Contents include the following: (1) mission requirements; (2) battery design features; (3) battery operational overview; (4) battery performance; and (5) summary and conclusions

Dawson, S.

Ewell, R.

Otzinger, Burton

Perrone, Dave

Shirbacheh, M.

Surampudi, S.

Valdez, T.

English

NASA Technical Reports Server

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MARS PATHFINDER BATTERY
PERFORMANCE
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B. OTZINGER, D. PERRONE, S. DAWSON, T. VALDEZ
S. SURAMPUDI , R. EWELL, M. SHIRBACHEH,
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NASA BATTERY WORKSHOP
HUNTSVILLE, ALABAMA
NOVEMBER 18-20, 1997
ELECTROCHEMICAL TECHNOLOGIES GROUP
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https://ntrs.nasa.gov/search.jsp?R=19990017678 2020-06-18T00:45:23+00:00Z
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OUTLINE
° MISSION REQUIREMENTS
° BATTERY DESIGN FEATURES
" BATTERY OPERATIONAL OVERVIEW
• BATTERY PERFORMANCE
- PRELAUNCH
- CRUISE
- EDL
- MARS OPERATIONS
° SUMMARY AND CONCLUSIONS
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MISSION REQUIREMENTS
• PRE LAUNCH 4 MONTH ACTIVE INVERTED STORAGE
• LAUNCH INVERTED BATTERY LAUNCH
C,
1",3
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• CRUISE
• EDL
7 MONTH ACTIVE STORAGE
40 AH, 1080 WH
• MARS OPR. CYCLES 30 CYCLES(1CYCLE/DAY, 8
HOUR CHARGE 16 HOUR
DISCHARGE) 50% DOD
• WEIGHT 15 KG
• DIMENSIONS 9.8" x 7.4" x 7.4"
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• VOLTAGE 27 V
• CAPACITY 40 Ah
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• RATE CAPABILITY 1-5 A
PULSE CAPABILITY 40 A FOR 40 MSEC
• CYCLE LIFE 40
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• WET LIFE 14 MONTHS
• WEIGHT 15 KG
• DIMENSIONS 9.8" x 7.4" x 7.4"
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KEY CELL DESIGN FEATURES
• Robust separator system - 5 layers of cellophane and 2 layers of polymer membrane.
To achmevelong calendar and cycle hfe
_ • Triple redundant case-to-cover seal including basic ultrasonic seal.
To prevent electrolyte leakage
To improve safety
• Large cell plate area - approximately 200 square inches.
Low temperature operatmon"
For enhanced pyro-firing
• Unique leak-free cell vent valves.
For inverted battery operation
allow gas venting under off-limit operation
• Minimal free electrolyte
For inverted battery operation
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KEY BATTERY DESIGN
FEATURES
& PROCESS
• Titanium fabricated battery case with sealable cover and gasket.
Light weight construction
gas and electrolyte containment
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• Battery vent valve and pressurization port.
Redundant valve to protect cells from electrolyte loss
• Battery heater and two temperature sensors.
Thermal management for charge control
• Over-pot of cells,, surface conformal coating, connector back side potting
electrolyte absorptmn system.
Prevent ionic conductive paths
Improve safety
and
•Cell Matching and selection
Extend cycle life
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"I KEY BATTERY OPERATING STRATEGIES
• Battery was mounted inverted and maintained at 12 C during pre-launch andlaunch Phases
•Battery was partially dischar ed to o
,, . _ g _ 80 YoSOC and on open circuit stand, at -5 to
u aegrees C, during 7 Month cruise period.
• Battery was charged at end of cruise through 1.2 Ohm resistor to 0.2 A cut-offand 1.95 V I cell Ave.
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• Battery was heated to 15 to 20 degrees C prior to all charges.
• Battery was charged during Mars operations without resistor to a selective
shunt limiter controlled maximum volta,-,- o: .... ,- ....
......... . . _. o,x vu_tage settings were available
w=tn 1.95 v / cell Ave.., the nom,nal full charge selection.
• Battery was taper charged !o a constant shunt limiter voltage, 1.95 V /
Ave.. well below the 2 V. I,m,t e'----' .... .,. ..... cell
full charge result. ,,,_,,uy=u i, constant current charging with same
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BATTERY CAPACITY VS CHARGE VOLTAGE
55
MARS PATHFINDER - 16 8ST Ag-Zn CELLS WITH 2+5 SEPARATOR SYSTEM
CONSTANT VOLTAGE CHARGE CHARACTERISTIC FOR NEW CELLS WITH 4.5 AMPERE INRUSH AT
25 _" C
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VOLTAGE
1.95 1.96
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, MARS Pathfinder Power System Configuration Relays
GSE/Cruise Solar Array
Deadface
Main B_Relay
Z_ Qk u,oae _ Battery
I _, _ypass \ Charge
I ffelay l_ Relay
Bus Return
Battery
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Battery
Isolation
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SUMMARY AND CONCLUSIONS
• The first use of a silver-zinc battery in a spacecraft application that
called for extensive rechargeable operation after 12 months of active
stand hasproven to be very successful.
BST has developed a silver-zinc battery with unique design features
for the Mars Pathfinder mission.
• JPL has developed battery management strategies to meet the Mars
Pathfinder mission requirements.
- Partial SOC at low temperature and open circuit stand was found to be
the most effective method for insuring extensive cycle life following a
long period of active storage
- Silver-zinc battery charging at a reduced constant voltage was shown
to provide full charge and a capability of supporting a large number of
cycles.
- Launch of an inverted silver-zinc battery was shown to be possible
when a leak free cell vent valve is employed.
- The use of a silver-zinc battery and shunt limiter in a direct energy
transfer power system resulted in a very energy efficient design
approach.
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ACKNOWLEDGMENT
The work described here was carried out at the Jet Propulsion Laboratory,
California Institute of Technology, under contract with the
National Aeronautics and Space Administration.
ELECTROCHEMICAL TECHNOLOGIES GROUP


Mars Pathfinder Battery Performance

Mars Pathfinder Battery Performance

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