METHOD OF CONTROL OF LONGITUDINAL MOTION OF CANARD AEROPLANE WITH SWEPT-FORWARD WING AND DEVICE FOR REALIZATION OF THIS METHOD Russian patent published in 1996 - IPC

FIELD: aeronautical engineering. SUBSTANCE: method is based on joint deviation of control members - fore plane, elevens and tail panels at angle of attack up to that corresponding to maximum lift force α < αcy_max; elevens are deflected down- ward in function of angle of attack which is selected from condition of enhanced aerodynamic characteristics of aircraft; tail panels are deflected through angle determined by condition of longitudinal trim of aircraft at indicated position of elevens; at angles of attack of α > αcy_max, tail panels are deflected for aircraft trim and after they come to limit, elevens are deflected to the same side; at any angle of attack, stabilization of aircraft is effected through deflecting the tail panels and fore horizontal planes relative to their trim position. Device for realization of this method has computer, angle-of- attack sensor, pitch-rate pickup, normal g-load sensor and control stick position sensor; first, second and third adders, first and second aperiodic elements, servo units of fore horizontal planes, tail panels and elevens; first and second scaling units at adjustable gain and first, second and third nonlinear functional converters. EFFECT: enhanced stability and controllability of aircraft at static longitudinal instability at angles of attack of αcy_max- and enhanced longitudinal stability at α > αcy_max as well as enhanced efficiency of longitudinal control in entire range of angle of attack. 3 cl, 3 dwg