Student pilot here - has been thinking about this question for the past 2 days and found this forum, very helpful! I will try to describe my understanding below, correction welcomed!

Vs = stall speed (weight dependent)
n = design load factor limit (weight dependent)

Making up some variables for ease of substitution:

A = critical AoA
W = aircraft weight (variable)
L = design wing loading limit (weight independent, the actual aircraft would have margins over it). L = W * n
S = speed at which L is reached at A. S = Vs * sqrt(n)

So:

Va = design maneuvering speed, greater than or equal to S, which is used to design the control surfaces to withstand the load at full deflection at the speed.
Vo = operating maneuvering speed, Vo <= S. Under Vo, aircraft will stall before reaching L or any other structural limit