FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft engine control systems. Proposed system comprises piezo electric vibration transducers arranged at the casing of at least one helicopter rotor drive assembly and configured to receive comprehensive data sufficient for diagnostics of in-flight helicopter assembly units and part, and electronic unit. Said electronic unit is connected with outputs of piezo electric vibration transducers for digital processing of vibration signals, control and collection, primary processing and estimation of signal parameters of separate transducers and/or combinations thereof and storage the data on external and/or plug-in carriers suitable for readout by computer and second in-flight processing.
EFFECT: higher efficiency of data collection, control and diagnostics.
12 cl, 7 dwg
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