Zero drift of integrating gyroscope at asymmetrical deformation of suspension
DOI:
https://doi.org/10.15587/1729-4061.2013.14809Keywords:
Integrating gyroscope, zero drift, asymmetrical deformation of suspension, synchronous drift, asynchronous driftAbstract
The article reveals the nature of appearance of a systematic zero drift of the integrating gyroscope in hypersonic flight. It was found that with asymmetrical deformation of a suspension of a gyroscope its surface moves into the category of impedance structure that gives rise to disturbing moments in the existing quasi-harmonic drift of the fuselage. Identification of the extent of this influence will permit to improve the performance of the device.
The method of successive approximations permits in the first approximation to assess the impact of Euler inertial forces on the appearance of periodic and systematic components in the output of the gyroscope during a flight.
The values of the time-averaged systematic drift of the gyroscope output signal during synchronous and asynchronous angular motion of an aircraft were obtained.
The results can be used in stand half-size tests of on-board equipment to make technical solutions for the elimination of additional errors of inertial sensors.
When analyzing the errors of command and measurement complex devices, it is necessary to take into account not only the portable inertial forces, but also the disturbing moments of Coriolis forces, which occur at certain levels of ionizing shock sound N-wave. This outlines a range of technical solutions for acoustic comfort in the instrument compartmentReferences
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