The Additional Error of Inertial Sensors Induced by Hypersonic Flight Conditions
AbstractThe 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
Share & Cite This Article
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.
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(3):299.Chicago/Turabian Style
Karachun, Volodimir; Mel’nick, Viktorij; Korobiichuk, Igor; Nowicki, Michał; Szewczyk, Roman; Kobzar, Svitlana. 2016. "The Additional Error of Inertial Sensors Induced by Hypersonic Flight Conditions." Sensors 16, no. 3: 299.
Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.