초록 ▼

A self adaptive limiter for use in aircraft control systems during approach and landing is disclosed. Estimated flight path angle is continuously computed during the glidepath tracking phase until a predetermined lock altitude above ground when a nominal flight path angle is latched. Nominal vertica

A self adaptive limiter for use in aircraft control systems during approach and landing is disclosed. Estimated flight path angle is continuously computed during the glidepath tracking phase until a predetermined lock altitude above ground when a nominal flight path angle is latched. Nominal vertical speed is continuously computed below the lock altitude as a function of the latched nominal flight path angle and ground speed of the aircraft. A vertical speed limit function is generated as a function of the nominal vertical speed and radio altitude. During approach and landing a pitch limit is computed from the vertical speed limit, vertical speed, ground speed, and pitch. When a pitch command to the autopilot exceeds the pitch limit(i.e. commands excessive pitch down attitude), it is limited to the pitch limit thus preventing the aircraft from descending below a safe altitude. The invention is self-adaptive since the pitch limit varies in response to changes in the ground speed of the aircraft, wind, and ILS beam angles.

대표청구항 ▼

[ The embodiments of an invention in which an exclusive property or right is claimed are defined as follows:] [1.] A fail operational flight control system for controlling the flight path of an aircraft within 18 miles of a destination runway, said control system in communication with aircraft syste

[ The embodiments of an invention in which an exclusive property or right is claimed are defined as follows:] [1.] A fail operational flight control system for controlling the flight path of an aircraft within 18 miles of a destination runway, said control system in communication with aircraft systems providing vertical speed data, horizontal speed data, altitude data, and pitch data representative of said aircraft, said control system comprising:a) a self adaptive pitch-limit computation apparatus, said pitch-limit computation apparatus having,1) angle computing means for computing an estimated flight path angle,2) averaging means for computing a nominal flight path angle from said estimated flight path angle,3) vertical speed means for computing nominal vertical speed from said nominal flight path angle and said horizontal speed data, and,4) vertical speed limit means for computing a vertical speed limit from said nominal vertical speed.