This paper discusses the problem of integrating modern methods of forecasting and modeling complex technical objects into the learning process. As an example, the problem of solving a system of ordinary differential equations is considered, which has significant practical application. In particular, solving a system of differential equations can be an essential part of patents. The neural network method to solve this problem by using Matlab simulation software and visual modeling tool Simulink is considered. Efficient cloud-based solution to ordinary differential equations is presented.

The authors present a compensation model for the general ranking of alternatives in their order of preference, considering the dependence of the attributes of software for spacecraft control systems. Among the discussed features is one that consists in the use of a set of target functions, which cannot be optimized simultaneously, due to their inherent incommensurability and target conflict.

The article deals with the application of simulation modeling and optimization-simulation approach to solving problems of synthesis of structures of automated spacecraft control systems, namely, the choice of spacecraft control points, which are multifunctional aggregates of stationary and mobile elements dispersed in space with developed technical means of receiving, transmitting and processing information. Various approaches to the joint use of optimization and simulation models in the synthesis of the structure of complex systems are analyzed. The main attention is paid to the possibility of joint use in the synthesis of optimization and simulation models, their rational interaction in optimization and simulation procedures that describe both the composition and interrelationships of the structural elements of the system, as well as dynamic and stochastic aspects of their functioning. An optimization-simulation approach based on the joint use of optimization and simulation models in the process of searching for optimal structure options is proposed. Rational mapping of a set of interrelated functions performed by a control system into a set of interconnected nodes with appropriate technical means, taking into account the costs of creating or reconstructing the system, the costs of operation and operation, the requirements of operational efficiency of management, the reliability of technical means, the survivability and globality of the control system and other characteristics. Consideration of the problem of optimizing the distribution of tasks included in the control loop by levels and control nodes of the system and determining a set of technical means that minimize the costs of equipping nodes with technical means and their operation when performing restrictions on efficiency, hardware reliability of performing control tasks, weight and energy consumption of on-board equipment, loading of nodes, etc.

The paper considers the possibility of automating the recognition of anomalies and nonlinear properties of objects in different environments by assembling the UAV payload in the form of a nonlinear locator with a minimum participation of the operator in the processes of probing influence. The process of selecting the main flight platform has a number of requirements that meet the required mission, and by its tactics and technical characteristics it is able to fully implement monitoring algorithms. The theoretical basis of the model construction is given and the main parameters for the standard operation of the model in terms of height, speed and required payload set are defined. The regression model of the interval of scanning of terrain areas depending on the speed of the device and the load of the main processor is compiled. The results of the calculations are summarized and reduced to the method of automated detection of anomalies and nonlinear transitions of objects detected as a result of terrain scanning missions. The main operating properties and optimal conditions of external technological impacts of the developed mathematical model are described.

The paper considers the joint application of the Iridium satellite communications system as well as the GLONASS and GPS satellite navigation systems that corresponds to the CNS/ATM concept. The originality of the proposed detection method is in constant communication between an object and a control center. The method can be applied to both manned and unmanned aircrafts. In any case, a control center can quickly respond to deviations of the trajectory of an object, or to an operation of accelerometers at critical overloads. The paper examines the advantages of introducing the Iridium satellite radio navigation system into the aviation sector to monitor aircrafts in both manned and unmanned aircrafts. Technical and economic advantages are given on the example of various search and rescue operations.

The variant of representation of various objects on video images in the form of samples of space-subband vectors is resulted. The technique of estimation of differences of parameters of distribution of multidimensional space-subband vectors of objects image is given. As indicators of closeness of two regions of localization of space-subband vectors of different objects, the vector of modules of difference of eigenvalues of corresponding spectral matrices of different objects, received from corresponding subband covariance matrices of objects, is used. Experimental estimations of differences in localization regions of different objects of Copter type using their video images are given. It is shown that when there is an obvious external similarity of objects, the areas of their localization differ significantly in size and orientation. It is shown that the localization region parameters of object vectors are practically invariant to object rotations on the image. The possibility of using spatially sub-band vectors and their estimates to build the decisive rules for the recognition of different objects on video images is shown.

The processes of space debris capture and processing into fuel are considered. The mentioned processes have a number of limitations on the choice of materials to be recycled (space debris) and on the creation of spacecraft for space debris utilization (hereinafter - space debris collector). Management of space debris capture and utilization processes is inseparably connected with pseudo-liquid fuel, received by the collector from space debris. Pseudo-liquid fuel is finely dispersed garbage in the environment of hydrogen (fuel) and oxygen (oxidizer). To control the processes of space debris capture and utilization into fuel it is necessary to determine the choice of materials of the spacecraft capture device and manufacturing of internal systems. Efficiency of space debris capturing and utilization into fuel management will be provided by fulfilling a number of fundamental requirements in addition to those of the work: orbital altitude of space debris collector is conditioned by space debris location in space (orbit altitude, inclination); space debris is captured only from certain materials and alloys (metallized space debris); space debris is captured by the network at the intersection of the target orbit at small angles; material and structure of the tether is selected based on maximum tension and absence of breaks.

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