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26. Numerical Solving of Radiation Geometrical Inverse Problem.

Author

Nenarokomov, Aleksey V., Chebakov, Evgeniy V., Reviznikov, Dmitry L., and Krainova, Irina V.

Subjects
*INVERSE problems, *HEAT flux, *RADIATION, *SPACE vehicles, *ARTIFICIAL satellite attitude control systems
Abstract

Compared to large satellites, on-board electronics of microsatellites, such as microprocessors, are more exposed to radiation and high-energy particles. This problem can lead to single-event upsets, which might generate false commands such as thruster firing or switching heaters on or off. In some cases, these upsets cause the loss of a spacecraft orientation and endanger the whole mission. This makes important to elaborate a reliable and robust attitude determination system which will enable us to correct and recover the spacecraft's attitude after a failure. It must have a simple design, low mass, and power consumption. In this paper we suggest a new method of determination of spacecraft's attitude based on heat fluxes analysis that could form the basis of such a system. In order to develop it we have to solve two inverse problems sequentially. The first inverse problem is the estimating of heat fluxes absorbed by the spacecraft surface. The second one is to determine the spacecraft's attitude based on the estimated values of radiative heat fluxes. This paper is dedicated to the solution of the second inverse problem. [ABSTRACT FROM AUTHOR]

Published
2024
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37. Thermo-mechanical characterization of carbon-based ceramic foams for high temperature space application

Author

Albano, M., Nenarokomov, A. V., Pastore, R., Budnik, S. A., Delfini, A., Alifanov, O. M., Marchetti, M., Morzhukhina, A. V., Titov, D. M., Santoni, F., Piergentili, F., and Netelev, A. V.

Subjects
thermal protection, inverse problems, Mechanics of Materials, carbon foam, SiC foam, Physical and Theoretical Chemistry, Condensed Matter Physics
Abstract

The successful development of aerospace reusable launch vehicles (RLV) require to realize effective thermal protection systems (TPS) for preserving spacecraft integrity from the severe thermal loads during re-entry phase. To such an aim, due to the need of reducing payload transportation costs, applied research is driven towards lightweight materials with advanced thermo-mechanical properties. Space TPS are often based on sandwich structures, where the core material has the main function of thermal insulation. Ceramic porous materials, as carbon (C) and silicon carbide (SiC) foams, represent ideal candidates for application as structural TPS component, thanks to both low density and significant thermal stability at very high temperatures. The paper presents a joint experimental study of carbon-based ceramic foams proposed as sandwich’s core for TPS design. A full thermal characterization of commercial C- and SiC-foam materials is reported, including measurements of thermo-mechanical combined stress, temperature-induced outgassing behavior and heat transfer properties. These latter, in particular, are studied by means of a robust numerical technique, known as the inverse method, which allows to evaluate materials thermal conductivity and heat capacity over a wide range of temperatures, thus establishing the required material behavior for potential use in spacecraft TPS.

Published
2022

41. Estimation of the Thermophysical Properties of C/C Plates with Ceramic Nanocoating at Different SiO2Filling for Aerospace Applications

Author

Morzhukhina, A. V., Alifanov, O. M., Budnik, S. A., Nenarokomov, A. V., Titov, D. M., Delfini, A., Pastore, R., Santoni, F., Albano, M., and Marchetti, M.

Abstract

In aerospace industrial and commercial scenario, the reusable launch vehicles (RLV) evolution works constantly toward the lowering of payload conveyance expenses. The thermal protection system (TPS) preserves the integrity of the space vehicle surfaces exposed to huge thermal shock during the re-entry phase: its advanced design and manufacturing, aimed at both reusing and withstanding harsh space environment, result in increasing the production and maintenance charges. The present study introduces a cost-saving concept of TPS component made of carbon/carbon (C/C) tiles coated by a commercial refractory varnish reinforced with ceramic nanoparticles. Using a reliable computing method, known as inverse method, the thermophysical properties such as heat capacity and thermal conductivity of the manufactured materials are assessed in a broad range of temperatures, with the input aid of an in-house developed experimental setup. The described technique is especially suited for approaching such kind of issues, thanks to the capability of taking into account several physical variables simultaneously, with the aim of gaining a robust knowledge of materials’ thermal behavior for potential use in spacecraft TPS.

Published
2023
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44. Thermo-mechanical characterization of carbon-based ceramic foams for high temperature space application.

Author

ALBANO, MARTA, NENAROKOMOV, ALEKSEY V., PASTORE, ROBERTO, BUDNIK, SERGEY A., DELFINI, ANDREA, ALIFANOV, OLEG M., MARCHETTI, MARIO, MORZHUKHINA, ALENA V., TITOV, DMITRY M., SANTONI, FABIO, PIERGENTILI, FABRIZIO, and NETELEV, ANDREY V.

Subjects
*SANDWICH construction (Materials), *FOAM, *HIGH temperatures, *THERMAL conductivity, *POROUS materials, *CARBON foams
Abstract

The successful development of aerospace reusable launch vehicles (RLV) require to realize effective thermal protection systems (TPS) for preserving spacecraft integrity from the severe thermal loads during re-entry phase. To such an aim, due to the need of reducing payload transportation costs, applied research is driven towards lightweight materials with advanced thermo-mechanical properties. Space TPS are often based on sandwich structures, where the core material has the main function of thermal insulation. Ceramic porous materials, as carbon (C) and silicon carbide (SiC) foams, represent ideal candidates for application as structural TPS component, thanks to both low density and significant thermal stability at very high temperatures. The paper presents a joint experimental study of carbon-based ceramic foams proposed as sandwich’s core for TPS design. A full thermal characterization of commercial C- and SiC-foam materials is reported, including measurements of thermo-mechanical combined stress, temperature-induced outgassing behavior and heat transfer properties. These latter, in particular, are studied by means of a robust numerical technique, known as the inverse method, which allows to evaluate materials thermal conductivity and heat capacity over a wide range of temperatures, thus establishing the required material behavior for potential use in spacecraft TPS. [ABSTRACT FROM AUTHOR]

Published
2022
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