N–Хвиля і похибки двостепеневого інерціального сенсора за умови GUASI – гармонічної синхронної хитавиці

The article reveals the nature of the effect of N-waves on the two-degree differentiative gyroscope in the mode of breaking the sound barrier in order to determine the additional errors of kinematical inertial sensors during the flight operation. Attention is focused on the kinematical errors of the device, which are caused due to synchronous rolling of fuselage, as well as on the aural errors caused by a shock N-wave during the sound barrier breaking. It was shown that the angular motion of fuselage emphasizes the generated acoustic vibration of the gyroscope suspension. As a result, an intense-elastic condition arises, which is perceived as the input value, and which serves as an additional acoustic error. In the frameworks of the precessional theory, under the assumption of absence of the circulation of aircraft, the systematic error of angular positioning of the aircraft is determined, due to the emerging zero drift of gyroscope under the powerful shock N-wave of hypersonic aircraft. These results serve as a scientific basis to further improvement of the positioning accuracy of moving objects by autonomous means based on inertial instruments. Analytical description of the nature of the influence of N-waves on the elastic structures of on-board equipment increases the possibilities of deep and comprehensive analysis of hypersonic technologies during the flight operationАнализируется погрешность двухстепенного дифференцирующего поплавкового гироскопа под действием N-волны в режиме преодоления звукового барьера. Определяется сдвиг нуля и погрешность инерциального сенсора при летной эксплуатацииАналізується похибка двостепеневого диференційючого поплавкового гіроскопа під дією N-хвилі в режимі подолання звукового бар’єру. Визначається зсув нуля і похибка інерціального сенсора при льотній експлуатаці