TECHNICAL FIELD

The present disclosure relates generally to electro-optical devices and more particularly, to methods and systems for providing radiation tolerance for electro-optical devices used for spacecraft communication.

BACKGROUND OF THE ART

With the wide availability and use of satellites in so many fields, there is a growing need for more operational flexibility for satellite operators. As the technology and architecture of communication payloads of satellites moves towards digital payloads, digital optical interconnect devices like parallel electro-optical modules are vulnerable to issues such as signal integrity, degradation, and functional interruptions when exposed to radiation. Therefore, improvements are needed.

SUMMARY

In accordance with a broad aspect, there is provided an electro-optical device for intra-spacecraft communication in space, the electro-optical device having at least one of transmitting capabilities for converting a first electrical signal into a first optical signal and outputting the first optical signal within a spacecraft, and receiving capabilities for receiving a second optical signal within the spacecraft and converting the second optical signal into a second electrical signal, the electro-optical device having at least one integrated circuit dedicated to at least one of the transmitting capabilities and the receiving capabilities, the at least one integrated circuit configured for operating in an analog mode where configuration voltages for the integrated circuit are provided by analog voltage settings unaffected by radiation.

In accordance with another broad aspect, there is provided a method for operating an electro-optical device for intra-spacecraft communication. The method comprises configuring integrated circuits in the electro-optical device dedicated to at least one of transmitting and receiving capabilities with analog voltage settings unaffected by radiation; driving the electro-optical device from an electrical circuit; and operating the integrated circuits in analog mode while performing at least one of: converting a first electrical signal into a first optical signal and outputting the first optical signal within the spacecraft; and receiving a second optical signal within the spacecraft and converting the second optical signal into a second electrical signal.

Features described herein may be used in various combinations, in accordance with the embodiments described herein.

