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A multirotor needs meaningful thrust margin to control itself, so maximum all-up weight is total static thrust divided by the target thrust-to-weight ratio — 2:1 is the usual design point. Payload is whatever remains after the airframe and battery.
Multirotor payload
AUW = total thrust / target thrust-to-weight; payload = AUW - airframe and battery mass
It puts hover near 50% throttle, leaving headroom to arrest a descent, fight a gust and yaw without saturating a motor.
It is optimistic. Thrust falls as the aircraft moves and in thin or hot air, so derate the figure for high-altitude or hot operations.