| 摘要 |
A control system (6) of an aircraft (1) comprises: a computer (15) which controls flight on the basis of either a flight control law (20) for controlling flight by controlling the angles of control surfaces (3) or a control surface/thrust force integrated flight control law (22) for controlling flight by controlling the angles of the control surfaces (3) and an engine thrust force; and a control surface trouble/damage detection device (18) for detecting that at least one of the control surfaces (3) is malfunctioning, and, when a malfunction of the control surface(s) (3) is detected, calculates, on the basis of the result of the detection, the angle of each control surface (3) and the rate of change of the control surface angle required for achieving a desired flight characteristic, and determines whether the calculated control surface angle or rate of change of the control surface angle is beyond a range within which changing is possible, thereby determining whether switching from the flight control law (20) to the control surface/thrust force integrated flight control law (22) is necessary. |
