Abstract An aircraft control system particularly useful during approach operations. 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 airspeed; and 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. The command signals control either instrument indicators which visually display the appropriate information to the pilot for manual operation or alternatively control an autopilot and autothrottle for automatic operation of the aircraft. If the aircraft is below the desired glide path but at the desired airspeed, a thrust command computer indicates the direction necessary to change the thrust to increase the aircraft''s flight path angle so that the aircraft returns to the glide path. As the thrust level is varied according to the thrust command signal, an angle of attack sensor senses the changes in the angle of attack of the aircraft and a pitch command computer produces a pitch command signal to maintain the angle of attack at a desired level determined from the desired airspeed. In addition to the approach mode, the control system offers advantages in the take off, climb, hold, maximum range, severe turbulence, and descent modes of an aircraft''s operation. The cruise mode operates similar to prior art systems.
A display system for automatically indicating the direction in which to change the thrust level of an aircraft to maintain the aircraft on a desired glide path comprising: a. first computing means for operating a first signal indicative of the aircraft''s vertical displacement from said desired glide path, b. second computing means responsive to said first signal for generating a second signal indicative of the desired rate of return of said aircraft to said desired glide path, c. third computing means responsive to said first signal for generating a third signal indicative of the aircraft''s actual rate of return to said desired glide path, d. means responsive to said second and third signals for generating a fourth signal indicative of the difference between the desired and actual rates of return of said aircrafts to said desired glide path, and e. thrust command display means responsive to said fourth signal for displaying an indication of said fourth signal.
Claim 2
Dependent Claim
157 words
A display system for automatically indicating the direction in which to change the thrust level of an aircraft to maintain the aircraft on a desired glide path comprising: a. first computing means for operating a first signal indicative of the aircraft''s vertical displacement from said desired glide path, b. second computing means responsive to said first signal for generating a second signal indicative of the desired rate of return of said aircraft to said desired glide path, c. third computing means responsive to said first signal for generating a third signal indicative of the aircraft''s actual rate of return to said desired glide path, d. means responsive to said second and third signals for generating a fourth signal indicative of the difference between the desired and actual rates of return of said aircrafts to said desired glide path, and e. thrust command display means responsive to said fourth signal for displaying an indication of said fourth signal.