The article considers the possibility of organizing a single information space on the basis of a modernized document management system within the technically complex products life cycle, which involves the processing of a large amount of various information. The attention is focused on the fact that in the existing automation systems of various processes for creating products at various stages of the life cycle, the availability, connectivity and consistent storage of data in the corresponding accounting systems are not ensured. A method for organizing data on a product is proposed, and on its basis a tool for implementing a single source in the form of a document management system describes the advantages of its application when integrated into a single information space.
The paper considers a possible method of optimal controlling the mirror shape of a spacecraft (SC) large-sized reflector using the mechanisms affecting the reflector mirror shape in the course of its orbital operation. The authors give a theoretical justification for the applica-tion of the least squares problem and adapt the Gauss – Newton method used for solving it to the problem of the reflector mirror shape optimal control. Mathematical modeling confirmed the effectiveness of the method as applied to controlling the mirror shape of an umbrella type offset reflector with a diameter of more than 10 m, which includes a device for adjusting the reflector shape. The main issues of the method implementation are outlined in relation to the on-board system for monitoring the operational characteristics of a large-sized transformable antenna. The paper shows that the considered method can be used to control the operational characteristics of antennas with large-sized reflectors by affecting their geometric characteris-tics, namely, by bringing the reflector mirror shape to the desired profile. It is noted that in the context of meeting high requirements for the accuracy of the onboard antenna geometry, the use of the method will ensure the stability of the onboard antenna geometry and minimize the degradation of the antenna radio technical characteristics during orbital operation.
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