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The simulation results of the thermal stabilization of polyacrylonitrile pressed organomorphic frame samples are presented. The local temperature maximum in the sample depth due to an exothermic oxidation reaction was confirmed. The possibility of the avalanche exothermic effect, which can lead to a sample burnout, is demonstrated theoretically. The analysis of the influence of the initial fiber oxidation degree on the sample temperature state have been carried out.

Due to an unintentional misunderstanding between the authors and the guest editors of the conference, the above-mentioned article has been accidentally published in Web of Conferences. The publisher, the guest editors and the authors have therefore commonly decided to remove this article. Request approved on February 19, 2020.

Currently, the task of designing large structures of space antennas is becoming increasingly important due to active research and development in the area of creating remote sensing and communication satellites. Designing such structures is a complicated task due to geometric features, a large number of joints, compactness requirements, as well as operating conditions of the outer space. These factors require special methods for assessing the workability of these structures. This paper presents the results of simulation and experimental studies aimed at creating transformable antenna reflectors. The results of choosing general structural layouts are considered. It is noted that the main reason for the reflector shape distortion is non-uniform heating by the solar radiation and radiation fluxes coming from the Earth. The paper presents the results of numerical modeling of temperature and stress-strain state of transformable antenna reflectors from metallic mesh sheet meeting the requirements for operating on the geostationary orbit.

The simulation results of the thermal state of a cylindrical workpiece made of composite material and exposed to the action of microwave radiation are presented. The mathematical model of a workpiece allows the analysis of the interconnected thermal and electromagnetic processes in the equipment operating area, and also takes into account the exothermic effect associated with the curing of the polymer matrix.

Due to an unintentional misunderstanding between the authors and the guest editors of the conference, the above-mentioned article has been accidentally published in Web of Conferences. The publisher, the guest editors and the authors have therefore commonly decided to remove this article. Request approved on February 19, 2020.

The paper presents methodology and results of tests conducted for porous carbon ceramic specimens on a high-temperature gas dynamic facility to simulate real operating conditions for heat shields. The structure of the materials before and after tests is compared.

Physical properties of composite materials can be improved by carbon nanotubes (CNTs). However, the thermal resistance between the polymer matrix and CNT at nanoscale can result in lower thermal conductivity. The paper analyses influence of CNTs’ diameter and length on effective thermal conductivity in epoxy-based composites. It analyses the effect of the diameters, lengths and volumetric fraction of CNT on composites’ thermal conductivity.

The strikes of the meteoroids represent a serious danger for transformable space structures. Multilayer plates and shells made of hybrid composite materials can be effectively used for protection and thermal control of such structures. The results of the analysis of the thermal regime and shock resistance of a multilayer structure flying in a circular orbit 400 km high are presented.

The operating temperatures for the current aerospace heat shield materials exceed 2000 K [1], which makes their experimental testing a complex and expensive issue requiring specialized testing facilities capable to obtain the temperature level in question. In most cases, the thermal tests of the materials samples and thermal shield elements are conducted on the radiative heating test facilities. Generally, these facilities use tungsten halogen lamps (THL) [2, 3]. However, maximal operating temperatures for such type facilities do not exceed 1500 K due to the tungsten-halogen cycle disruption. The main challenge is to comply with the bulbs thermal conditions, which must remain below 1270 K [1]. This paper outlines the layout of the working area of the THL radiative heating facility, where the test specimen temperature is increased to 2100 K due to the compressed air flow over the bulbs, which for a considerable part solves the problem of the thermal behavior simulation.

This paper is dedicated to the numerical simulation of the gas-phase 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 paper is concerned with the theoretical and numerical characterization of the thermal conductivity of porous carbon ceramic materials. The material structure models are created based on 3D computer tomography (CT) images. The temperature functions of the molecular and effective thermal conductivity for the porous carbon-ceramic material were obtained. It was investigated, whether a simplified model could be used to estimate the thermal conductivity. The thermal conductivity data obtained with the computer tomography method and with the proposed simplified model are compared.

The article presents models representative volume element of the porous carbon-ceramic material. Simulating of heat transfer process in a representative volume element is carried out and thermal characteristics of material are determined by a settlement way. Influence of characteristics of material structure – its porosity and type of reinforcement – on values of heat-physical characteristics is investigated. It is shown that in the field of high temperatures (more than 1500 T) the defining role in the course of heat transfer in high-porous (Р> 40%) materials belongs to radiation heat exchange in a pores.

In this paper gas dynamic numerical modelling of leading edge flow is presented and thermal loading parameters are determined. Numerical modelling of combined radiative and conductive heat transfer of the wing edge is carried out, thermal state of structure is given and the results are analyzed.