Composite situation analyzer and instrument flight system

Abstract

Flight path angle is displayed relative to the aircraft reference indicator in a unique display and aircraft control system particularly useful during approach operations. Flight path angle is computed as a function of vertical velocity of the aircraft and air speed. Angle of attack is displayed as an angle relative to the flight path angle and is derived by computing the difference between pitch and flight path angle. Thrust command is displayed vertically relative to the aircraft reference indicator while heading command is displayed laterally with respect to the aircraft reference indicator. In the approach mode, a pitch command computer produces a pitch command signal for controlling an aircraft's pitch to maintain a desired angle of attack, and hence, a desired air speed; a thrust command computer produces a thrust command signal for controlling the flight path angle to maintain an aircraft on a desired glide path for landing; and a desired heading command computer produces a heading command signal for controlling the aircraft's heading to maintain a desired course or heading depending upon mode selection. In addition in the approach mode, the unique display and control system provides the capability of substituting the flight path angle with a ground path angle input. This offers the advantage that the projection of the aircraft symbol relative to the horizon is really where the aircraft is going relative to the ground. A runway symbol is displayed in the approach mode only and is driven by the output of a navigation receiver.

Dependencies are inferred from the claim text.