SYSTEM OF FLIGHT AUTOMATIC CONTROL OF HIGH MANEUVERING AIRCRAFT Russian patent published in 2008 - IPC B64C13/18 

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