The following explicitly states that not all of the lift comes from the control surfaces, wich practically sinks Gaijin’s entire argument.
The desired-direction lift and quadrature lift ( the resultant force component in orthogonal direction due to the moment no longer being balanced caused by rotating frame of reference and motive fins being recessed at that instant)
which result are also shown in FIGURE 9. (US3010677A, see above)
Actually, the lift force generated by the wings is only a fraction of the required lift force. The remainder of the force is provided by the fuselage.
So at a reductive level yes, the Igla and the Redeye work effectively the same way (implementation is slightly different due to differing mechanization). For the Improved Guidance & Control section of the Stinger it has an additional set of oscillating, and Feedback inputs as to avoid building excessive inertia which it would then need to overcome.
Prior to the invention set forth in the hereinafter cited copening application, control of a rolling missile was effected by utilizing fixed incidence, variable area canards or wings which were extended into the missile air stream at a certain point in the revolution of the missile, as described (see Figure 9, above) The present invention constitutes another means for accomplishing the control of a rolling missile and is an improvement over the system described and claimed in (US3010677)
The servosystem of the present invention utilizes variable incidence wings or control surfaces as did the system disclosed in the above mentioned copending application. However, this invention provides an air vehicle such as a missile with a pair of fixed wings or canards and a pair of variable incidence control surfaces or canards which are continuously dithered or vibrated so as to provide instantaneous movement due to the elimination of the initial inertial force.