Thanks to our dear Hesham - Here are some excerpts I've made on the proposed control systems for the tailless versions (From Paper 78-100 at AIAA 16th Aerospace Sciences Meeting, Huntsville, Ala., Jan. 16-18 1978):
"The figure shows the strong influence of airload distribution on bending moment and the importance of the tip fins in producing an efficient spanwise airload distribution. The simple rectangular planform that houses the payload is not nearly as efficient as a more tailored planform in producing the elliptical Joad distribution. The tip fins carry the required lift to increase effective aspect ratio from 4.9 to 7.9. This results in significant improvements in LID without a significant penalty on wing bending moment. [...] Whereas normal airplane configurations with tapered wings require considerable twist to prevent tip stall, the rectangular wings on distributed load airplanes will have lower section lift coefficients at the tip. Therefore it is possible to build the basic wing box without twist and to control the span load distribution with relatively small deflections of the control surfaces."
"An essential function of flight controls will be to regulate flight loads at all times and, as such, the controls will become as important to the airplane as the primary structure itself. [...section on multiple redundant computers and automated-diagnosing of system failures]"
"The control surfaces function both as flaps and primary flight controls. The wingtip fins provide directional and engine-out control. Operated together, they function as both a redundant pitch control and as side force generators. The airplane with this system is capable of direct lift control, permitting a flat landing attitude. The large span makes it desirable to land at very small roll angles, and it is probable that a tight control on roll will be maintained automatically during landings."
"The control surfaces function both as flaps and primary flight controls. The wingtip fins provide directional and engine-out control. Operated together, they function as both a redundant pitch control and as side force generators. The airplane with this system is capable of direct lift control, permitting a flat landing attitude."
