Global measuring station network requirements analysis had been done. Network design methodology is proposed and its performance experimental study for pre-cise navigation and timing service for GLONASS users are presented. Recommen-dations regarding GLONASS measuring facilities development has been provided.

The article discusses an aircraft integrated navigation system providing high accuracy positioning of phase center of multifunction airborne radar antenna. High accuracy positioning method is based on correction of estimates of integrated INS/GNSS navigation system. The simulation results prove the perspectives of this research direction.

In this paper we consider the problem of ensuring a given orientation of microsatellite with flywheels and electromagnetic executive bodies on a board. The papers gives control law for flywheels (7) and electromagnetic coils to discharge angular momentum flywheel (9). Paper gives simulation results for the orientation of the satellite (figure 2, 4) and discharging of flywheels kinetic moment (Figures 5). In addition paper gives results of digital modeling the behavior of the satellite during dis-charging flywheel kinetic moment at the time of failure of one or two components of the magnetometers on a board (Figures 6).

An approach to the development of trajectory motion control system for mobile robot along piecewise smooth path, defined by waypoints and parameterized set of straight and circular sections, is described. The synthesis of control based on the differential-geometric approach and nonlinear transformation of dynamic model. Main results are presented by task-oriented model of spatial motion and a suitable nonlinear algorithm of control.

Active industrial development of oil and gas in the ocean shelf area requires navigational and hydrographic support, one of the most important issues being the depth measurement. Effective survey of bottom profile can be conducted using a multi-beam echosounder, however, this method requires reliable data on hydrophysical characteristics of the surveyed water area. The proposed method of depth determination does not require the knowledge of the actual sound speed profile and can present a practical interest.

The information about development progress of strapdown inertial navigation system (SINS) based on laser gyros by the Ukrainian enterprises is presented. This system is designed for usage in control system of CYCLONE-4 launch vehicle (LV). Special attention is paid to issues of SINS experimental testing strategy in conditions of limited number of LV test launches as well as to analysis of test results of SINS experimental prototypes received during factory and environmental tests.

We have investigated a technique of registering the synchronization threshold of counter propagating waves in a ring laser based on digital processing of laser gyro quadrature signals. We have worked out requirements on mechanical rotation pro-viding a reasonable error of measurements. The process does not require any precision rotating unit. It is insensitive to equipment characteristics, is easy to implement, and excludes human factor.

The research problem of theoretical and applied aspects of the analysis and synthesis of the reversible Thermal Control System (TCS) Fiber-Optical Gyroscopes (FOG) and Strapdown Inertial Navigaton System (SINS) with these gyroscopes, fig.1-4, is delivered and solved. The purpose is essential increase of accuracy FOG and SINS. Application of Peltier’s modules in the thermal control system is offered and proved Mathematical models of dynamic systems "FOG-TCS", “SINS-TCS”, formulas (1)-(15) are constructed and researched. Supporting algorithmic and the software is developed. Parameters of the Thermal Control System are chosen. Estimations of functioning of dynamic systems are received at difficult temperature effects, fig 5-13.

Problems of angular rate sensor (ARS) development based on hemispherical resonator gyroscope (HRG) are considered. Sufficiency of the simplified gyro model is justified in the view of two equations for mathematical oscillator. By comparison of physical parameters of the metal resonator with mathematical model, special coefficients for equations are chosen as well as additional terms, which describe the external perturbations, are introduced in the right side of equation. The gyro mathematical model, derived in such a way, is a basis for mathematical program-ming, which, in turn, provides synthesis of the sensor for parameters to be set. On the basis of the development results, three-axis angular rate sensor assembly is manufactured and calibrated. The experimental results of the gyro assembly agree closely with the results of mathematical simulation.

The article describes the design and operation of two-speed measurement system of KIND34-064 rate gyro for spacecraft control systems developed at Kuznetsov Research Institute for Applied Mechanics. Key design features are covered, and results from accuracy tests of one measurement channel are provided.

Parameters of C40-ST-09 centrifuge by Actidyn Systemes are estimated using independent external aids. The proposed method to determine the error in compensation of centrifuge major axis rotation by its satellite mechanism uses a TA HS 500-57 autocollimator with 10 kHz readout frequency. The results of testing the proposed method are provided.