The laser gyro frequency response is studied by means of numerical simulation using a phase equation. The calculation results are compared to the results of experimental measurements on a precision dynamic test-bench. Quantitative relationship between the threshold value of static lock-in zone and frequency response distortions is established. Numerical methods helped to obtain and experimentally confirm the quantitative dependence of frequency response distortion on the amplitude and frequency of meander-shaped biasing. It is shown that the biasing shape significantly affects the frequency response form. Furthermore, it is demonstrated that frequency-response distortions depend on conditions of its measurement, in particular, on the time. The conducted research allows biasing parameters to be optimized with a view to increase the accuracy of measurements using laser gyroscopes.

The effect of mutual delays in rate sensor (RS) channels on the accuracy of a strapdown inertial navigation system (SINS) has been studied. Two types of SINS motion have been identified, for which the delays of about one microsecond in the RS channels result in significant navigation errors. Sensitivity of navigation errors to the deviations from these motions has been investigated, as well as the effect of delays in the RS channels on real trajectories registered in course of flight tests.

The data processing problem in attitude and heading reference system based on two units of micromechanical gyroscopes is considered as a special class of information processing problems from two measurement sources. A novel algorithm used for processing the measurements data from two units of micromechanical gyroscopes is proposed, which can improve orientation system performance while reducing the requirements for external sensors. A mathematical error model of micromechanical gyroscopes and orientation system is given, considering the rotation of the measurement units, and the advantages of the proposed method is analyzed in comparison with other algorithms.

This paper presents a novel on line algorithm for maneuver classification of a moving vehicle with six degrees of freedom, using on-board MEMS IMU’s data (three accelerometers and three rate gyros). The classification is either discrete (i.e. high, low or no maneuver), or continuous (a value that reflects the intensity of the maneuver). It should be mentioned that there is no explicit solution for this problem in any research paper previously published, due to the inability to find a direct mathematical model capable of characterizing this problem, despite its importance and its impact in improving the functioning of navigation systems. The proposed algorithm is based on a machine learning technique called logistic regression, which is a discriminative probabilistic classification model. Computer simulations, using MEMS IMU’s data taken from real experiments of an UAV, showed the effectiveness of the proposed algorithm, taking into account the sampling time, and the suitability for a wide spectrum of applications.

A well-known method of 1/f-noise representation as a sum of steady processes is considered. Two series of forming filters are used within the frequency band specified by the user. Ratios of filter parameters are determined. Spectrum approximation error is studied. An algorithm of fluctuations modeling is proposed as a system of stochastic differential equations of the first order. The algorithm can be applied to the simulated models used in studying the errors of navigation systems.

Тhe paper addresses the problems associated with the design of electromagnetic log sensor for deep-sea investigations. Finite element analysis has been performed for the design computer model, and the results of structural parameters optimization to reduce the strains due to external hydrostatic pressure are presented. Interrelation between the design challenges and the specific features of manufacturing and operation is demonstrated.

The performance characteristics of gyroscopic angle sensors (GAS) with ball bearing suspension, such as determined magnetic pickup on angle sensor output circuits from torque motor currents, and rate of rotor’s controlled motion, significantly influence the operation of gyroplatform stabilization and control circuit. The GAS performance characteristics can be improved by upgrading their design. The idea of upgrade consists in making the electromagnetic circuits of angle sensors and torque motors mutually independent.

The paper presents brief history of development of new autonomous navigation equipment, a radio astronavigation system (radiosextant), and discusses new technological solutions implemented in the radiosextant, as well as the reasons for stopping its further development.