Scholarlink

<p>This work presents the <Emphasis FontCategory="NonProportional">BLIZZARD</Emphasis> CFD module developed in the scope of the implementation of the high-fidelity branch of the <Emphasis FontCategory="NonProportional">PAMPERO</Emphasis> spacecraft-oriented re-entry tool. First, the Riemann solver, the immersed boundary method, and the adaptive mesh refinement of <Emphasis FontCategory="NonProportional">BLIZZARD</Emphasis> are briefly detailed. The mass loss generated by the chosen immersed boundary method is investigated on a sphere and a satellite case. Then, the results of the simulation of static hypersonic wind tunnel test cases are presented. A part of a cube’s trajectory computed by the modified Newton theory (method used in spacecraft-oriented tools) is computed using the pressure loads of <Emphasis FontCategory="NonProportional">BLIZZARD</Emphasis>. The impact of the fluid modeling on the stability of the object is shown. Finally, the surface pressure distribution and the aerodynamic coefficients obtained with a body-fitted CFD reference code, the modified Newtonian theory and <Emphasis FontCategory="NonProportional">BLIZZARD</Emphasis> on a satellite case are compared. <Emphasis FontCategory="NonProportional">BLIZZARD</Emphasis> shows major improvement compared to the modified Newtonian theory.</p>

错误：搜索内容不能为空，请输入英文关键词
错误：关键词超出字数限制，请精简
高级检索

Pampero HiFi: improvements in aerodynamic modeling of a spacecraft-oriented destructive re-entry code

  • 期刊论文

  • 出版模式：

    开放获取

  • 发表日期：

    2025年8月19日

查看全文
  • Valentin Ledermann,
  • Iko Midani,
  • Eddy Constant,
  • Pierre Van Hauwert,
  • Martin Spel,
  • Laurent Stainier,
  • Julien Annaloro,
  • Stéphane Galera

摘要

This work presents the BLIZZARD CFD module developed in the scope of the implementation of the high-fidelity branch of the PAMPERO spacecraft-oriented re-entry tool. First, the Riemann solver, the immersed boundary method, and the adaptive mesh refinement of BLIZZARD are briefly detailed. The mass loss generated by the chosen immersed boundary method is investigated on a sphere and a satellite case. Then, the results of the simulation of static hypersonic wind tunnel test cases are presented. A part of a cube’s trajectory computed by the modified Newton theory (method used in spacecraft-oriented tools) is computed using the pressure loads of BLIZZARD. The impact of the fluid modeling on the stability of the object is shown. Finally, the surface pressure distribution and the aerodynamic coefficients obtained with a body-fitted CFD reference code, the modified Newtonian theory and BLIZZARD on a satellite case are compared. BLIZZARD shows major improvement compared to the modified Newtonian theory.