The Additional Error of Inertial Sensors Induced by Hypersonic Flight Conditions

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.

Information and measurement system of weapon stabilization parameters based on precision piezoelectric sensitive element

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Reproducing of security and limited visibility of fire weapons of defence line from aerial reconnaissance

“…The projects of cruise missiles, suborbital and atmospheric hypersonic technologies of different functions and other are developed along with ballistic missiles [1]. However, ground means of defense aren't lose their positions -fighting vehicles (tanks), antiaircraft guns, different mortar means, self-propelled artillery, kamikaze robots and so on.…”

Diffraction of sound waves on a metal ring

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