| 摘要 |
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.
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