Modification of superalloy honeycomb thermal protection system

Abstract

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.

Thermal conductivity prediction of aerogel considering heat treatment effect and the application to a TPS of long endurance HFVs

“…For a hypersonic flight vehicle (HFV), the thermal protection system (TPS) is such important as it protects the main structure of the HFV from being destroyed by harsh thermal environment, especially for the HFVs of long endurance (Liang et al , 2023). Among the various types of TPSs (Sziroczak and Smith, 2016; Uyanna and Najafi, 2020; Brodzik, 2021; Le et al , 2021), the simplest and most classical one is a multilayer structure composed of a heat resistant layer and a thermal insulation layer fixed over the main metal structure of the flight vehicle (Dai et al , 2022). For this kind of TPS, the ability to prevent heat transfer is determined by the material used for the thermal insulation layer.…”

Evaluation of Fay and Riddell formula under hypersonic flight conditions

“…In addition, the dissociated species may recombine and release heat onto the surface depending on the surface catalycity. To protect hypersonic reentry vehicles from aerothermal heating, designing thermal protection systems (TPS) has been essential (Rivier et al , 2019; Brodzik, 2020). The TPS design, such as the material and thickness, is determined by the total amount of heat load and the maximum heat flux under hypersonic flight conditions (Meseguer et al , 2012; Yang et al , 2021).…”