| 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 ).
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