The two stall conditions are both under different circumstances than the low speed, static stall conditions from exceeding critical Angle of Attack (AoA), they are not one and the same however.
Dynamic stall is described in this article from the Ohia State University, in relation mainly to helicopter rotors:
Aerodynamic bodies subjected to pitching motions or oscillations exhibit a stalling behavior different from that observed when the flow over a wing at a fixed angle of attack separates.
Further reading in this article from the University of Adelaide. The stall behaviour is described as Dynamic Stall, and tied to a pitch rate of the profiles.
Accelerated stall is mainly referred to for aeroplanes subject to g-forces, such as described in this answer on this site.
So when yanking the yoke back during a high speed low pass, creating higher g-forces, Accelerated Stall seems to be the more appropriate term. The situation is of course dynamic as well...
The Ohio State article mentions dynamic stall occurring in a windmill, which is of course not an accelerated stall. So not all dynamic stalls are accelerated stalls.
Also, can a dynamic stall occur at less than the normal stall AoA if the pitch rate is very fast?
The Adelaide University article describes a pitch-up rate temporarily increasing $C_L$, then developing deep stall. The pictures show a leading edge vortex developing at 40° AoA (figures 3d and 3j), way higher than static stall angle. Pitch-up movement seems to delay the stall, until it occurs very dramatically without any warning.
And, last but not least, is an airplane taxiing on the ground considered stalled (the stall AoA is not reached, but the lift produced is insufficient to fly)?
No it is not considered stalled. Stall is a condition of separation of the boundary layer, which does not occur during taxiing.
