SYSTEM FOR AUTOMATIC CONTROL OF HIGHLY-MANEUVERABLE AIRCRAFT FLIGHT Russian patent published in 2008 - IPC B64C13/18 

FIELD: transportation; information technologies.

SUBSTANCE: aircraft control system failure allow for switchover from primary control loop to backup control loop under condition of information system failure. At output of information system altitude-speed parameters signals are generated such as static pressure, dynamic impact air pressure, Mach number. At output of central sensor unit signals of normal glideslope, angular velocity in pitch and stick position are generated. There are calculators of main and backup control loops, actuator and aerodynamic controller. Memory device, two threshold devices, logical device and integrating device are additionally introduced in backup control loop. When information system fails the actuator is disconnected from main control loop calculator and connected to backup control loop calculator. Herewith flight altitude-speed parameters for information system failure moment are stored in backup loop and aircraft attitude is determined. According to aircraft attitude at the moment of information system failure, fixed values of altitude-speed parameters and time period within which they have to be changed from values for information system failure moment to selected values are selected.

EFFECT: switch to backup control loop without dynamic errors according to overload control signals and angular velocity and flight safety improvement.

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