FIELD: test equipment.
SUBSTANCE: invention relates to testing equipment. Method consists in that on the base on which the aircraft equipment is installed in the form of two identical onboard compressors for obtaining compressed air on board the aircraft, one compressor is installed on standard rubber vibration absorbers, and the other compressor is installed on the investigated dual-mass vibration isolation system including rubber vibration absorbers and a resiliently damping intermediate plate with vibration absorbers, for example, in the form of plates from polyurethane, which like the standard rubber vibration absorbers of the compressor are installed on a rigid bulkhead, which is installed on the base via a vibro-damping gasket. On the rigid bulkhead, between the compressors, a vibration sensor is fixed, the signal from which is directed to an amplifier and the recording equipment, for example an octave spectrometer operating within the frequency band (Hz): 2; 4; 8; 16; 31.5; 63; 125; 250; 500; 1,000; 2,000; 4,000; 8,000 Hz. Then the obtained amplitude-frequency characteristics of operation of each of the compressors are compared and conclusions on vibration isolation efficiency of each system, where they are installed, are made. To determine fundamental frequencies of each of the analyzed vibration isolation systems, impact pulse loads are simulated on each of the systems with the help of a diagnostic impact device, comprising a body, piezoelectric dynamometer, impact element, and on the base on which a rigid bulkhead with installed sensors and onboard compressors is installed through the vibro-damping gasket, a sensor is additionally installed to measure the amplitude-frequency characteristics of the base, signal from which is directed to an amplifier and spectrometer, and for carrying out the harmonic analysis of the vibration isolation system "the second compressor is directed to the resiliently damping intermediate plate with vibration absorbers", as well as to identify the vibration-isolation properties of vibration absorbers and to select their optimum parameters, an additional sensor is additionally installed on the resiliently damping intermediate plate to measure its amplitude-frequency characteristics, the signal from which is directed to an amplifier and spectrometer. To analyze the maximum vibration amplitude of individual constituent elements of a vibration isolation system between the base and rigid bulkhead relative displacement sensor is additionally installed to measure the vibration amplitude, the signal from which is directed to an amplifier and spectrometer.
EFFECT: technical result is expansion of technological capabilities of testing objects having several flexible links with aircraft structural parts.
1 cl, 5 dwg
