Purpose Paper aims to present problem of aerodynamic heating of a metallic heat shield. The key elements of this construction are metallic layers of superalloy honeycomb, which significantly increase the structure’s resistance to impact. Paper describes the problem of influence of damage size on increase of thermal load. Design/methodology/approach Numerical analysis was performed in a non-commercial environment FreeFem++ using finite element method, and its results were compared with the results given in the literature. Findings In thermal protection system, a modification was used to delay increase in temperature on the underlying structure as well as to reduce its maximum value. Originality/value In the further part of the paper, selected insulation material was modified by adding additional conductive material.
Original scientific paper https://doi.org/10.2298/TSCI19S4025BPaper presents the problem of heating the damaged insulation of an orbiter. Changes of the insulation's thermal properties, made by adding conductive material of high value of specific heat in a form of a dope to the protective layer, were examined. An iterative algorithm determining a variable of dope concentration in the material was developed. Insulating material LI900 was used for calculations. Determination of distribution of conductive material concentration was made for materials which, after verification, demonstrated the most beneficial effect on protective properties of the modified insulation layer. Change of properties was to enable time extension of the LI900 insulation tile heating up to the maximal temperature and, additionally, to lowering this temperature.
The content of the article concerns the analysis of heat insulating material of the thermal protection system, which is related to aerodynamic heating during atmospheric reentry by spacecraft. The example of the heat flux distribution as a function of flight time for analysis is used. The purpose of the article is to investigate the effect on the results of the new material of model with relatively high thermal conductivity coefficient across the isolating tile. It is considered that it may allow to compensate the temperature on the surface of underlying structure. The article contains the comparison of two types of thermal analysis of selected insulating tile models. The first case assumed that the models contain only three layers, e.g. insulation, strain isolator pad and underlying structure. In the second analysis, calculations are based on models consisting of four layers. Due to the good thermal properties as the additional material titanium alloy is selected. All analyses take into account two types of models: undamaged and damaged tiles. The conclusions contain graphs of maximum temperature distribution in function of time on the surfaces of selected layers. The results allowed to determine the temperature difference calculated on the basis of the considered of both cases.
The paper presents the problem of aerodynamic heating of a damaged Alumina Enhanced Thermal Barrier AETB. At the given minimum dimensions of the cover layers, the impact of damage size on the temperature increase on the skin surface was analyzed. The aim of the study was to determine the temperature curve as a function of the size of damage. In the calculations FreeFem ++ non-commercial environment was used.
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