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<p>The Reusability Flight Experiment (ReFEx) is an experimental vehicle developed by the German Aerospace Center (DLR). It simulates the reentry of a reusable booster stage. After being launched with a VSB30 rocket to an altitude of about 139&#xa0;km, it will perform an autonomous reentry. This paper focuses on the analysis of the aerothermal loads during the ascending and reentry phases. Different approaches are applied and compared for investigating thermal heating: from a very conservative worst-case analysis to a fully coupled simulation via the DLR CoNF<InlineEquation ID="IEq1"> <InlineMediaObject> <ImageObject Color="BlackWhite" FileRef="12567_2025_620_Article_IEq1.gif" Format="GIF" Height="10" Rendition="HTML" Resolution="72" Type="Linedraw" Width="8" /> </InlineMediaObject> <EquationSource Format="TEX">\(^\text {2}\)</EquationSource> <EquationSource Format="MATHML"><math> <mmultiscripts> <mrow /> <mrow /> <mtext>2</mtext> </mmultiscripts> </math></EquationSource> </InlineEquation>aS<InlineEquation ID="IEq2"> <InlineMediaObject> <ImageObject Color="BlackWhite" FileRef="12567_2025_620_Article_IEq1.gif" Format="GIF" Height="10" Rendition="HTML" Resolution="72" Type="Linedraw" Width="8" /> </InlineMediaObject> <EquationSource Format="TEX">\(^\text {2}\)</EquationSource> <EquationSource Format="MATHML"><math> <mmultiscripts> <mrow /> <mrow /> <mtext>2</mtext> </mmultiscripts> </math></EquationSource> </InlineEquation> tool chain (Coupled Numerical Fluid Flight Mechanic And Structure Simulation). In the context of a numerical flight test, CoNF<InlineEquation ID="IEq3"> <InlineMediaObject> <ImageObject Color="BlackWhite" FileRef="12567_2025_620_Article_IEq1.gif" Format="GIF" Height="10" Rendition="HTML" Resolution="72" Type="Linedraw" Width="8" /> </InlineMediaObject> <EquationSource Format="TEX">\(^\text {2}\)</EquationSource> <EquationSource Format="MATHML"><math> <mmultiscripts> <mrow /> <mrow /> <mtext>2</mtext> </mmultiscripts> </math></EquationSource> </InlineEquation>aS<InlineEquation ID="IEq4"> <InlineMediaObject> <ImageObject Color="BlackWhite" FileRef="12567_2025_620_Article_IEq1.gif" Format="GIF" Height="10" Rendition="HTML" Resolution="72" Type="Linedraw" Width="8" /> </InlineMediaObject> <EquationSource Format="TEX">\(^\text {2}\)</EquationSource> <EquationSource Format="MATHML"><math> <mmultiscripts> <mrow /> <mrow /> <mtext>2</mtext> </mmultiscripts> </math></EquationSource> </InlineEquation> is an integrated fluid–structure interacting coupled process chain, allowing the combination of various flow solvers, such as DLR Tau, with commercially available structural solver codes, as well as simple heating evaluations. The focus of the presented work is the heat conduction within the structure induced by the surrounding atmosphere during launch and reentry on the experimental ReFEx vehicle itself, excluding the sounding rocket motor.</p>

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Aerothermal loads analysis of ReFEx by coupled fluid–structure simulations

  • 期刊论文

  • 出版模式：

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  • 发表日期：

    2025年5月10日

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  • Marius Franze,
  • Viola Wartemann,
  • Clemens Merrem,
  • Henning Elsäßer,
  • Tobias Ruhe,
  • Thino Eggers,
  • Hendrik Weihs

摘要

The Reusability Flight Experiment (ReFEx) is an experimental vehicle developed by the German Aerospace Center (DLR). It simulates the reentry of a reusable booster stage. After being launched with a VSB30 rocket to an altitude of about 139 km, it will perform an autonomous reentry. This paper focuses on the analysis of the aerothermal loads during the ascending and reentry phases. Different approaches are applied and compared for investigating thermal heating: from a very conservative worst-case analysis to a fully coupled simulation via the DLR CoNF \(^\text {2}\) 2 aS \(^\text {2}\) 2 tool chain (Coupled Numerical Fluid Flight Mechanic And Structure Simulation). In the context of a numerical flight test, CoNF \(^\text {2}\) 2 aS \(^\text {2}\) 2 is an integrated fluid–structure interacting coupled process chain, allowing the combination of various flow solvers, such as DLR Tau, with commercially available structural solver codes, as well as simple heating evaluations. The focus of the presented work is the heat conduction within the structure induced by the surrounding atmosphere during launch and reentry on the experimental ReFEx vehicle itself, excluding the sounding rocket motor.