AEROPLANE WITH SYSTEM OF OBTAINING RESERVE INFORMATION ON ATTITUDE POSITION OF AIRCRAFT

FIELD: engines and pumps. ^ SUBSTANCE: distinctive feature of an aeroplane with a control integrated complex is the implementation of a system for obtaining reserve information on an attitude position. The system comprises units for evaluating of entry parameter mean value relative to a reserve position pitch, and to a reserve position of a roll angle, quaternion values of a course, a pitch, a roll; it comprises unit for evaluating position reserve angles, unit for correction of position reserve angles, unit for evaluating a zero drift of position reserve angles, unit for contracting of reserve angles, unit for quaternion integrating of angle speeds, unit for correcting angle speeds, a unit for evaluating a zero drift of angle speeds and a unit-Dispatcher. The operation of the system is based on the evaluation of angle coordinates of an aircraft by means of two essentially different methods depending on the current conditions of a flight. It is specifically foreseen to evaluate the current values of pitch and roll angles with Euler formulas on the base of instantly obtained information from on-board sensors (if a flight is horizontal) and also to evaluate current values of angle coordinates my means of integrating sensor values of angle speeds from the complex control system with usage of quaternions (during maneuvering). ^ EFFECT: increase of flight safety in case of a sudden failure of the main information sources on the attitude position. ^ 14 dwg, 29 tblr