All our devices are tested following ECSS process and lot acceptance. Component pre-screening can be done for every batch of transceivers sold for this application..

• Small: less than 6 mm high (module and interposer)
• Rugged: withstand radiation doses >100 krad (Si) and qualified per MIL-STD 883 shock and vibration.
• Expected life: up to 20 years
• Performance: up to 28 Gbps/channel over a recommended operating temperature range of –40 ºC to 85 ºC
• Link budget: >7 dB with BER 10^–9 (measured at 25.7 Gbps).
• ​Low power consumption: 160 mW/channel (<6 pJ per bit)
• 4 TRX (4+4)-lane per module (100G, full duplex)
• 12 TX or 12 RX channel per module (300G half duplex)
• Multimode 850 nm wavelength laser
• Over 60 m reach on OM3 or OM4 ribbon fiber
• Standard MT parallel fiber connector
• RoHS
• Monitoring: LOS, RSSI, temperature, etc.
• Attaches to system board with 1,55 mm LGA interposer

Applications

• High-throughput communication satellites
• LEO satellite constellations
• GEO satellites
• Board-to-board and payload-to-payload connections
• High I/O density, high BW communication link

Open larger version of Image Caption

Test summary

• Proton testing: Total Non-Ionizing Dose (TNID)
• Heavy ion testing: Single Event Effect & Latch-up (SEE and SEL)
• Gamma Ray using Cobalt-60: Total Ionizing Dose (TID)
• Random vibration: NASA GEVS, GSFC-STD-7000A
• TVAC: Vacuum < 5E-5 hPa
• Outgassing: ECSS-Q-ST-70-02C

LightABLE qualifications

• Vibration tests per MIL-STD-883, Method 2007.3.
• Mechanical shock tests per MIL-STD-883, Method 2002.4.
• Thermal shock tests per MIL-STD-883, Method 1011.9.
• Damp heat tests per MIL-STD-202, Method 103B.
• Cold storage tests per MIL-STD-810, Method 502.5.
• Thermal cycling tests per MIL-STD-883, Method 1010.8.

References

Stephen Buchner, Paul Marshall, Scott Kniffin and Ken LaBel. “Proton testing guidelines”, NASA/Goddard Space Flight Center, 2002.
Doug Sinclair and Jonathan Dyer. “Radiation Effects and COTS Parts in SmallSats”, SSC, 2013.