I just got off an Erj 145 and noticed that the flaps and spoliers seem to have a much smaller extension that the heavies, and also seem to be smaller laterally than the heavies. Is my perception correct that the control surfaces are proportionally larger on the heavies tham smaller jets?
Spoilers are the surfaces on the top of the wing. On the heavies they are broken up into many individual panels, though on small aircraft they might be as little as a single panel. So, that gives both complexity, and redundancy. Spoilers may be used for roll control, as speed brakes and as ground spoilers. In all cases, the amount of extension and the actual panels that move will vary according to need. The speed brake function also allows for direct pilot control of the amount of deflection.
On most aircraft, the ailerons are the outer panels of the wing only. They may additionally have a droop function which has the effect of partially incorporating them into the flaps. The 747 has an additional small aileron panel at about half span. At higher speeds the outer ailerons are inhibited and only the inners used, to reduce wing bending loads.
The effectiveness of the ailerons will be a function of speed, deflection and moment arm. So, I expect that for a shorter wing span, an aileron would need to be proportionally larger to be able to generate the same rolling moment. Looking at a plan view of the 145 (
https://upload.wikimedia.org/wikipedia/commons/6/61/Bmi_erj145_planform_arp.jpg) the trailing edge of the wing is quite standard in that all of it is used for flaps and ailerons.
Here's a link to all you could ever want to know about the 145s control system.
Plane Embraer EMBRAER-135-145
The larger aircraft have the space, complexity, and power systems to allow for much more complex flap systems. From a quick look at the ERJ's system, it looks as if the flaps are simple hinged panels, which extend to about 45º. In contrast the bigger aircraft will have area increasing flap systems, in which the panels extend aft in the initial stages of their motion to increase the total wing area, before bending down in the later stages. In the end it all comes down to a balance between need, cost, and complexity.
The wing itself will attempt to counter any roll inputs. The down-going wing has a slightly greater angle of attack, which will make more lift. The up going has the opposite effect. Roll rates in airliners probably top out at about 15-20º per second. Aircraft like the Mirage and A4 had sustained rates of 720º per second.