| 摘要 |
The system (1) comprises three independent information sources (3, 4, 9), determining first, second and third values for an aerodynamic parameter of the aircraft and precision information indicating the precision of said values, a control means (6), acting on the operation of the engine (2), a sensor (7), measuring a fourth value for said parameter, an arithmetic unit (8), selecting a control value by using said first, second, third and fourth values of the aerodynamic parameter and the precision information and using said control value to determine a control sequence for the control means (6) and an information transmission network (12), to which said information sources (3, 4, 9) and the arithmetic unit (8) are connected, permitting a transmission of information between said sources of information (3, 4, 9) and said arithmetic unit (8). |
