and performance characteristics. Conclusions and tests results are presented along with recommendations for further study

Kirsch, W. W.

English

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https://ntrs.nasa.gov/search.jsp?R=19750017218 2020-03-22T22:07:42+00:00Z
INTERIM TEST REPORT
SENERAL ELECTRIC 20-AMPERE HOUR
NICKEL-CADMIUM BATTERY
by
W. W. Kirsch
N75-25290(NASA-C'-110748)	 i:ENE D AT. rLEcri• IC 20-AMPERE
NOUF NICKVL-CA1)"1I f1M bdTT: Y interim Test
Deport (Sperry Rand Corp-) 	 22 p HC 4)3.25
ZSCL 10C Unclas
G 3/44
	 17775
Prepared under Contract No. NAS8-21812
by
SPERRY RAND CORPORATION
For
Electrical Power Branch
Electrical Division
Astri.onics Laboratory
GEORGE C MARSHALL SPACE FLIGHT CENTER
4' or1 Z a-M/o
1
iI
CONTENTS
Paragraph Title Pte.
1. PURPOSE 1
2. CONCLUSIONS AN P, 'iiECOMMENDATIONS 1
3. PROCEDURE 2
3.1 Test plant
:1. 2 Test conditions 2
1. TEST RESULTS 3
-1.1 GE battery no. 1 3
4.2 GE battery no. 2 U)hase 1, cycle 0-1313) 4
4.3 GE battery no. 2 (phase 2, cycle 1313-230) 5
i. 4 C. — battery no. 2 U)hase 3, cycle 254-540) 6
-1.5 GE batt- p ry no. 2 (phase 4, cycle 540-620) 7
LIST OF ILLUSTHATIONS
Figure	 Title Page
I .	 Maximum cell voltage vs. temperature. ri
2.	 GE batteryno. 1, cycles 12 and 13
characteristics. 9
3.	 GE battery no. 2, phase 1 cycle
characteristics. 1t1
1.	 GE battery no. 2 capacity characteristics 11
5.	 GE battery no. 2 cell divergence:
characteristics. 12
^fo /y 1,A 44/0
n
LIST OF IT, I,ITS'I'R AT TONS 
(continued)
1' i__^*u re T itle Page
^;. GE battery no. 2, cycle :10, phase 1
(8-24-47,	 15:05). 13
. GE b:!ttery no. 2, cycle 134, phase 1
(8-31-67, 8:43, WA", overcharge). 14
8. GE battery no. 2 charge characteristics,
cycle 2.17 (9-12-67, 5b',/'r overcharge). 15
9. GE battery no. 2, cycle 62 0, phase 4
(10-16-67,	 12:00). 16
APPENDIX A NASA AND GE RECOMMENDED PROCEDURES A-1
!^ D /Y y 2' 'V/0
ii
(b) A second 100-cycle test should be performed starting with a
con,hletely discharged battery to which normal cycling is
applied.
(c) A series of tests should be }performed where any ind
voltage, during; the charge cycle, is allowed to ris4
,to y y 2 IV/ a
1.	 PURPOSE:
The purpose of this test was to observe, record, and become familiar
with the General Electric (GE) 20-ampere-hour, 24-cell nickel cadmium battery.
Of major concern was the interaction, effect, and controllability of the various
performance parameters.
2. CONCLUSIONS AND RECOMMENDATIONS
2.1 The following conclusions can 1 .lrawr. after 620 cycles of operation on
the GE battery.
(aI	 The battery capacity decreases after a high in`.tial charge, as a
function of cycles. This may pie the result of a memory effect,
or the battery achieving a sta, : of equilibrium. Whether the
battery is achieving a state ci equilibrium or not has not been
determined.
(b) The required overcharge caruiot be achieved becau.,. , of excessive
cell divergence. This also can cause a capacity loss.
(c) Parameter variations, such as temperature or load, have no
apparent effect on reversing the reduction in battery capacity.
'rhe overall performance of the battery to date has been marginal for
application with the Apollo telescope mount (ATM) power system. Voltage n•,atching
(it individual cells is required to permit recharge. The y causes of capacity loss
must Ix^ determined.
2.2 The purpose of the following test recommendations is to acquire further
data ()n capacity losses, equilibrium, and battery charge parameters. It is
recommended that testing be performed in the following areas:
(a)	 A 100-cycle test should be conducted starting with a fully
charged battery.
r	 ^
(d) Tests should also be completed to determine the relationship
between the maximum individual cell charge voltage, the
percentage of overcharge, and the steady state capacity of
the battery.
3. PROCEDURE
3. 1 Test plan. The basic test plan was to cycle the battery under simulated
orbit conditions. As dat •i was accumuiated, it was analyzed and evaluated in terms
of hatter, parameters and performance characteristics. An attemp! was then made,
during; subsequent tests, to acquire more specific information on particular
characteristics and parai, eters.
3.	 Test conditions. The battery was tested wider "worst case" ATM orbit
conditions as follows:
(a) Charge time	 58 minutes
(b) Discharge time	 36 minutes
(c) 'Temperature	 25 + 5 degrees Celsius (C)
All individual cell voltages and the total voltage were monitored with a
data sc:mner. The current, total voltage, and controlling; third electrode were
monitored by a strip chart recorder. An additional strip chart recd der was
used to r: cord two other third electrode signals. orbit simulation was provided
by a timing; unit composed of an oscillator and an electronic counter. A 700-watt
power supply simulated the solar source. The system load was simulated with a
liand contr(llect wire wowed rheostat. Constant power was supplied throughout the
charge/discharge cycle.
The battery was charged with a breadboarded ATM charger/regulator.
I)uring; charge, the maximum battery current was limited to 10 amperes until a
preset maximum voltage level was achieved. At this point, charging current
was limited to prevent exceeding maximum battery voltage. Charge cutoff
occurred when any one of three third electrode signals exceeded their preset
levels.
The 24 cells were mounted in the restrainer provided by GE. Heat sinks,
also supplied, were positioned as a spacer between individual cells and extended
lwyond the bottom of the battery to decrease temperature gradients among the cells.
Temperature was maintained within + 1 degree C -,%-ith a thermal chamber.
40H;,2 V10
2
All standard battery capacity tests were performed with the battery
toad maintained at a constant 8 amperes. The discharge was terminated when
the voltage of any cell decreased below 1 volt.
4.	 TEST RESULTS
4.1 GE hattery nh. 1.
I. 1. 1 P rocedure. The GE battery no. 1 was received in a discharged
condition having been previously conditioned in accordance with the National
Aeronautics and Space Administration (NASA) recommended procedure in
Appendix A. The recommended GE conditioning cycle, as noted in Appendix
A, was immediately applied to the battery. At the completion of this cycle,
the total open circuit battery voltage was 31.32 volts with the maximum individual
cell voltage divergence at 8 millivolts (mV). Following the above conditioning,
the b:ittery was placed on automatic orbit cycling using the previously noted
orbit conditions. Control parameters for this portion of the test were deter-
mined by GE as follows:
(a) Temperature was maintained between 25 -1 5 degrees C.
(b) A1.L11111U111 battery voltage was not to exceed a particular vah
as noted in figure 1, corresponding to a given battery
temperature.
(c) The third electrode load resistor value was to be between 1
and 3 ohms.
(d) No third electrode cutoff information was given. It was, 1,	 , r,
maintained at 125 mV during this test.
A typical charge/discharge cycle is shown in figure 2. As shown, no
third electrode cutoff occurred during the charge cycle. With no cutoff, the
charge was 150 pc1• cent of the capacity taken out during discharge. An additional
undCsirahle factor was the individual cell divergence, or voltage spread, at the
end of charge. This divergence exceeded 39 mV. The NASA conditioning procedure
was :ipjilicd to the- hattery as a result of the 39-mV divergence compared to the
post conditioning; divergence of 8 mV. A 2.3 mV maximum divergence was noted
on the final conditioning charge.
The battery was placed on simulated orbit cycling following the special
conditioning. After two days, the divergence had increased to 45 mV. A final
discharge of this battery resulted in a measured capacity of 27 ampere hours.
1. 1.2 Summary. The performance information obtained from the preceding
test is as follows:
(a) The battery was cycled according to ATM conditions :30 times
during: this test.
(b) No third electrode cutoff occurred (luring normal cycling.
(c) Exces:.ive cell divergence occurred at the end of a charge
eye le.
Subsequent information received from GE indicated a 7-ohm third
electrode resistor was preferred instead of the 1-ohm unit that had previously
been used. In addition, the third electrode cutoff criteria was established to be
the signal level necessary to permit 20 percent overcharge of *he battery.
Since the excessive cell divergence of GE battery no. 1 was not
necessarily typical of GE cells, it was decided to use a second 24 cell GE >)attery
(GE battery no. 2) specimen (luring subsequent tests.
4.2 GE batterryno. 2 (phase 1, cycle 0-138).
X1.2. 1 Procedure. The second GE battery was received in a discharged
state, having previously been preconditioned using the recommended NASA pro-
cedure in :appendix A. After reconditioning the battery using the GE procedure,
the unit was placed un the 94-minute simulated orbit cycle. However, a change
was incorporated in this test. The third electrode resistor was increased from
I to 7 oh.nis, and the third electrode cutoff was set to permit 20 percent over-
charge. The 1xittery was continuously cycled 138 times following the conditioning
cycle.
4.2.2 Summai2^. The performance characteristics are shown in figures
3, 4, 5. G, ,end ". Figure 4 indicates the less in capacity after 138 cycles of
operation. Figure 5 illustrates the increase in cell divergence from 8 to 38 mV.
Two tnnical charge/discharge cycles are shown in figure 3.
Detailed charge characteristics for cycles 30 and 1:34 are illustrated
in figures G and 7.
4	 .f^^y x /V/D
The evaluation of the phase 1 test resulted in the following con-
elusions:
(a) individual :ell voltage spread (divergence) increases to a
maximum value as a function of cycle time.
(b) Capacity decreases over the cycle life.
(c) Third electrode performance is consis t znt. However, there
are questions concerning nonlinear ",amps" in the signal
(figure 3).
(d) The percent of overcharge is self limited to 10 percent
because of excessive cell divergence.
4.3 GE battery no.^2 hose 2, cycle 138-230).
-1. 3. 1 Procedu re. Since the low value cf overcharge may have caused tilt,
loss in capacity during; phase 1, the third electrode cutoff was increased from
130 to 140 mV. Normal simulated orbit cycling was then continued for 90
cycles. At cycle 230, figure 4, the battery capacity was again measured and
found to ham decreased to 14. 6 ampere hours.
4.3.2 Summary. Evaluation of the battery performance resulted in three
possible causes for battery capacity loss.
(a) The battery was not charged completely.
(b) The battery was not discharged completely.
(c) Effective battery capacity had been reduced.
-1.3.3 Capacity test (cycle 230-25- 1). The questions of improper charge
were tested by continued simulated orbit cycling for 12 cycles. During the
12th cycle, however, third electrode cutoff control was removed. The measured
overcharge during; this cycle was 59 percent and is shown in figure 8. The
capacity test immediately following the 58 percent overcharge. indicated 16
ampere hours of capacity.
5
Asa result of the last two tests, it was concluded that the effective
battery capacity had Ix,-en reduced. Another attempt was made to compl :rely
charge the cell. On the initial charge, 23.5 arr ere hours were placed in the
cell. Hine cycles of simulated orbit conditions followed with no third electrode
control. The overcharge during each charge was 20 percent. Assuming 100
percent battery efficiency, approximately :30 ampere hours of charge were
added to the battery. The subsequent discharge resulted in a 22 ampere hour
battery capacity.
Two basic problems emerge as a result of the phase 2 test. One is
the individu;11 cell divergence at the end of each charge cycle. 'The other is
the loss in battery capacity as a function of cycling,
1.4 GE battery no. 2(phas e :3, cycle 254-5.10).
4.4. 1 Procedure. The 'oss in battery capacity could have been caused by a
memory effect. If this vrc the case, any change in operating parameters,
such as temperature or load, should reverse this apparent memory. Basal un
the foregoing„ the batter , was cycled under simulated orbit conditions for one
week. At cycle 350, after an apparent memory effect had taken place, normal
c-cling was continued. The temperature, however, was varied from 20 to 30
.egrees every 24 hours.
1. 1. 2 Summary. A capacity test at 20 degrees C was performed at cycle
WO rafter one week of temperature cycling. The results indicated a decrease
I rtim J S. 5 to 16 ;unpere hours. Immediately thereafter, the battery was again
h:^r„cal and -	 ed for D; hours at 30 degrees C. The subsequent discharge
resulted in an additional loss in capacity to 14.5 ampere hours.
From cycle -41 7 5 to 540, cycling; was continued with the battery load being
varied Irom ct to 2 amperes every 12 hours. At cycle 5 .10 the battery capacity
^^ : ► ^ I I ampere hours.
The test re ,- nits (luring phase 3 can be Libulated as follows:
(a)	 Battsry capacity decreases as a function of cycling.
(I))
	
Capacity appears to decrease as the tenl1wrature increases
(figure 1).
(c)	 (_:cll divergence it maximum charge is not affected by
tcnIl)VVcitu.1V (figure 5).
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(d)	 The third electrode signal varies approximately ti mV
[w.r degree C.
(c)	 Excessive cell divergence Knits the battery overcharge
capability.
1.5 GE battery no. 2 hase •1, cycle 5 ,10-620	 Phase 4 was begun by
discharging individual cells with 1-ohm resistors for 72 hours. The subse-
quent charge was at a 2-ampere rate for 20 hours in accordance with GE
recommendations. Normal cycling followed the high overcharge. The battery
Was C\'Cled for one week prior to a capacity test. The results of the capacity
test are shown in figure 4. Cell divergence is noted in figures 5 and 9.
7	
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120 —
110
100
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Figure 2 GE battery no. 1, cycles 12 and 13 characteristics
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Figure 3 GE battery no. 2, phase 1 cy,:{a characteristics
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APPENDIX A
NASA AND GE RECOMMENDED PROCEDURES
IWO
^K^,^^G PAGE 8^8 Vol
f
10. INTRODUCTION
'rho following two procedures are conditioning cycles w}+ich tiro
to be performed on GE 20-ampere-hour, 24-cell nickel cadmium	 1
batteries after they have been inactive, or in storage for more than 20 days.
1 0. 1 Conditioning cycle ree, 	 Ior.ded by NASA.
p^(a) Place battery in an appropriate restrainer.
(b) Charge the battery at 2 amperes for 13 hours.
(c) Discharge the battery at 2 amperes until the voltage
on any cell decreases to 1 volt.
(d) Charge the battery at 5 amperes for 5 hours.
(e) Discharge the battery at 5 amperes until the voltage
on any cell decreases to 1 volt.
(i)	 Charge the battery at 10 amperes for 2.25 hours.
(g)	 Discharge the battery at 10 amperes until the voltage
on any one cell decreases to 1 volt.
Conditioning is complete.
10.2 Conditioning; cycle recommended by GE.
(a) Place the battery in :in appropriate restrainer.
(b) Charge the battery at 0.5 ampere for 50 hours.
(c) Discharge the battery at 4 amperes until the volutge on any
one cell decreases below 1 volt.
(d) Charge the battery at 1 ampere for 25 hours.
Conditioning cycle is complete.
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General Electric 20-ampere hour nickel-cadmium battery

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