In the attached photos, you see the F-22 in a moderate AOA (see vortices & deflected AB exhaust) rolling turn. The horizontal stabilizers are deflected for a left roll, while the aileron are deflected for a right roll. Is this aileron positioning to generate a proverse yawing moment? There is no visible rudder deflection.
We often see both ailerons deflected up and the flaperons deflected down during a symmetrical pull, which increases the aerodynamic twist to reduce the bending load at the tip of the wing. But I have never noticed this opposing roll deflection of the ailerons and horizontal stabs.