I have to study an ADCS sensors suite and I am struggling to find a criteria to decide how many and in which directions the sun sensors shall be mounted, considering that they are coupled with star sensors for redundancy, initial acquisition and safe mode. I have read that Exomars Trace Gas Orbiter or TGO had 2 coarse sun sensors, while, for example, Mars Reconnaissance Orbiter or MRO had 8 sun presence sensors.

What justifies these different architectures?

  • $\begingroup$ Sun sensors and sun presence sensors may have slightly different applications and different characteristics. $\endgroup$
    – AJN
    Dec 26, 2021 at 10:43


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