Patent Number: 6,168,117

Title: Flight control system for airplane

Abstract: A flight control system according to the present invention includes a vertical acceleration control device for calculating a pitch axis steering angle command to make a difference between a vertical acceleration of an airplane and a target turn acceleration to zero, and transmitting it as a variable to a pitch axis control device, a reference bank angle device for calculating a reference bank angle from the target turn acceleration, an altitude control device for calculating a bank angle correcting quantity from a difference between an altitude of the airplane and a target altitude and obtaining a bank angle command by correcting the reference bank angle, and a roll axis control device for calculating a roll axis steering angle command for make a difference between a real bank angle and the bank angle command to zero and for transmitting it as a variable to a roll axis control device.

Inventors: Shinagawa; Takashi (Utsunomiya, JP)

Assignee: Fuji Jukogyo Kabushiki Kaisha

International Classification: B64C 13/00 (20060101); B64C 13/16 (20060101); G05D 1/08 (20060101); B64C 013/16 ()

Expiration Date: 01/02/2018