METHOD OF CONTROL OF FLYING VEHICLE AND DEVICE FOR REALIZATION OF THIS METHOD (VERSIONS) Russian patent published in 2007 - IPC B64C9/02 B64C9/04 B64C9/12 

FIELD: aviation and aerodynamics of flying vehicle control members.

SUBSTANCE: according to one version, method of control of flying vehicle consists in distribution of pressure over lifting surface by deflecting the trailing edge of lifting surface and flaps. At control of distribution of pressure, upper flap of wing is deflected upward simultaneously with upward deflection of trailing edge on upper surface of each wing; at downward deflection of edge, lower flap of wing is deflected downward on lower surface of each wing. At control of distribution of pressure on vertical tail, flap on left-hand surface of vertical tail is deflected to the left simultaneously with deflection of trailing edge of rudder; at deflection of rudder trailing edge to the right, flap of right-hand surface of vertical tail is deflected respectively to the right. Device proposed for realization of this method includes deflectable trailing edge of lifting surface and flaps with drives for their deflection. Flaps are mounted on upper and lower surfaces of wing on area in front of axis of turn of external section of aileron to elastic axis of wing. Axis of turn of each flap is oriented along wing span. Each flap differs in span from aileron by no more than 50%. Each flap and aileron are provided with individual drives for their deflection at absence of kinematic linkage of flap with aileron. Vertical tail has flaps mounted on left-hand and right-hand surfaces on area in front of axis of turn of rudder to elastic axis of vertical tail. Axis of turn of each flap is oriented along vertical tail span. Each flap has the same span as the rudder. Each flap and rudder are provided with individual drives for their independent deflection at absence of kinematic linkage of flaps with rudder.

EFFECT: reduction of losses for aerodynamic drag; reduction of unfavorable torque; simplified construction of aircraft.

8 cl, 21 dwg