STATIC AND FULL PRESSURE MEASUREMENT SYSTEM USING INITIAL SIGNAL SPLITTING AT THE SECONDARY CONVERTER INPUT
Annotation
Pressure sensors are widely used in aircraft to measure the static and full pressure of the oncoming air flow as a primary information in on-board air signal systems. In the data system, the measurement results are recalculation automatically to determine the flight altitude, speed, true air speed, Mach number, and vertical speed, according to well-known algorithms. A sensor of the full and static pressure with elastic membrane sensing element is presented. The membrane deformation is measured by an optical system, consisting of radiation source and position-sensitive photodetector based on the photo-detector line, installed opposite each other, with a curtain attached to the membrane center and placed between them. The membrane deformation displaces the optical spots formed on the photodetector surface by the passed through slits in the curtain. A novelty of the proposed sensor consists in the use of splitting of the initial information achieved by application of shutter with n slits forming n light spots on the photodetector, and these spots are displaced depending on the change in the measured pressure. Thanks to this innovation, it is possible to obtain n independent values of the measured pressure for one cycle of sensor line polling and to increase the measurement accuracy by averaging the results. The absence of additional elements on the curtains (emitters and light detector) improves the dynamic characteristics of the sensor. The proposed solution made it possible to minimize the influence of external disturbing factors (in particular, the aircraft vibrations) and to increase the accuracy and speed of the pressure sensor. Experiments carried out using a laboratory facility have confirmed the high level of the pressure sensor metrological performance.
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