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2011 NASA Aerospace Battery Workshop15-17 November 2011
ORS Phase 3 (TacSat-4)30Ah Li-ion Battery
(A Tale of a Battery’s Adventure from Storage to Flight)
Susie N. LaCavaU.S. Naval Research Laboratory
Thanks to support from:Bob Skalitzky, NRL; J. Christopher Garner, USG;Zoila Forgione, TASC; Paul Beach, Vince Visco,
& Hiroshi Nakahara, Quallion
2011 NASA Aerospace Battery Workshop15-17 November 2011 2
ORS/ISET* Activities
How will it get to Orbit?
What Orbit is it going into?
What Payloads does itneed to support?
How will it be operated?
Make it “Responsive”
Make it “Low Cost”
Generate a Set of Spacecraft Bus Standards, in Sufficient Detail to Allow a Vehicle Manufacturer to Design, Build, Integrate, Test, and Deliver a Low Cost Spacecraft Bus Satisfying an Enveloping Set of Mission Requirements (Launch Vehicle, Target Orbit, Payload, etc.) in Support of a Tactical Operational Responsive Space Mission
Charter
• Government and Industry Team Defined Capabilities• Documents created to capture capabilities include
– Payload Developers Guide (For payload developer independent of Bus Fab)– General Bus Specification (performance capabilities of the Bus)– Software Interface Standards (Ground – Bus and Bus – Payload)
* Operationally Responsive Space/Integrated System Engineering Team
2011 NASA Aerospace Battery Workshop15-17 November 2011 3
Document Descriptions
Payload Developers Guide- Mechanical, Electrical, Thermal Interface Definition
General Bus Specification- Performance Characteristics,- Launch Vehicle Interfaces, etc.
Software Interface Standards - Space to Ground- Bus to Payload
2011 NASA Aerospace Battery Workshop15-17 November 2011 4
ISET Standards (Performance)
Parameter ORS Bus Standard*Total Wet Mass 425 kg
Payload Mass 175 kg
Bus Wet Mass 250 kg
Payload Power (Orbital Average) 200 W (700 W Peak)
Pointing Control (3-sigma) 0.05 deg
Pointing Knowledge (3-sigma) 0.01 deg
Slew Rate (deg/sec) Up to 2
Orbit Position Knowledge 30 m (1-sigma)
Payload Data Storage Payload Specific/ 1 Gbyte for Payload Health & Status
Payload Data Transfer Capability [Telemetry D/L]
500kbps to 2Mbps for HEO orbits/ 2Mbps for LEO
Payload Digital Command & Data Interface
RS-422/ HDLC andSpacewire
Switched 28V Power Lines For Payload
3 -> 2 (Critical & Nominal)
Payload Interface Temperature -30°C to +55°C on the Bus, Isolated from the P/L
Bus Propulsion Capability (DeltaV) 300 -> 175 m/s min.
Other Derived Power Rqmts.- 350 Watt-hours in Eclipse for P/L- System Powered off at Launch- Battery Stored Separate from Bus- Battery Installation < ~ 1 day- No charging of Battery once integrated
with the Launch Vehicle
* Services supplied to a Payload
2011 NASA Aerospace Battery Workshop15-17 November 2011 5
Programmatics• ONR Payload, Flt Ops, Test Bed Sponsor• OFT Bus Sponsor – “Phase 3” Bus Prototype• AFSPC, SMC-12 Provided Launch (M-IV Star 48)• NRL Program Manager• STRATCOM to Assign COCOM Priorities for Use and
Exercises• Multi-Service Participation
Spacecraft and Payload Highlights
TacSat-4 Mission Summary
Ground Equipment• BFT Devices: MTX, Grenadier Brat, Others• COTM: Legacy Radios and Compatible UHF
Wideband Radios• Data-X Buoys and Gnd Sensors >1 Watts• Ground Terminal: One Per 2000 nm Theater• Spacecraft Cmd and Cntrl: Blossom Point, MD
– Additional Coverage From AFSCN– Payload Tasking on SIPRNET-based Virtual
Missions Operations Center (VMOC)
• Satellite [Space Vehicle]: – 444 kg (Incl. Prop and Contingency)– Payload Power: 200-700W– Low HEO (4 hr) Orbit– 1 Year Life
• Payload Capability: – Data-X (>1W) and Blue
Force Tracking (BFT)– Comms-on-the-Move (COTM)
- Legacy Radio and IP Netted Support- MUOS-Like Wideband Capability
Objectives• Demo High Dwell ORS Capability via a HEO Orbit
– Augment Poor/No Coverage Areas• Evaluate and Mature Phase 3, System Level Bus
Standards in Realistic Design, I&T, Launch, and Flight Operations Environment
• Provide TACSAT/ORS Comms-on-the-Move Capability (Legacy, Netted, and MUOS-Like)
• Collect BFT Devices in Underserved Areas• Perform Buoy/Sensor Data-X on Moderate-to-High
Power Transmissions
2011 NASA Aerospace Battery Workshop15-17 November 2011 6
Spacecraft Block Diagram
Latch Valve Torque Rods
Star Tracker
GPS
Thrusters
Htrs w/Thermostats
TempSensors
PressureSensor
Diplexer
Critical Loads
FwdOmni
AftOmni Mag
422 Cmd/Tlm/Sync
Transponder
Command and Data Electronics
Power Supply Card
Std. Spacecraft Processor
Processor and AttitudeInterface
Attitude and PropulsionInterface Card
Payload Data Handler
Crit Cmd
Power Switching
Cmd & Tlm Interface
Power Sys Elect.
Star TrkrElect.
IMU/IRU
SunSensors
Non-Critical Loads
SADE
Command, Telemetryand Control Card
EPSPlug
LV Sep.
Test
Cou
pler
Switc
h
Battery Charge Control
I&T Test
Payload
UHF Dual Feed
X Band TX Horn
X Band RX Horn
Survival Htr PwrSwitched Payload Pwr
Deployments
Discrete Cmd/TlmI/F
Battery
422 Cmd/Tlm
422 Cmd/Tlm
422 Cmd/Tlm
1 Mbit D/L
Level Cmds
API Bus
AnalogSA Deployment
SolarArraySADA
SolarArray
SADA
SA Deployment
Non-Critical PowerCritical PowerDigital I/F
AnalogRF
Propulsion Power
Battery Interface
LV Sep.
Low Rate D/L
IMU PwrSply
ODTML/UIE Spacewire
TachometerRWA
TachometerRWA
TachometerRWA
RW Elect.
Non-Critical Propulsion Power
2011 NASA Aerospace Battery Workshop15-17 November 2011 7
EPS Block Diagram
Solar ArraySystem
SADA SADA
PowerSystem
ElectronicsBox
(PSEB)
Battery
SPG
Payload
Bus Loads
NRLNRL/IndustryIndustry
Solar ArraySystem
IMUCU
DIRECTENERGY
TRANSFERTOPOLOGY
LAUNCHEDWITH BATTERY OFF BUS
2011 NASA Aerospace Battery Workshop15-17 November 2011 8
30Ah Li-ion Battery Required Bus Installation
Battery Radiator Plate
Last Panel Installed Into BusRemovable at Any Time
Battery MaintenanceDone External to Vehicle(Charge/Discharge/Test)
Using Three ExternalConnectors
Battery Mechanically InstalledFully Charged and Then
Connected to Vehicle HarnessVehicle HarnessEgress Port
2011 NASA Aerospace Battery Workshop15-17 November 2011 9
Battery/Cell Acquisition Approach
• NRL Surveyed the Li-ion Industry for Low Cost Battery Cells• NRL Introduced to Quallion through Joe Stockel
– Quallion Builds State-of-the-Art Li-ion Battery Cells for DoD, NRO, and NASA– Provided Cells at Low Cost in Exchange for Knowledge and Data
• Cooperative Agreement Contract Awarded to Quallion October 2006– Coop-Agreement Instead of CRDA (Cooperative Research & Development
Agreement), Because $$ Provided to Quallion for Cells• Quallion Built, Tested, and Delivered 40 Cells to NRL On or Before 15 August
2007 (in Batches so NRL Can Begin Battery Build)• NRL to Provide Quallion With Design “Know-How” for the Build and Qualification
of Battery Assembly Including Drawings, Procedures, Test Plans, etc.• Quallion Observed Construction and Testing, and Will Receive On-Orbit Data• Cell Selected: QL015KA (15Ah)• Battery Topology Selected: 8S2P
2011 NASA Aerospace Battery Workshop15-17 November 2011 10
QL015KA 15Ah Li-ion Cell Detail
• Manufacturer: Quallion• Chemistry: LiNiCoAlO• Nameplate Capacity: 15 Amp-Hours*• Part Number: QL015KA• Voltage Range: 0.0 - 4.1 Vdc• Cell Mass: 460 grams• Cell Cover Material: SS• Cell Case Material: SS• Cell Dimensions: 3.5” x 2.0” x 2.5”• Energy Density: 121 Whr/kg* When Charged to 4.1 Vdc and Discharged to 2.7 Vdc
• Cell Level Tests Performed by Quallion– DC Internal Resistance Test Pre-
and Post-Testing– C/5 Cycling at 0, 25, and 40°C:
Cycle Between 3.0 and 4.1 Vdc(With Taper Charge) Three Times; Evaluate Capacity
– Self Discharge Test; When Cells Are Fully Charged, Let Stand for 72 Hours, Then Evaluate the Drop in Cell Potential
– C/5 Cycling at 0, 25, and 40°C After Storage at 50% SOC over 90 Days; Evaluate Capacity; Calculate Capacity Loss If Any
– X-Ray Photographs and Leak Test
2011 NASA Aerospace Battery Workshop15-17 November 2011 11
Quallion QL015KA 15Ah Li-ion CellElectrical Performance Data (Life Data)
TOTAL STANDARD CAPACITY MEASUREMENT AND DC RESISTANCE
8
9
10
11
12
13
14
15
16
0 2000 4000 6000 8000 10000 12000 14000 16000 18000
Cycle Number
Cap
acity
(Ah)
0
0.01
0.02
0.03
0.04
0.05
0.06
0.07
0.08
DC
Res
ista
nce
(ohm
s)
60% DOD LEO CyclingQuallion 15 AhTest Temperature 23 °C
Total Standard Capacity
DC Resistance
2011 NASA Aerospace Battery Workshop15-17 November 2011 12
Quallion QL015KA 15Ah Li-ion Cell Electrical Performance Data
QUALLION QL015KA 15 AH LITHIUM-ION CELL CHARACTERIZATIONAT C RATE OF DISCHARGE
2.500
2.700
2.900
3.100
3.300
3.500
3.700
3.900
4.100
4.300
0.00 10.00 20.00 30.00 40.00 50.00 60.00TIME (minutes)
Cel
l Vol
tage
(Vdc
)
-16.000
-14.000
-12.000
-10.000
-8.000
-6.000
-4.000
-2.000
0.000
Cur
rent
(Adc
)
Cell VoltageDischarge Current
--> greater than 60% DODVcell(DOD=60%) = 3.385 Vdceclipse load: about 25 Amps
last update: 25 November 2006
2011 NASA Aerospace Battery Workshop15-17 November 2011 13
30Ah Li-ion Battery Electrical Block Diagram
• Wiring Per SB-EP-0010• Box ID: A015• Cell-to-Cell Interconnects Using Custom
Flexible Bus Bars Manufactured by Storm Copper
– 2 Sizes Required: Parallel, Series Connections
– Copper Braid in between seamless copper bars that are nickel-flashed and gold-plated
• 4 Temperature Sensors – 2 AD590 sensors for Telemetry– 2 LTN11 sensors for Ground Test
• 3 Circular Connectors: D38999 Series IV– J1 Power: 4 +, 4 Rtn lines – J2 Telemetry (Voltages, Temps)– J3 Ground Charge – Cell Balance
2011 NASA Aerospace Battery Workshop15-17 November 2011 14
30Ah Li-ion Battery Packaging
Virtual30Ah Cell
Tie Rods forCompression
(Mechanical & Thermal)
Cover, ConnectorsNot Shown
ThermalWalls
SupportStructure
CellInterconnects
2011 NASA Aerospace Battery Workshop15-17 November 2011 15
30Ah Li-ion Battery Thermal Analysis - Heat Dissipation
STANDARD BUS 30 AMPERE-HOUR LITHIUM-ION BATTERY HEAT GENERATION DURING DISCHARGE AT 25 AMPS
0
20
40
60
80
100
120
0 500 1000 1500 2000 2500 3000
TIME (Seconds)
HEA
T G
ENER
ATI
ON
(Wat
ts)
Pinakin, Vtn Methods Averaged
-->greater than 60% DOD
last update: 25 November 2006
2011 NASA Aerospace Battery Workshop15-17 November 2011 16
30Ah Li-ion Battery Thermal Analysis
Baseline Deviations:
• 2610 Second Transient Calculation (43.5 Minutes), 10 Second Time Step
• Transient Power Dissipation Curve (Pinakin, Vtn Methods Averaged) Supplied by 8244
• Power Group on 11/30/2006
• No Shims
• Walls 1 and 5 are 0.075 in. Thick
• Walls 2 and 4 are 0.225 in. Thick
• Wall 3 is 0.300 in. Thick• Maximum Cell Temperature Delta (End of Transient) = 4.36 °C• Cell Thermal Profiles Are Matched Well From Cell to Cell• Less Than 3 °C Temperature Delta Within Planes Parallel to the Baseplate From Virtual Cell to Virtual Cell, and Within a Cell
2011 NASA Aerospace Battery Workshop15-17 November 2011 17
Photos of Battery
Battery Mass:29.6 lbs.
Battery Size:10-31/32” x 8-26/32” x 7-1/16”
2011 NASA Aerospace Battery Workshop15-17 November 2011 18
Battery Tests/Charging Operations
• Battery was Tested per NCST-TPL-SB008• Tests were Performed between 21 March 2008 and 04 May 2008
– Safe-to-mate– Insulation Resistance (Pre- and Post- Random Vibe)– Capacity Tests
3 Cycles @ 10°C, 20°C, and 30°C 2 Cycles @ 10°C post-Random Vibe & TVAC
– Orbital Cycling (2 days → 12 cycles)– Random Vibration– TVAC (1 day → 6 cycles @ 10°C, 20°C, 30°C, and then 20°C again)– ALL Tests PASSED
• System Level Tests Supported by Battery– Vibration– EMI– Magnetic Dipole Moment
• Charge Control– All Charging Done by Battery Charging/Test System– Charging Can Be Done in Parallel with Bus Testing if Battery is Installed
• Battery Placed in Storage in Battery Lab Separate from Bus at Room Temperature from May 2008 to April 2009
2011 NASA Aerospace Battery Workshop15-17 November 2011 19
Battery Test/Charge Control Approach
Cell Cell
Cell Cell
Cell Cell
Cell Cell
Cell Cell
Cell Cell
Cell Cell
Cell Cell
GRND
TEST
J3
RedundantBattery
CellBypass*
TELEMETRY
J2
T
T
POWER J1
POWER J1
BatteryChargeRackandComputerMonitor*
I-Mon
*Modified U/S
Controls Charge End PointProtects Against Over-Charge
2011 NASA Aerospace Battery Workshop15-17 November 2011 20
Capacity Test @ 10°C
SBEP0050 SN002 CHARACTERIZATION DURING CAPACITY TEST AT 10 DEG C 20080411 CYCLE 3
2.000
2.200
2.400
2.600
2.800
3.000
3.200
3.400
3.600
3.800
4.000
4.200
4.400
0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800 850 900
Time Elapsed (Minutes)
Volta
ge (V
dc)
-8.000
-6.000
-4.000
-2.000
0.000
2.000
4.000
6.000
8.000
Cur
rent
(Adc
)
Cell 8 V
Cell 7 V
Cell 6 V
Cell 5 V
Cell 4 V
Cell 3 V
Cell 2 V
Cell 1 V
Current
2011 NASA Aerospace Battery Workshop15-17 November 2011 21
Capacity Test @ 20°C
SBEP0050 SN002 CHARACTERIZATION DURING CAPACITY TEST AT 20 DEG C 20080416 CYCLE 3
2.000
2.200
2.400
2.600
2.800
3.000
3.200
3.400
3.600
3.800
4.000
4.200
4.400
0 50 100 150 200 250 300 350 400 450 500 550 600 650 700
Time Elapsed (Minutes)
Volta
ge (V
dc)
-8.000
-6.000
-4.000
-2.000
0.000
2.000
4.000
6.000
8.000
Cur
rent
(Adc
)
Cell 8 V
Cell 7 V
Cell 6 V
Cell 5 V
Cell 4 V
Cell 3 V
Cell 2 V
Cell 1 V
Current
2011 NASA Aerospace Battery Workshop15-17 November 2011 22
Capacity Test @ 30°C
SBEP0050 SN002 CHARACTERIZATION DURING CAPACITY TEST AT 30 DEG C 20080418 CYCLE 2
2.000
2.200
2.400
2.600
2.800
3.000
3.200
3.400
3.600
3.800
4.000
4.200
4.400
700 750 800 850 900 950 1000 1050 1100 1150 1200 1250 1300 1350 1400 1450 1500
Time Elapsed (Minutes)
Volta
ge (V
dc)
-8.000
-6.000
-4.000
-2.000
0.000
2.000
4.000
6.000
8.000
Cur
rent
(Adc
)
Cell 8 V
Cell 7 V
Cell 6 V
Cell 5 V
Cell 4 V
Cell 3 V
Cell 2 V
Cell 1 V
Current
2011 NASA Aerospace Battery Workshop15-17 November 2011 23
Battery Install Photos20 July 2010 & 06 August 2010
2011 NASA Aerospace Battery Workshop15-17 November 2011 24
Battery Tests/Charging OperationsStorage #1
• May 2008 to April 2009 (~10 months) – Battery in storage in Battery Lab at Room Temperature separate from Bus
• 01-05 May 2009 – Battery tested per NCST-TPL-SB008
– Capacity Test (3 Cycles at Room Temperature (25 ± 5°C))
• 06 May 2009 – Battery installed in Bus!
– Capacity Test (1 Cycle at Room Temperature (25 ± 5°C))
• Observation Noted
– Hardly any loss over the 10 months in storage in cells: ~0.002 Vdc max
• 04 August 2009 – Launch delayed…
– Battery physically de-mated and removed from Bus and put back in storage at Room Temperature in Battery Lab
2011 NASA Aerospace Battery Workshop15-17 November 2011 25
Battery Tests/Charging OperationsStorage #2
• August 2009 to July 2010 (~11 months) – Battery in Storage in Battery Lab at Room Temperature separate from Bus
• 18-22 March 2010 – Battery tested per NCST-TPL-SB008
– Capacity Test (3 Cycles at Room Temperature (25 ± 5°C))
– No capacity loss observed during 7.5 months in storage
• 20 July 2010 – Battery installed in Bus!
• 17-19 August 2010 – Battery tested per NCST-TPL-SB008
– Capacity Test (3 Cycles at Room Temperature (25 ± 5°C))
– No capacity loss observed since last capacity test in March (5 months)
• 31 August 2010 – Launch delayed again…
– Decision made to keep Battery installed in Bus; electrically de-mated
– Entire Bus placed in Storage
2011 NASA Aerospace Battery Workshop15-17 November 2011 26
August 2009 – July 2011 StorageCell VoltagesSBEP0050 SN002 CharacterizationStorage - August 2009 to July 2011
Monthly Checks
3.3000
3.3500
3.4000
3.4500
3.5000
3.5500
3.6000
3.6500
3.7000
17-A
ug-2
009
11-S
ep-2
009
06-O
ct-2
009
31-O
ct-2
009
25-N
ov-2
009
20-D
ec-2
009
14-J
an-2
010
08-F
eb-2
010
05-M
ar-2
010
30-M
ar-2
010
24-A
pr-2
010
19-M
ay-2
010
13-J
un-2
010
08-J
ul-2
010
02-A
ug-2
010
27-A
ug-2
010
21-S
ep-2
010
16-O
ct-2
010
10-N
ov-2
010
05-D
ec-2
010
30-D
ec-2
010
24-J
an-2
011
18-F
eb-2
011
15-M
ar-2
011
09-A
pr-2
011
04-M
ay-2
011
29-M
ay-2
011
23-J
un-2
011
18-J
ul-2
011
Date (Actual)
Cel
l Vol
tage
(V)
Cell 1 (V)
Cell 2 (V)
Cell 3 (V)
Cell 4 (V)
Cell 5 (V)
Cell 6 (V)
Cell 7 (V)
Cell 8 (V)
2011 NASA Aerospace Battery Workshop15-17 November 2011 27
Battery Tests/Charging OperationsStorage #3
• August 2010 to February 2011 (~5 months) –Battery in Storage installed in Bus
• 08 February 2011 – Bus pulled out of Storage!
– Battery Pack and Cell Voltages Measured
No change since placed in storage
• 01 March 2011 – Bus, Payload, and I&T Crew left NRL for Kodiak, AK!!!
• 02 March 2011 – Arrived at Kodiak, AK!!!
• Launch Date: 05 May 2011
2011 NASA Aerospace Battery Workshop15-17 November 2011 28
Battery Tests/Charging OperationsStorage #2
• 28-30 March 2011 – Battery tested per NCST-TPL-SB008. Too cold for Kodiak bears to be out and about…
– Capacity Test (3 Cycles at Room Temperature (25 ± 5°C))
– No capacity loss observed
• Final Charge on Battery Scheduled for 15 April 2011!
• 07 April 2011 – Launch was placed on-hold due to issues related to the Taurus fairing failure and Minotaur manifest ordering
– SV placed in storage in current position in the KLC PPF…
• 31 May 2011 – Received word that Minotaur LV approved to return to flight. TacSat-4 to launch 3rd in line after ORS-1 and HTV-2B. Yay!
• 21-23 June 2011 – Battery tested per NCST-TPL-SB008. Saw one Kodiak bear on way to KLC.
– Capacity Test (3 Cycles at Room Temperature (25 ± 5°C))
– No capacity loss observed
– Observed an “issue” with GSE with third cycle on charge
Resolved on 13 July 2011 - GSE verified to be operational
2011 NASA Aerospace Battery Workshop15-17 November 2011 29
Battery Capacity ComparisonSB-EP-0050 SN002 Battery Capacity Comparison
May 2009 through June 2011Voltage vs. Capacity
20.0000
22.0000
24.0000
26.0000
28.0000
30.0000
32.0000
34.0000
0.000 5.000 10.000 15.000 20.000 25.000 30.000 35.000
Capacity (Ah)
Pack
Vol
tage
(V)
Battery Capacity 2010-03 (March)
Battery Capacity 2009-05 (May)
Battery Capacity 2010-09 (August)
Battery Capacity 2010-12 (December)
Battery Capacity 2011-03 (March)
Battery Capacity 2011-06 (June)
31.024 Ah
30.510 Ah
May 2009: Discharge took 308 Minutes at 6A. (Baseline)
30.882 Ah
August 2010: Discharge was 2 Minutes Shorter.March 2010: Discharge was 6 Minutes Shorter.
December 2010: Discharge was 3 Minutes Shorter.
30.727 Ah
30.641 Ah
March 2011: Discharge was 5 Minutes Shorter. 30.686 AhJune 2011: Discharge was 4 Minutes Shorter.
2011 NASA Aerospace Battery Workshop15-17 November 2011 30
Current Status
• Final Battery Charge Performed 07 September 2011
• Launch Date: 27 September 2011
Battery
2011 NASA Aerospace Battery Workshop15-17 November 2011 31
SV Photos
2011 NASA Aerospace Battery Workshop15-17 November 2011 32
Launch Photos
2011 NASA Aerospace Battery Workshop15-17 November 2011 33
Day in the LifeThermal/Power/Attitude
• Satellite Goes Through Six, 4 Hour Orbits Per Day• Apogee Operations:
– Payload Will Pass Over Primary Theater at Apogee Three Consecutive Passes
– Next Three Passes Spacecraft Will Not Pass Over Primary Theater – Payload Will Operate for Up to 2 Hours During Each Pass Over
Primary Theater – Payload Will Operate During Non-Primary Theater Passes to Service
Additional Theaters– Mission ConOp Includes Servicing Multiple Theaters in a Given Day,
Within Spacecraft Limits– Typical Payload Operations Per Pass Over Primary Theater
10 Legacy Comms Channels for 1 Hour, 24 Minutes Or 6 Legacy Comms Channels for 2 Hours Or Blue Force Tracking and Wideband Comms for 2 Hours Or Data-X for 2 Hours
– Payload Will be Targeted to a Specific Point in Theater During Payload Operations Nominally Targeted at Ground Terminal
• Non-Apogee Operations:– When Payload Is Off, Spacecraft Will Be Aligned -Z to the Sun
Was Selected As Best Attitude for Bus Thermal Subsys Allows Solar Panels Uninterrupted Access to Sun
• BP Contacts As Available - 3-4 per Day
2011 NASA Aerospace Battery Workshop15-17 November 2011 34
Orbit Track
2011 NASA Aerospace Battery Workshop15-17 November 2011 35
Post-Launch Battery Performance Data
TacSat-4 30Ah Li-ion Flight Battery Performance SB-EP-0001 S/N002
Battery Voltage and Current
30.000
30.500
31.000
31.500
32.000
32.500
33.000
33.500
9/27/11 16:48:00 9/27/11 17:02:24 9/27/11 17:16:48 9/27/11 17:31:12 9/27/11 17:45:36 9/27/11 18:00:00 9/27/11 18:14:24 9/27/11 18:28:48 9/27/11 18:43:12
Date & Time (Zulu)
Volta
ge (V
)
-15.000
-10.000
-5.000
0.000
5.000
10.000
15.000
20.000
Curr
ent (
A)
BATT VMON BATT IMON
2011 NASA Aerospace Battery Workshop15-17 November 2011 36
Post-Launch Cell Performance Data
TacSat-4 30Ah Li-ion Flight Battery PerformanceSB-EP-0001 S/N002
Cell Voltages
3.800
3.850
3.900
3.950
4.000
4.050
4.100
4.150
9/27/11 16:48:00 9/27/11 17:02:24 9/27/11 17:16:48 9/27/11 17:31:12 9/27/11 17:45:36 9/27/11 18:00:00 9/27/11 18:14:24 9/27/11 18:28:48 9/27/11 18:43:12
Date & Time (Zulu)
Volta
ge (V
)
VC 1
VC 2
VC 3
VC 4
VC 5
VC 6
VC 7
VC 8
2011 NASA Aerospace Battery Workshop15-17 November 2011 37
Post-Launch Battery Performance Data
TacSat-4 30Ah Li-ion Flight Battery PerformanceSB-EP-0001 SN002
Battery Voltage & Current
32.000
32.100
32.200
32.300
32.400
32.500
32.600
32.700
32.800
32.900
33.000
10/7/11 23:16:48 10/8/11 4:04:48 10/8/11 8:52:48 10/8/11 13:40:48 10/8/11 18:28:48 10/8/11 23:16:48
Date & Time (Zulu)
Volta
ge (V
dc)
-0.100
0.000
0.100
0.200
0.300
0.400
0.500
Curr
ent (
A)
BATTERY_VMON BATTERY_IMON
2011 NASA Aerospace Battery Workshop15-17 November 2011 38
Post-Launch Cell Performance Data
TacSat-4 30Ah Li-ion Flight Battery PerformanceSB-EP-0001 SN002
Cell Voltages
4.000
4.010
4.020
4.030
4.040
4.050
4.060
4.070
4.080
4.090
4.100
10/7/11 23:16:48 10/8/11 4:04:48 10/8/11 8:52:48 10/8/11 13:40:48 10/8/11 18:28:48 10/8/11 23:16:48
Date & Time (Zulu)
Volta
ge (V
dc)
VC1 VC2 VC3 VC4 VC5 VC6 VC7 VC8
2011 NASA Aerospace Battery Workshop15-17 November 2011 39
Eclipse Projection