Windshear guidance for aircraft having inertial sensor

Details Windshear guidance for aircraft having inertial sensor Windshear guidance for aircraft having inertial sensor

G - Physics

05

D

341/97

G05D 1/10 (2006.01) G05D 1/06 (2006.01)

Patent

CA 1334862

An aircraft guidance system for flying an optimal inertial flight path in a windshear encounter. Zero inertial flight path angle command is utilized as the basis for guidance commands for either horizontal or vertical windshears; the flight path angle command is constant regardless of the actual magnitude of the shear. The effect of the guidance law described is to provide a zero inertial flight path angle to prolong excitation of the aircraft's phugoid oscillatory mode. By utilizing inertial flight path angle derived from an inertial refecence system, errors introduced by vertical gyroscope systems are eliminated and thus a very accurate flight path angle guidance law is produced. The described guidance control law maximizes the aircraft's time in the air during a windshear encounter. Protection against aircraft stall is also provided by using a computed variable maximum allowable angle of attack.

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