Gas turbine aeroengine control system

摘要: In a control system for gas turbine aero engine, the (ECU) is configured as dual comprising two channels, Ch-A and Ch-B. has CPUs which conduct calculations separately based on sensor outputs one of compares results if they coincide, CPU sends result other to FCU. If not, determines that an abnormality arises in Ch-B constituted standby channel having only whose operation monitored by simple watchdog timer circuit. This enhances failure detection with relatively configuration, eliminates need provision overspeed protector.