Development of the measuring channel of the pressure distribution system on the surface model of the aircraft during the experiment in the aerodynamic tube

Abstract

The development of modern aircraft construction is impossible without accurate aerodynamic tests (weight, drainage, strain gauge, flutter, bench, calibration), because they: allow to determine the aerodynamic properties of all aircraft and their parts; provide an opportunity to study the basic characteristics of the flow, especially when they are combined with methods of theoretical analysis. At the same time, the statistical analysis of the wind tunnel operation mode shows that the main disadvantages of drainage tests are the outdated and cumbersome system for determining the pressure at points with the help of liquid manometers. The expediency of using a strain-resistive semiconductor sensor HoneyWell Ultra Low Pressure Sensors, which has indisputable advantages among others, namely: compactness; the measurement range is 0.01% of the atmospheric pressure. To reduce the temperature error of strain-resistant transducers, the efficiency of using analog compensation devices based on the method of using temperature-dependent resistors is substantiated. The method of digital error compensation and the possibility of its use during modeling of the measuring channel are investigated. The structural scheme of the measuring channel is developed.