A task of constructing a tightly-coupled inertial satellite integrated system under the conditions of limited visibility is considered in terms of solving both orientation and navigation problems. To determine the orientation parameters of a moving object, a doublemode gyrocompass is implemented, which comprises a gimballess inertial measurement unit (IMU) on fiber-optic gyros (FOG), and two-antenna receiving equipment (RE) of global satellite navigation system (GNSS). Algorithms and errors of a GNSSgyrocompass with antenna baseline at the level of wavelength of carrier frequency and satellite receivers with external reference oscillator are studied. At that, the IMU with the antenna module of GNSS RE operates in reverse modulation rotation mode. A specific feature of this system is that a GNSS-compass can be constructed while observing at least one navigation satellite of GPS or GLONASS; moreover, it has an autonomois operation mode which implements a stabilizer gyrocompass scheme based on the IMU and log data, as well as position reckoning in absence of signals from the navigation satellite. The ambiguity of phase measurements and unreliable measurements are removed by referring to the IMU data when forming differential measurements in the integrated system at the level of the first differences of phases. The results of desktop analysis of bench testing data for a prototype system Orion-M with a GNSS compass (designed by CSRI Elektropribor) comprising GNSS receiving units 2K-363E-62 (RIRV JSC) and FOG-based inertial unit VG 910 (Fizoptika JSC) are presented in the paper.

The paper considers the development of the approach proposed earlier by the author to ensure the imperturbability of dead reckoning, based on the construction of a single-channel inertial vertical using a trihedron of accelerometers and a single free gyroscope. In order to improve the accuracy of instantaneous orientation angles required to solve vehicle control problems, a method is proposed that uses the data from the inertial vertical channel, as well as the difference in heading values generated with the use of information from the free gyro and the “budget” MEMS inertial unit, and lag readings processed in accordance with the principle of gyroscopic orientation with a controllable pendulum. The simulation results are presented, which confirm the effectiveness of the proposed method.

This paper aims at investigating and analyzing the behavior of Micro Electromechanical Systems (MEMS) inertial sensors stochastic errors in both static and varying dynamic conditions using two MEMS-based Inertial Measurement Units (IMUs) of two different smartphones. The corresponding stochastic error processes were estimated using two different methods, the Allan Variance (AV) and the Generalized Method of Wavelets Moments (GMWM). The developed model parameters related to laboratory dynamic environment are compared to those obtained under static conditions. A contamination test was applied to all data sets to distinguish between clean and corrupted ones using a Confidence Interval (CI) investigation approach. A detailed analysis is presented to define the link between the error model parameters and the augmented dynamics of the tested smartphone platform. The paper proposes a new dynamically dependent integrated navigation algorithm which is capable of switching between different stochastic error parameters values according to the platform dynamics to eliminate dynamics-dependent effects. Finally, the performance of different stochastic models based on AV and GMWM were analyzed using simulated Inertial Navigation System (INS)/ Global Positioning System (GPS) data with induced GPS signal outages through the new proposed dynamically dependent algorithm.

The results showed that the obtained position accuracy is improved when using dynamic-dependent stochastic error models, through the adaptive integrated algorithm, instead of the commonly used static one, through the non-adaptive integrated one. The results also show that the stochastic error models from GMWM-based model structure offer better performance than those estimated from the AV-based model.

Mathematical models of three-dimensional nonstationary temperature fields of an angular rate measurement unit and the fiber optic gyroscopes included in it are constructed and implemented, both in the basic design and that with a reverse thermal control system. Comparative analysis of temperature fields under conditions of complex temperature effects is performed. The effectiveness of using the twocircuit reverse thermal control system is estimated.

At present, the information on the deflection of the vertical (DOV) is obtained by means of modern geopotential models. The authors have obtained the DOV model values in the Western Siberia Region; the results of their components comparison are analyzed in the paper. The said components have been calculated on the basis of global geopotential model EIGEN-6C4, as well as of the results of astrogeodetic measurements taken in the Western Siberia Region. The survey results showed that in plane areas standard deviations of model DOV from the on-ground values obtained by traditional astrogeodetic method, do not exceed 1 arc sec.

The paper addresses software-based joint processing of signals from global (GLONASS, GPS, BeiDou, Galileo) and regional (IRNSS) navigation satellite systems. General block diagram of an implemented model of software-based multisystem navigation receiver is presented, and its capability to process the signals from navigation systems are studied.

As a result of software processing, separate and joint navigation solutions were computed for the signals from 30 spacecraft of 5 different navigation systems used in the North-West of the Russian Federation. The accuracy of these solutions, as well as the values of horizontal dilution of precision are analyzed in the paper.

The paper presents the results of experimental research of time scales comparison by a differential method using the signals from global navigation satellite systems (GNSS), which demonstrate the possibility of taking into account the integer property of ambiguities of GLONASS unmanned spacecraft. The obtained value of random error of time scales comparison is about 55 ps.

This article is an overview of the papers presented at the European Navigation Conference 2017, and dedicated to the application of satellite technologies.