THE CASCADE PHASE CHANGE HEATING STORAGE

This paper discusses the prospects for using a cascade phase change heating storage tank to reduce heat losses and increase efficiency during the operation of space heating and do-mestic hot water.Авторы выражают благодарность Правительству Московской области за финансирование проекта в рамках гранта Губернатора Московской области по договору №33 от 24.07.2020

DEVELOPMENT OF A HARDWARE-SOFTWARE COMPLEX FOR STUDYING PHASE TRANSITIONS OF SUBSTANCES DURING THE COOLING

The work is devoted to the development of a hardware-software complex for studying the phase transitions of substances during cooling and calculating the main physical and chemical characteristics of substances

Synthesis and Research Phase Change Materials Based on a Hydrate Salt Zn(NO3)2·6H2O Composite

This work is devoted to the synthesis of heat storage materials based on zinc nitrate hexahydrate, the study of their thermophysical characteristics and the study of thermal stability in the cyclic heating/cooling mode.Данные исследования выполнены при поддержке Фонда содействия развитию малых форм предприятий в научно-технической сфере (FASIE)

Thermal analysis of advanced ceramic coating on carbon/carbon substrates for aerospace re-entry re-usable structures

Aim of the work is to describe a novel coating process based on the Al-Oxide ceramic varnish ‘Pyropaint’ applied on a spacecraft Thermal Protection System for re-entry application. The proposed treatment is intended to preserve the thermo-mechanical properties of a Carbon/Carbon substrate from the detrimental space environment conditions, such as LEO thermal cycles, outgassing due to ultra-high vacuum, and Atomic Oxygen / UV irradiation. In order to enhance the coating performance, the used varnish is enriched with Si-Oxide nanoparticles in different weight percentage. The first step is to analyze the coefficient of thermal expansion (CTE) by dilatometric measurement in order to evaluate the thermal stress of both substrate and coating layer at high temperatures. Particular emphasis is devoted to study the effect of the coating/substrate adhesion, which may result in anomalous mechanical behavior. After thermal conditioning, the several specimens under test are investigated by full microscopy analysis using SEM/EDX techniques, then the experimental results are compared each other. The present study paves the way for the future development of advanced structural spacecraft panels as well as of re-usable re-entry systems

Thermal analysis of advanced plate structures based on ceramic coating on carbon/carbon substrates for aerospace re-entry re-usable systems

The development of reusable launch vehicles (RLV) must include a significant reduction of the payload transportation costs. One of the most expensive systems for any RLV is the thermal protection system (TPS), which protects the vehicle from the high thermal loads during re-entry. The reusability and on-orbit environment are the key parameters for the design of TPS and its materials. Aim of the work is to analyze a novel coating process based on the alumina base coating applied on a TPS for re-entry application. The proposed treatment is due to preserve the thermo-mechanical properties of a Carbon/Carbon substrate from the detrimental space environment conditions, such as LEO thermal cycles, outgassing due to ultra-high vacuum, Atomic Oxygen and UV irradiation. The experimental measurement of the coefficient of thermal expansion (CTE) is performed in order to evaluate the thermal stress and performance of both the substrate and coating layer. Particular emphasis is devoted to the study of the effect of coating/substrate adhesion, which may result in anomalous mechanical behavior. By the use of the inverse method heat capacity and thermal conductivity are analysed. A robust numerical approach, such this inverse method, is one of the best for these problems as many parameters concur for the determination of properties. Such approach permits to perform the parametric and structural identification of the model. These procedures are presented including both experimental investigation and methodical numerical aspects. Special test equipment and the regularizing algorithm for solving the ill-posed inverse heat conduction problem are described. Such approach provides estimating of thermal properties of different types of Carbon/Carbon substrate coating. After thermal conditioning the integrity of the coating and the substrate will be investigated by full microscopy analysis using SEM/EDX techniques. The experimental results are implemented in numerical simulations in order to foresee the overall performance of the material

Thermo-mechanical characterization of carbon-based ceramic foams for high temperature space application

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 tural 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 SiCfoam 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 , heat capacity over a wide range of temperatures, thus establishing the required material behavior for potential use in spacecraft TPS

Thermal analysis of advanced plate structures based on ceramic coating on carbon/carbon substrates for aerospace Re-Entry Re-Useable systems

The development of reusable launch vehicles (RLV) must include a significant reduction of the payload transportation costs. One of the most expensive components of a RLV is the thermal protection system (TPS), which preserves the spacecraft from the high thermal loads during re-entry. Reusability and on-orbit environment are key parameters in TPS design, mainly as far as the adopted materials are concerned. Aim of the work is to analyze a novel TPS concept, proposing an hybrid multiscale ceramic coating - i.e., alumina-based varnish enriched by silica nanoparticles - to be applied on Carbon/Carbon (C/C) plates. The treatment is aimed at preserving the thermo-mechanical properties of the ceramic substrate from the detrimental space environment conditions, such as LEO thermal cycles, outgassing due to ultra-high vacuum, as well as Atomic Oxygen/UV irradiation. Experimental measurements of the coefficient of thermal expansion (CTE) are performed in order to evaluate the thermal stress and performance of both substrate and coating layer. Particular emphasis is devoted to evaluate the effect of coating/substrate adhesion, which may result in anomalous mechanical behavior. By the use of a robust numerical technique, known as the inverse method, heat capacity and thermal conductivity are analyzed; such approach is particularly suited to address these kind of problems, as a number of physical parameters concur for a reliable determination of material properties. The special test equipment and the regularizing algorithm for solving the heat conduction problem are described. After thermal conditioning, the integrity of coating and substrate is investigated by full morphological analysis using SEM/EDX techniques