US 11,841,713 B2
Controllers and aircraft with takeoff stall protection system
Jong-Yeob Shin, Savannah, GA (US); Gi-Yun Chung, Savannah, GA (US); and Lakmal Kaviratna, Savannah, GA (US)
Assigned to Gulfstream Aerospace Corporation
Filed by Gulfstream Aerospace Corporation, Savannah, GA (US)
Filed on Jan. 7, 2020, as Appl. No. 16/736,036.
Prior Publication US 2021/0206476 A1, Jul. 8, 2021
Int. Cl. G05D 1/08 (2006.01); B64C 13/16 (2006.01); B64C 13/04 (2006.01); B64C 9/00 (2006.01); B64C 13/26 (2006.01); B64D 43/02 (2006.01)
CPC G05D 1/0833 (2013.01) [B64C 9/00 (2013.01); B64C 13/0421 (2018.01); B64C 13/16 (2013.01); B64C 13/26 (2013.01); B64D 43/02 (2013.01); G05D 1/0808 (2013.01); G05D 1/0816 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A flight control system for an aircraft comprising:
an input configured to generate a position signal in response to a pilot input; and
at least one processor operative to receive the position signal, the at least one processor operative to
calculate a pitch rate command in response to the position signal;
calculate a pitch angle saturation limit during takeoff based at least in part on
a flight path angle during takeoff, and
a stall angle of attack of the aircraft;
compare the pitch angle saturation limit during takeoff to a sum of
a scaled pitch angle,
a scaled pitch rate, and
the pitch rate command;
generate a damped pitch rate command by modifying the pitch rate command to limit an aircraft pitch attitude; and
generate a control signal from the damped pitch rate command when a sum of the scaled pitch angle, the scaled pitch rate, and the pitch rate command is greater than the pitch angle saturation limit during takeoff of the aircraft, the control signal for coupling to an aircraft control surface that is operative to alter the aircraft pitch attitude in response to the control signal.