CORRECTED GYROCOMPASS SYNTHESIS AS A SYSTEM WITH CHANGEABLE STRUCTURE FOR AVIATION GRAVIMETRIC SYSTEM WITH PIEZOELECTRIC GRAVIMETER

摘要

The present article introduces the development of a corrected gyrocompass with an automatic switch of the gyrocompass into the gyroazimuth mode. The issues of multi-criterion synthesis of the gyrocompass control loop have been studied. The necessity of temporary delay input (with selected values) under the previously mentioned switching is shown. On the basis of given requirements, we chose the parameters which provide the device with a switching-back into the gyrocompass mode under any initial gyrocompass deviations in the horizontal plane. An algorithm of gyrocompass ballistic deviation compensation due to the amendment generated by the special observing device, without recourse to external information regarding the ship's acceleration, was developed.