FIELD: flight testing.
SUBSTANCE: invention relates to the field of flight testing of aircraft gas turbine engines, and can also be used in the practice of measuring deformations, temperatures, vibrations, etc. in the aviation industry, mechanical engineering, construction in the study of the strength of nodes of rotating structures under conditions of a high level of interfering factors. Digital non-contact multi-channel measuring complex for flight testing of aircraft gas turbine engines consists of a measuring unit, receiving and power units, recording and visualization tools. On the rotor part of the measuring unit there are 16 measuring channels with a data converter of all channels into a single digital stream with encoding according to the Manchester protocol, a transmitting antenna of the digital data stream, as well as a supply voltage driver with an inductive power receiving antenna. On the stator part of the measuring unit, there is a transmitting antenna for inductive power and a receiving antenna for a digital data stream. The transmission channel of the digital data stream is made in the form of a non-contact rotating differentiating circuit, data transmission occurs only at the moments of rise and fall of the fronts of rectangular pulses, data transmission does not occur in stationary sections of the digital stream, which significantly increases the noise immunity of the transmission channel. A receiving unit is located on the stator part of the aircraft engine, in which the sequence of digital data is restored, frames are formed and they are transferred to the memory of a personal computer via the Ethernet protocol. In addition, the unit generates and inductively transmits electricity to the rotor part of the measuring unit to power the electronic components located on the rotor part.
EFFECT: creation of digital non-contact multi-channel measuring complex for flight testing of aircraft gas turbine engines.
1 cl, 2 dwg
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