The paper considers the improvement of accuracy of spacecraft attitude determination. The task is per-formed using the identification of drift model coefficients and referencing the measurement axes of gimballess ESG to the axes of celestial sighting device under normal operation. The real-time software for the automatic calibration of drift model coefficients of ESG couple and spacecraft attitude determination is developed. Results of office studies of ESG data are presented.

The parametric electrode is normally used in the hemispherical resonator gyroscopes, operating in the whole angle regime, for maintaining amplitudes of vibratory patterns. It is well known that owing to the variation of the gap between the resonator and parametric electrode, a drift of the vibrating patternis obtained. This drift is similar to the gyro drift stipulated by the Q-factor imperfections and substantially decreases the quality of the hemispherical resonator gy-roscope. The present paper considers the methods of compensation of these drifts by means of the special control of the vibrating pattern by the sectioned parametric electrode. Compensa-tion of the drifts is achieved through amplitudes of voltage and phase manipulations at the sectioned parametric electrodes. The side effect of this control which consists of the spurious splitting of the frequencies of the vibrating pattern is discussed.

The paper considers Allan variance, an up-to-date data diffusion characteristic which is gaining more and more popularity in applied fields, such as estimating the performance of navigation aids. To analyze Allan variance and to compare it with the other estimates a system for esti-mating the measurement errors is presented. Allan variance is compared with a classical sam-pling variance based on the theory of statistical decisions. For the formal description of Allan variance and other error characteristics it is proposed to use the functional Hilbertian spaces with reproducing kernels.

The procedure of checking the external navigational information is considered as ap-plied to a semianalytic-type inertial navigation system (INS) using algorithms of op-timal filtering in a closed-loop correction system. Special attention is paid to check-ing of the data coming from a water speed log. Examples of processing the meas-urements containing different irregularities are presented.

In article "Parametrical synthesis of a dynamic system "the Small artificial satellite of the Earth - hi-rodempfers" with aperiodic mode of attenuation of own fluctuations" the opportunity of use of an aperiodic mode of calm of own fluctuations of an artificial satellite after action of in-dignations, as most energetically preferable from the point of view of the power savings and reducing time of stabilization concerning a surface of the Earth is considered. As a result at a design stage at corresponding selection of parameters of the satellite and hirodempfers the opportunity of maintenance of attenuation of own fluctuations of a small artificial satellite in an aperiodic mode takes place, that essentially increases a resource of useful functioning in an orbit and reduces time of preparation for work in a mode of its constant orientation to a surface of the Earth.

The paper addresses results of micromechanical sensors development provided by OAO Moscow Insti-tute of Electromechanics and Automatics. One of them - a single-axis angular rate sensor ÄÓÑ-ÌÌÀ - is designed to replace lot-produced electromechanical devices with a rotating rotor. The sensor has passed preliminary tests and has been tested on board Yak-130 aircraft. The second device - a three-axis motion parameter meter ÈÏÄ-ÌÌ -measures angular rates and linear accelerations on three perpendicular axes as well as pitch, roll and heading angles in inertial coordinate system. The sensor is designed for a wide range of flying vehicles both as a standby device to assist accurate measurement systems, and as a main device for un-manned vehicles. Its main advantages: miniature size: 40x40x40 mm, high accuracy, and low power consumption < 2.5 W. The paper also presents structural features and structural-and-functional construction of the developed devices. Their photos are shown. Technical data of these devices compared to that of lot-produced devices of similar purpose is given.

The paper presents the process flowchart and equipment for thermal deposition of chrome films 100 - 1000 A thick on the spherical surfaces of precision devices. Technical solutions to control the coating thickness during the deposition are proposed. Dependencies of the film electrical conductivity on its thickness and deposition conditions are given. Potential of the developed method for enhancing the gyro assemblies performance is evalu-ated.