Source:  Cascade Ultralites 1983 promotional brochure.

    This is Figure 1 from the above patent.  It is a perspective view of the aircraft at rest, with all the directional control airfoils and vortex generating and control airfoils in their neutral positions.
    ABSTRACT:  Tailless airplanes, such as declared in U.S. Patent No. 3,438,597 as a stall occurs or is about to occur, may be flown at very high angles of attack to generate favorable spanwise vortex flows which augment the swept wing profiles creating resultant wing profiles having better lift characteristics, i.e., the vortexes created are lift generating.  However, the aircraft is then uncomfortable to be in during such flights at very high angles of attack.  Therefore, to achieve the benefits of this lift generating vortex flow, without maneuvering such aircraft into a very high angle of attack, the swept wing is equipped with airfoil structures and accessories which are extended beyond the cruising speed contour of the swept wing at lower speeds to create spanwise vortex air flows which selectably enlarge the effective overall airfoil contours as sensed by the passing major air flows.  Sustaining aerodynamic lift forces are thereby created at angles of attack well beyond the stall angles of the cruising airfoil contour and, by timely use of such airfoil structures, the vortex air flows are created soon enough for lift generating, so stable flight conditions may be created without so extensively altering the pitch of the landing and/or slow flying tailless aircraft.

    The wingtip rudders are the second roll control system which also have the dual function of yaw control.  In order to balance out the aerodynamic force on the deflected rudder, an aerodynamic balance forward of the hinge line is provided. (Fig. III-8)
    This aerodynamic balance moves over the wingtip when the rudder is deflected, acting as a spoiler on the wingtip and also adding to the drag.  The spoiler action decreases the lift on the wing.  Consequently the lift differential on the wing produces a rolling moment in the direction of the actuated rudder.  Additionally, because the endplates and rudders are inclined outboard, when the rudder is actuated, its inclination produces an additional downward force helping the roll.  Actually, the turn can be made with the rudder alone, without the need of aileron to "coordinate" it.  The figure below shows this concept from a top view.