| 摘要 |
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft condition field monitoring systems. The aircraft structure technical state monitoring system contains sensors of technical condition of helicopter blades of an oar or airplane outer wing panels and onboard recorder unit. On each helicopter blade of an oar or airplane outer wing panel there are not less than two fibre-optic Bragg grating strain sensors and not less than two vibroacoustic sensors. The system includes fibre-optic trunk cables, optical connectors, electric control buses, optical switches, fibre-optic measuring lines. Helicopter monitoring system additionally comprises optical rotating connector. The recorder unit contains reference signal unit, fibre-optic switching unit, light source unit, spectrum analysis unit, control and data analysis unit, data storage unit, The recorder unit has electric control signal input/output and electric power supply input, electric power supply unit. Strain sensors and vibroacoustic sensors are imbedded into the mass of composite material in top-loaded parts of helicopter blades of an oar spars and airplane outer wing panels.EFFECT: possibility to monitor technical condition of blade spars and outer wing panels made of composite materials in manufacturing and in service.4 cl, 5 dwg |
