ADCS / Design phase
Attitude Determination & Control
Detumbles the satellite after deployment and holds coarse nadir pointing so the payload sees the ground.
What it does
The v1 baseline is magnetorquer-assisted coarse nadir pointing. Hysteresis rods damp the tumble after deployment; a magnetometer, MEMS gyro and per-face sun sensors determine attitude; and B-dot plus PD control drive wound X/Y/Z coils through a driver board.
Payload interface
ADCS raises a “within pointing cone” flag that the payload uses to decide when to capture, which fits the mission’s opportunistic-sampling concept.
Status
Draft, not yet scoped. Reaction wheels, a star tracker and GPS are deferred to v2 or later.