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Journal of Projectiles, Rockets, Missiles and Guidance >

2019 , Vol. 39 >Issue 5: 127 - 130

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2019.05.030

Prediction Ablative Shape of C/C Nosetip

  • ZHAO Lining ,
  • MENG Jun ,
  • ZHOU Peipei
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  • China Academy of Aerospace Aerodynamics, Beijing 100074, China

Received date: 2018-08-15

  Online published: 2025-05-12

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Abstract

Approximate engineering codes have been developed to predict the C/C nosetip ablative shape change during reentry process.A rapid engineering aero-heating calculation is established by axisymmetric analog method, and the ablative velocity of C/C nosetip is considered by solving the mass and chemical conservation equations of boundary.Then, the shape of C/C nosetip in fluid zone is changed by grid remeshing.At last, this engineering codes is appoved with C/C nosetip ablative experiment, the result show that it can predict the ablative shape change effetvely.

Key words： hypersonic; ablation; aeroheating; thermal protection

Cite this article

ZHAO Lining , MENG Jun , ZHOU Peipei . Prediction Ablative Shape of C/C Nosetip[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2019 , 39(5) : 127 -130 . DOI: 10.15892/j.cnki.djzdxb.2019.05.030

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