Patent ID: 6168117
Filing Date: 2001-01-02
Classification: B64C,G05D

Abstract:
A flight control system for an airplane, having a roll axis maneuvering device for controlling a rolling motion of the airplane, a pitch axis maneuvering device for controlling a pitching motion of the airplane, an altitude sensor for detecting an altitude of the airplane, and an attitude sensor for detecting various angles including a bank angle of the airplane, comprising: a vertical acceleration sensor for detecting a vertical acceleration of the airplane and for generating a vertical acceleration signal; vertical acceleration control means responsive to said vertical acceleration signal for calculating an acceleration deviation of the acceleration from a target turn acceleration and a pitch axis steering angle command for making said acceleration deviation to zero and for transmitting the pitch axis steering angle command to said pitch axis maneuvering device; reference bank angle calculating means responsive to a target turn acceleration command for calculating a reference bank angle and for generating a reference bank angle signal; altitude control means responsive to said altitude for calculating an altitude deviation of the airplane from a target altitude and a bank angle correcting quantity from said altitude deviation and for generating a bank angle command signal by correcting said reference bank angle signal using said bank angle correction quantity; and roll axis control means responsive to said bank angle command signal for calculating a bank angle deviation of said bank angle from the bank angle command and roll axis steering angle command for making said bank angle deviation to zero and for transmitting the roll axis steering angle command to said roll axis maneuvering device as a manipulated variable so as to attain a precise control of said airplane with high response ability and accuracy.