| 摘要 |
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft gas turbine engine control systems. System implementing the method of detecting the falling of engine parameters beyond tolerances and defining the character of magnitudes of said parameters for detection of emergency situation probability. Signal about origination of emergency conditions aboard the aircraft is automatically transmitted to ground station to define level of fault and to prepare recommendations for its elimination. Proposed method comprises the following steps: detecting buildup of parameter threshold (E10) in engine operation; automatic transmission (E20) ob alarm message to ground surface; reception of said alarm message (E30) and its automatic processing (E40); automatic determination (E50) of fault level; incrementing the counter fault corresponding to said level (E60).EFFECT: higher reliability and safety.12 cl, 4 dwg |
