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Sensors 2016, 16(3), 299; doi:10.3390/s16030299

The Additional Error of Inertial Sensors Induced by Hypersonic Flight Conditions

1
Department of Biotechnology and Engineering, National Technical University of Ukraine “Kyiv Polytechnic Institute”, 37, Avenue Peremogy, Kyiv 03056, Ukraine
2
Industrial Research Institute for Automation and Measurements PIAP, Jerozolimskie 202, 02-486 Warsaw, Poland
3
Institute of Metrology and Biomedical Engineering, Warsaw University of Technology, Boboli 8, 02-525 Warsaw, Poland
4
Foreign Languages Department, Zhytomyr State Technological University, Chernyakhovskogo str., 103, Zhуtomуr 10005, Ukraine
*
Author to whom correspondence should be addressed.
Academic Editor: Vittorio M. N. Passaro
Received: 2 November 2015 / Revised: 18 February 2016 / Accepted: 19 February 2016 / Published: 26 February 2016
(This article belongs to the Section Physical Sensors)
View Full-Text   |   Download PDF [1324 KB, uploaded 26 February 2016]   |  

Abstract

The emergence of hypersonic technology pose a new challenge for inertial navigation sensors, widely used in aerospace industry. The main problems are: extremely high temperatures, vibration of the fuselage, penetrating acoustic radiation and shock N-waves. The nature of the additional errors of the gyroscopic inertial sensor with hydrostatic suspension components under operating conditions generated by forced precession of the movable part of the suspension due to diffraction phenomena in acoustic fields is explained. The cause of the disturbing moments in the form of the Coriolis inertia forces during the transition of the suspension surface into the category of impedance is revealed. The boundaries of occurrence of the features on the resonance wave match are described. The values of the “false” angular velocity as a result of the elastic-stress state of suspension in the acoustic fields are determined. View Full-Text
Keywords: hypersonic technologies; inertial sensors; additional acoustic error hypersonic technologies; inertial sensors; additional acoustic error
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This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).

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MDPI and ACS Style

Karachun, V.; Mel’nick, V.; Korobiichuk, I.; Nowicki, M.; Szewczyk, R.; Kobzar, S. The Additional Error of Inertial Sensors Induced by Hypersonic Flight Conditions. Sensors 2016, 16, 299.

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