MeddleMoe - I realise I didn't answer your question:
As a blade moves round the rotor disc, the pitch change rods follow the swash plate, changing the pitch of the blades and thus their Angle of Attack (AoA). As the AoA changes, so does the amount of lift the blade produces causing it to flap upwards or downwards.
If the uncorrected swash plate is titled forwards, the forward half of the swash plate is creating a reduced pitch command and the rear half is producing an increased pitch demand with neutral pitch at the 3 and 9 o'clock positions.
So, as the blade passes the 3 o'clock (US rotation) it sees reducing pitch and AoA and begins to flap down - at the 12 o'clock position it sees minimum pitch and minimum AoA and is at its maximum rate of flapping down.
From 12 o'clock to 9 o'clock, the pitch down demand is reducing (as the pitch change rod starts to climb uphill again) but the pitch and AoA are still less than at the 3 and 9 so the blade continues to flap down but at a reducing rate until it gets to its lowest point at 9 o'clock.
This is why the corrected swash plate is tilted at 90 degrees so that forward cyclic equals nose low blade and therefore forward movement of the helicopter.
There are different combinations of jack positioning and pitch change rod placement on different helicopters but they all achieve the same end result.
The blades flapping is a result of aerodynamic forces induced by the change in pitch and AoA.
Is that coherent enough?
Congratulations, you have hereby explained how the gyroscopic effect works on a rotor blade.
What is next? There is no such thing as friction, it is just collisions between micro-structures and van der vaals forces dissipating energy.
There is no such thing as the bernoulli effect but air molecules accelerating from high pressure to low pressure following a gradient in collision probability.