The article presents an overview of the research and development of gyroscopic technologies in Russia in the past 15 years. The current status and prospects for advancement of inertial technologies in future are analyzed.

The paper outlines an integrated navigation and attitude reference system (INARS), using a strapdown inertial attitude reference system (SIARS) based on electrostatic (ESG) and fiber-optic (FOG) gyros, for an orbital spacecraft. INARS algorithms are presented as regards co-processing of ESG and FOG data, which use the Kalman filter and the corresponding criteria. Given are the results of PC simulation of INARS operation algorithms in MATLAB package, using the real data array of ESG and FOG test results.

A method of fast first fix using a low cost GNSS receiver is represented. The method allows reducing significantly the time to first fix in the case that GNSS ephemerides, good estimates of the initial user position and time are available. It is also proposed to use Doppler measurements for the initial estimate of the user co- ordinates. Expected time to first fix depending on the input GNSS signal power is calculated.

A MEMS RR-type gyro consisting of uncased micromechanical sensors and ASIC for the gyro are presented. The results of the pilot batch tests are submitted for the gyro are presented. The results of the pilot batch tests are submitted.

Test results of the micromechanical RR-type gyro of MMG-2 modification, de- signed in CSRI "Elektropribor", are presented. The experimental estimations of the metrological characteristic variations when tests on centrifuge, vibration stand and shock table are carried out. Functions of device parameters related to mechanical effect are obtained. Methods of reduction of the vibration and impact influence on characteristics of MMG as angular rate sensor are determined. MMG as angular rate sensor are determined.

The paper considers the differences in accuracy criteria for the gyros in two applications: measuring rotation about a fixed axis and measuring rotation about a point. We describe the class of noises with zero spectral density at zero frequency. In these gyros, the noises do not cause the errors of apparent turn angles (integrals of angular rate projection on the gyro sensitivity axis) to accumulate in time, but lead to accumulation of error in attitude determined by strapdown inertial systems. Ways of identifying the gyro noise structure using the known lower order methods are analyzed: first difference method (Allan variance), second difference method (Hadamar variance), and proposed methods of higher orders differences.

When processing the results of airborne gravity survey in the Artic at flight heights of 2000 to 3000 m, the authors encountered the conditions when the free-air gravity anomaly exceeded the values taken from the anomaly map. The formula for the calculation of the vertical gradient as a function of latitude has been refined. The tentative calculations reported in the paper also indicate that free-air gravity anomaly above the mountainous areas contains additional positive systematic components, since only the effect of the vertical gradient of the normal gravity is taken into account here; and the flight height should be held constant during the survey, otherwise it would be needed to consider additional bias errors for different flights.

The paper deals with solving the problem of reliability calculation for redundant systems with consideration for the final composition of SPTA set equipment. The formulas for calculating probability of no-failure operation of typical element connecting circuits are suggested with due regard for the SPTA set final composition. The proposed approach gives a more accurate reliability evaluation in comparison with the techniques used at present time, and provides the reliability goal using a much smaller SPTA set.

The paper presents the sensitivity theory applications to the analysis of data processing and control systems under off-design operating conditions; to the problems of simplifying the mathematical error models, simplifying the filters in data processing systems and the regulating devices in controls systems; to the problems of synthesizing the systems with low or minimal sensitivity to simulation errors.