초록 ▼

The present invention constitutes a system for generating an elevator command signal for directing a pilot in guiding his aircraft along a path effective for recovering from hazardous windshear conditions. The system includes a descending mode guidance subsystem (10), an ascending mode guidance subs

The present invention constitutes a system for generating an elevator command signal for directing a pilot in guiding his aircraft along a path effective for recovering from hazardous windshear conditions. The system includes a descending mode guidance subsystem (10), an ascending mode guidance subsystem (12) and a switching mechanism (14) for shifting between the two subsystems. The descending mode subsystem includes an acceleration generator (20), a flight path command generator (22), a flight path error generator (24), a descending mode pitch error generator (26), an airspeed control device (28) and a descending mode signal controller (30). These components are connected serially together and operate to form an elevator command signal corresponding to the acceleration required to halt the descent of the aircraft by a fixed altitude level. They also function to control and condition this signal with respect to important flight parameters such as the aircraft\s maximum safe angle of attack and the response capabilities of the pilot and aircraft.

대표청구항 ▼

A system for generating a guidance signal for directing a descending aircraft to recover from a windshear condition, the parameters characterizing the descent of said aircraft including airspeed, vertical velocity, and a first flight path, comprising: means receiving signals corresponding to said ve

A system for generating a guidance signal for directing a descending aircraft to recover from a windshear condition, the parameters characterizing the descent of said aircraft including airspeed, vertical velocity, and a first flight path, comprising: means receiving signals corresponding to said vertical velocity, airspeed, and first flight path for generating a pitch error signal representing the difference between said first flight path signal and a flight path command signal, the flight path command signal being generated from said vertical velocity and airspeed signals and representing a second flight path by which said aircraft can arrest its descent by a predetermined altitude; means for preventing said pitch error signal from assuming values that exceed a predetermined angle corresponding to a maximum safe angle of attack of said aircraft; means for adjusting said pitch error signal in accordance with said airspeed signal, thereby to compensate said pitch error signal for any airspeed in excess of said aircraft\s normal flight requirements; and means for limiting said flight path command signal to values corresponding to descent angles greater than a predetermined level below horizontal.