Can a helicopter apply full cyclic and then full collective at the same time? Would'nt the blades on one side (opposite of the intended tilt direction) have already maxed their aoa, resulting in a net dissapearence of dissymmetry of lift, with the effect equal to just applying full collective? Or does full collective + cyclic result in even greater aoa (the inputs add up)?
Multiple questions here. Assuming by full cyclic you mean pushing the cyclic to a mechanical stop while pulling full collective to the mechanical stop, the answer is yes, at least for the Bell 206, a very common turbine helicopter in use worldwide. There are no restrictions with regards to full flight control inputs. At stabilized hover on a no wind day there is no appreciable dissymmetry of lift as aerodynamically, there is no advancing or retreating blade. If you push the cyclic straight and full forward, mechanically tilting the rotor disc, the instant you move forward you now have dissymmetry of lift between the advancing and retreating blades
Yes it is possible to apply both max collective and max cyclic, without stalling the rotor blades (which I understand is the basis of your question). By design, the collective provides about 8 to 10 degrees of blade pitch travel - it would stall at about 13º.