SPARK BATTERY PASSIVATOR
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Radiation TID immune disconnection
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Manufactured to IPC3
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Design and testing based on ECSS
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Single-failure tolerant design
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Battery disconnection and loading
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High current, high efficiency design
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Best-in-class on size and mass metric
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Availability off the shelf
SPARK BATTERY PASSIVATOR
Disconnect and deplete your spacecraft batteries simply and reliably
The Spark battery passivation unit combines a fail-safe bidirectional battery disconnection switch and an electrical load in a single unit.
Designed as a seamless plug-and-play subsystem, it serves the critical function of disconnecting and depleting the batteries at end-of-life, both required as part of the spacecraft passivation.
The unit requires a dual ARM then FIRE command preventing its accidental activation. It uses an innovative switching and loading technology which allows extremely low line power losses while rendering it both single failure tolerant and immune to the effect of total ionizing radiation dose.
USE CASE EXAMPLE
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Unregulated spacecraft bus where solar panels supply the battery through a PCDU
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Passivator seamlessly integrate between the battery and the PCDU
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Discrete ARM and FIRE lines controlled from the on-board computer
Performance
Current rating
ON resistance
Quiescent power
Dissipative power
50 A
< 2 mΩ
< 10 mW @ 28 V
> 5 W
Interface
Electrical interface
Voltage range
Control interface
Mechanical interface
Size
Mass
4-pin Datamate Power
6-pin CMM (MIL-DTL-55302F)
22 V - 34 VDC
0 V - 5 V (discrete ARM then FIRE)
4 x M3 fasteners
48 mm x 48 mm x 12 mm
< 45 g
Environmental
Temperature range
Radiation
Random vibration
Shock
-30 °C to +60 °C operational
-40 °C to +70 °C non-operational
TID > 30 krad, TID immune for maintenance
14.1 grms
SRS 1000 g (ECSS-E-ST-10-03C)
Customizations
Electrical interfaces
Dissipative power
Control interfaces
Analysis
Flying leads, custom connector
0 W - 5 W
0 V - 3 V (discrete)
PSA, WCA, FIT, Structural