Abstract. This paper is dedicated to the numerical simulation of the gasphase deposition into the porous carbon-carbon frame for the gradient thermal protection of reentry vehicles. The paper presents the specifics of creating the representative volume elements of the porous carbon-carbon frames based on the microstructure data from the computed tomography scanner, electronic scanning microscope and porosimetry results. The finite-element models of the representative volume elements are created in order to obtain the net independent solution, including the special finite elements at the phase interfaces. The finite-element and finite-volume method was used for calculation, implemented in MSC.Digimat and ANSYS software packages. The effect of the reagent parameters on the gas-phase deposition process, uniformity and rate of silicon carbide deposition was simulated parametrically, and the results are presented.

The rapidly developing aviation industry is looking for new design solutions in the field of designing modern passenger airliners. To ensure reliability and increase the service life of developed products can help polymer composite materials, which are already successfully used in the construction of a number of aircraft. This work is devoted to the urgent task of determining and optimizing the structural parameters of the carbon fiber wing load-bearing elements, taking into account rational reinforcement schemes. The wall thicknesses, layup patterns of unidirectional layers, the safety margins of the wing structural elements, taking into account the current operational loads for several angles of attack corresponding to different flight modes. The work is part of the methodology for designing a wing of polymer composite materials.

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At present, in order to increase the weight efficiency of parts and structures of promising aircraft and rocket-space vehicles, various types of additive technologies and topological optimization methods are being actively introduced. Their purpose is a significant reduction in time and financial costs in the manufacture and creation of fundamentally new geometric solutions. The article considers approaches to selecting the geometric parameters of the strength elements of the flight vehicle body made of a metal-matrix composite material based on VT6 titanium alloy, reinforced with a finely dispersed silicon carbide powder, which is produced by direct laser growth technology. On the basis of numerical simulation, the dependences of the metal-matrix composite material physicomechanical and thermophysical characteristics on the volume fraction of silicon carbide have been determined. It was found that the use of a metal-matrix composite material and the optimization of geometric parameters with adaptation to the direct laser growth technology allows reducing the weight of the strength element of the flight vehicle body by more than 30% (depending on the overall dimensions).

The passenger aircraft wing is an extremely complex object, especially in design, in which it is necessary to take into account many different factors, physical processes and phenomena both in individual areas of science and engineering, and at their junction. The main enlarged areas and issues that are solved during the development of wings include aerodynamics, aeroelasticity, strength, stability, and manufacturability. All this causes significant time and labour costs, especially at the stage of design calculations. In this connection, the urgent task of compiling a universal integrated methodology for designing a wing of polymer composite materials, which allows to accelerate and facilitate the selection of design parameters at the stage of outline design. The methodology being developed is tested on the passenger aircraft wing and takes into account the choice of the geometric shape of the wing, taking into account optimal aerodynamics and minimizing the operating loads, determining the position of the main power elements providing the necessary structural strength, as well as calculating the main structural parameters of individual polymer composite elements.