SYSTEM OF FLIGHT AUTOMATIC CONTROL OF HIGH MANEUVERING AIRCRAFT

FIELD: engines and pumps. ^ SUBSTANCE: suggested system for an automatic control of aircraft transfer into a horizontal flight foresees cross control of longitudinal and transversal channels. To achieve the said a signal of a specified normal overload in the system is generated as a signal proportional to product of signals corresponding to a vertical speed and to an absolute value of a current roll angle, at that the signal is generated so, that the latter is negative at an absolute value of roll angles less than 80, equal to zero at roll angles from 80 to 100, and positive at absolute values of roll angles more than 100. The signal of the specified value of a roll angle is generated as the signal depending on a vertical speed with consideration to a sign of a roll angle at the moment of switching the mode of aircraft transfer into a horizontal flight. If at the moment a sum of signals corresponding to values of a current roll angle and a current roll angle speed by its absolute value does not exceed the signal corresponding to the roll angle of 180, then the sign of a specified value of the roll angle corresponds to the sign of a roll angle. If a sum of the said signals exceeds in its absolute value the signal corresponding to the roll angle of 180, then the sign of the signal corresponding to a specified roll angle value is changed to an opposite. Additionally this system of automatic control foresees a forced switching of auto throttle which controls an instrument speed. ^ EFFECT: invention increases a flight safety due to essential decrease of time for an aircraft transfer into a horizontal flight and decrease of a possibility of an aircraft overrunning the range of maximum allowed values of an instrumental speed. ^ 3 cl, 1 dwg