The problems of formal description of the functional stability of navigation and information systems are considered using the concepts of the quality of the functions performed by them, taking into account the status of available navigation fields and the mobile radio systems used. The navigation information system is an automated information management system designed to control one or more mobile objects based on processing of their location, traffic parameters and status. A graphic interpretation of the process of ensuring the functional stability of the system is presented. Ensuring the functional sustainability of the navigation information system is reduced to the process of maintaining the current quality vector for performing the system functions in the required area.

Ionizing radiation from outer space is reported to be currently the main factor affecting spacecraft reliability. In present, calculations of reliability are carried out without an account for the effect of ionizing radiation because according to normative documents, the influence of ionizing radiation is to be accounted for only in the case of the absence of requirements to electronic products durability. Two mathematical models accounting for the increasing character of elements failure rates under the influence of ionizing radiation as a function of time are proposed. The first of the models allows to evaluate the reliability of equipment with structural diagram containing an unloaded reserve. The use of the second model makes it possible to reduce the volume of spacecraft equipment ground testing using the a priori information on its reliability.

To assess the reliability of space images, special studies should be made of the measurement and visual properties of images obtained by spacecraft surveying systems in various ranges of the electromagnetic spectrum. The need for geometric processing of raw space survey materials to produce highprecision products is due to the influence of distortions that arise during the formation of images under the influence of various factors. Features of estimation of geometrical accuracy of space survey materials are considered. A mathematical description of the fundamentals of the methodology used for estimating the coordinate-measuring characteristics of images obtained by the target equipment of space remote sensing systems of the Earth is given. Several problems arising in the estimation of geometrical accuracy of images, limitations and features of the methodology chosen for implementation are considered. Ways of overcoming the problems of estimating the coordinate-measuring characteristics are proposed. A method for determining sufficiency of a sample of test objects is described. Recommendations and requirements for reference points selection are given. The ways of further development of the technology of coordinatemeasuring characteristics estimation are specified.

Unified space platforms (USP) are increasingly being used In space projects implementation. The concept of the unification principle consists in the possibility of constructing space platforms with tactical and technical characteristics corresponding to the intended purpose of the spacecraft project from a set of reliable and tested blocks and devices, including those having flying qualifications. Application of unified space platforms is mainly aimed at providing a useful load of resources by mass, energy, operating conditions, required accuracy of orientation and stabilization, maneuvering capabilities in orbit, command and telemetry information. Basic concepts of comparative evaluation of the technical level of the universal space platforms are considered. The methods in question are reducing the multicriteria problem to a onecriterion one, by introducing a complex performance indicator that depends on partial parameters, thus performing the so-called convolution of criteria.

A method for determining motion parameters of low-orbit spacecraft is presented. The approach is based on joint use of high-sensitive accelerometers measurement data and information from the satellite navigation equipment. Methodical aspects of the use of these high-sensitive accelerometers are considered for the case of the presence of navigation equipment measurements as well as for intervals of orbital parameters forecast. Estimated accuracy of definition and forecasting of orbital motion parameters of space vehicles with the use of proposed technique with the account for technical characteristics of highsensitive accelerometers are compared with results obtained with traditionally applied methods of navigating problems solution. Limitations are formulated for the field of high-sensitive accelerometers application in low-orbit spacecrafts to guarantee the accuracy of navigation problems solutions. The presented results confirm the possibility to improve the accuracy of solving the problems of navigational support of flight control of space vehicles and the quality of target information processing.

Methodological, methodical, and technological basis of description and solving problems of reconfiguration of on-board equipment of small-sized spacecraft is proposed. An applied theory of proactive control over structure dynamics of complex technical objects is proposed as a mean for investigation and solving the reconfiguration problems. The problems under consideration are formally described and interpreted as the problems of dynamic structural-functional synthesis of complex technical objects. The developed models, methods, and algorithms are based on constructive implementation of the concepts of integrated modeling and proactive management. Data on the practical implementation of the developed special model-algorithmic support in an experimental sample of the software package are presented.

The inverse geometry of radio tomographic satellite sounding of the ionosphere with the use of ground-based transmitters system signals is considered. The main advantages of the inverse scheme of ionosphere radio tomography are complete control over work of ground transmitters, simplification of receiver integration into the a small spacecraft structure, and also a low cost of expansion and service of ground radio beacons network. Technical characteristics of the proposed ground and satellite modules for ionosphere radio tomography equipment are presented.

The task of providing the required level of reliability of space equipment and its elements and modules is especially urgent in modern conditions. To solve this problem, a technology has been developed for assessing the reliability of elements and modules of advanced special and scientific equipment for space applications that have been operating for a long time in the space environment. The technology is a set of provisions, rules, techniques, mathematical models, algorithms and methods for assessing the reliability of elements and modules of new samples of advanced special and scientific equipment for space applications implemented using software and hardware means. The developed technology and hardware and software complexes are expected to be used at the enterprises of the rocket and space industry, as well as in the head organization on the Roscosmos information system for automated evaluation and analysis of the reliability of prospective spacecraft samples at the design, development and operation stages.

Methods of calculation acceleration in modeling radar systems with synthetic aperture on the GPU parallel architecture are considered. The simulation is based on a point model of the underlying surface. The modeling algorithm assumes preliminary calculation of the reflected signals with the increased sampling rate and subsequent approximation of obtained results to derive a hologram of the district model. It is shown that the time limit for hologram synthesis is defined as the product of number of processes in the block and the number of blocks in the lattice. The combination of these parameters is to be selected based on the architecture of the graphics accelerator. Results of simulations carried out on NVIDIA Tesla K20 GPU using CUDA are presented. Efficiency of the graphic accelerator application for modeling the RLS RSA is confirmed. Thus, in the case of a hologram for a 100x100 points model, the time gain is more than twenty times compared to calculations performed with a general-purpose processor.

Features of development, creation and testing of experimental sample of space plasma flow sensor using precision selective elements from nanostructured materials and a four-section collector are considered. The design features of the experimental sample of the plasma flow sensor based on the Faraday cylinder are discussed. Results of complex tests of physical functioning of the experimental sample of the cosmic plasma flow sensor and its selection elements are presented, calculated characteristics of the sensor are compared with results of the experimental studies. The comparison demonstrates a good agreement between blocking characteristics of the four-collector sample of the DP-10-34-4K sensor at normal and oblique incidence of the ion flow upon the sensor input window with corresponding calculated data, and thus confirms the possibility to reliably measure the transport flow velocity and its temperature in the isotropic approximation. Angular characteristics of the four sensor manifolds are symmetrical enough to coincide with the calculated ones, which allows using one sensor to determine the magnitude and direction of the ion flux, thereby reducing the mass of the device into which the sensor will be embedded.

The features of monitoring the state of rocket and space equipment (RCP), transported by rail, are analyzed. The questions of complex use of methods, technologies and means of navigational definitions are considered on the basis of combined navigation systems, including small-scale inertial-free modules with coordinate correction modules based on GLONASS/GPS signals. The developed experimental model of the hardware-software complex of multi-level wireless system for assessing the state of transported space objects is based on combination of navigation systems with telemetric means of measuring external factors affecting the transported RKT objects. Information about the state of the RCT facility is collected remotely by non-contact sensors with low power consumption. The sensors are integrated into a selforganizing wireless network using radio modules operating under the IEEE 802.15.4 ZigBee standard. This approach allows for the collection and transmission of information on the status of the monitored RCT facility at various levels of control and operational control in a near real time mode.