FIELD: test equipment.
SUBSTANCE: invention relates to testing equipment. In the stand for the study of vibration isolation systems, containing a base on which additional plates are placed with vibration-proof devices fixed to them and recording equipment, on the basis of installed equipment of aircraft, for example, two identical on-board compressors for obtaining compressed air on board the aircraft, while one compressor is installed on the regular rubber vibration isolators, and another compressor is installed on the investigated two-mass vibration isolation system, which includes rubber vibration isolators and elastic-damping intermediate plate with vibration isolators, for example, in the form of plates of polyurethane, which, just like the standard rubber vibration isolators of the compressor are installed on a rigid bulkhead, which is installed on the base through a vibration damping gasket, and on the rigid bulkhead, between compressors, a vibration sensor is secured, signal from which is supplied to the amplifier and recording equipment, for example, octave spectrometer operating in the frequency band (Hz): 2; 4; 8; 16; 31.5; 63; 125; 250; 500; 1,000; 2,000; 4,000; 8,000, and 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. On the base, on which rigid bulkhead is installed through the vibration damping pad, with the sensor and on-board compressors installed thereon, sensor is additionally installed for the base amplitude-frequency characteristics measuring, the signal from which comes to the amplifier and spectrometer. Base on which a rigid bulkhead is installed through the vibration damping gasket is connected to a rod-like spatial vibration isolation system including elastic platforms: upper and lower, between which the rod elastic elements are hinged, allowing to control all six coordinates of the displacement of the on-board compressors under shock and vibration loads.
EFFECT: expanded process functionality of testing objects having several flexible links with aircraft structural parts.
1 cl, 5 dwg
