Not, exactly. What happens with the Redeye is that in the instant when the paired set of control surfaces (one set of planar surfaces that can deflect), need to change orientation (Imagine the procession of the target the plane of wings though image 2, 3 & 4 of the series of five rotational states in Figure 9; or basic trig “Sin(ref and signal phase)” being of opposed magnitude ), due to the target falling behind the plane of the control surface they are suddenly commanded to change their defection to the opposite limit but until that occurs they are deflected to some degree and so generate lift in that direction for that half of the rotation for some period of time as rotates around its axis.
Due to the fact that as a rolling airframe it has to pick some rate, and either Clockwise or Counterclockwise rotation (and it does vary over the flight), the time it spent with surfaces deflected out of the desired plane of maneuver, either against or with the direction of rotation causes the net change to be towards the direction of the point of intercept, but due to having non-limited inertia and no method for fin AoA feedback it doesn’t take the shortest path, but a curvilinear one.
(in a sense its like one of those very basic line following robots with two wheels that students program where if it sees a Low return the wheels rotate in opposite directions, and once it sees High it reverses the motors and so can follow a path by oscillating backwards and forwards with the sensor and line’s width determining pathing)
The Stinger on the other hand has two sets of Planar Control surfaces (once deployed one set is fixed at some AoA, the other can freely deflect into the airstream) this allows it to use the fixed surface’s inherent lift generation (and implicit moment coupling) to allow it to maintain the rotation and thus control surface effectiveness and not need the motive surfaces to provide the moment coupling.
By dithering the motive surfaces, what is happening is that its avoiding the onset of the sustained inertia of the missile, by minimizing average out of plane rotation, because commands are no longer continuous (full deflection over a half rotation), but discrete inertial kicks in the more correct net direction of the target.
The relevant exerpt is as follows
Due to an oscillator, described presently, in the electronic portion of the guidance and control section 12 which causes continuous motion or dithering of the control surfaces 14, the motor 41 is sensitive to very small signals from the seeker section 11 since the dithering action overcomes the inertial effects of moving control surfaces 14.
Part of this is due the fact that the surfaces cycle around ~250 times a second, and the missile body rotates at approximately 14~17Hz or so. and actuating at much higher rate reduces the apparent inertial forces significantly.
