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To avoid the ablation lag problem of pulsed plasma thrusters (PPTs), researchers have used laser ablation as a replacement for spark plug ignition and proposed a new laser-sustained PPT (LS-PPT) (Arai in AIAA J 17:634–640, 1979; Zhang in Theoretical, experimental, and simulation study of laser-sustained pulsed plasma thrusters. Graduate School of National University of Defense Technology, Changsha, 2014) Arai et al. (ISAS Rept 544, 1976; AIAA J 15(11):1656–1657, 1977), Arai and Karashimat (Aiaa J 2(2):572–579, 1979) studied the transient ablation problem of the PTFE ablative thermal protection layer on a blunt-body spacecraft during reentry under intense radiative and convective environments. They also elucidated the surface recession of the PTFE layer and the internal temperature and time evolution pattern of the molten layer. Finally, they constructed a phase change ablation model of a one-dimensional (1D) bilayer PTFE (Clark in J Heat Trans T ASME 94: 347–354, 1972), considering the transmittance of the crystalline and molten layers as well as the bulk absorption of radiant energy by the bilayer structure. Stechmann (Numerical analysis of transient Teflon ablation in pulsed plasma thrusters. Worcester Polytechnic Insitute, p 354, 2007) slightly modified the ablation model proposed by Arai et al. and used a volume fraction method to capture the phase change interface between the crystalline and molten layers and obtained the ablation pattern along the surface of the PTFE propellant in the PPT.

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Numerical Simulation of the Laser Ablation Process of PTFE Propellant

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  • 发表日期：

    2025年

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  • Jianjun Wu,
  • Jian Li,
  • Yuanzheng Zhao,
  • Yu Zhang

摘要

To avoid the ablation lag problem of pulsed plasma thrusters (PPTs), researchers have used laser ablation as a replacement for spark plug ignition and proposed a new laser-sustained PPT (LS-PPT) (Arai in AIAA J 17:634–640, 1979; Zhang in Theoretical, experimental, and simulation study of laser-sustained pulsed plasma thrusters. Graduate School of National University of Defense Technology, Changsha, 2014) Arai et al. (ISAS Rept 544, 1976; AIAA J 15(11):1656–1657, 1977), Arai and Karashimat (Aiaa J 2(2):572–579, 1979) studied the transient ablation problem of the PTFE ablative thermal protection layer on a blunt-body spacecraft during reentry under intense radiative and convective environments. They also elucidated the surface recession of the PTFE layer and the internal temperature and time evolution pattern of the molten layer. Finally, they constructed a phase change ablation model of a one-dimensional (1D) bilayer PTFE (Clark in J Heat Trans T ASME 94: 347–354, 1972), considering the transmittance of the crystalline and molten layers as well as the bulk absorption of radiant energy by the bilayer structure. Stechmann (Numerical analysis of transient Teflon ablation in pulsed plasma thrusters. Worcester Polytechnic Insitute, p 354, 2007) slightly modified the ablation model proposed by Arai et al. and used a volume fraction method to capture the phase change interface between the crystalline and molten layers and obtained the ablation pattern along the surface of the PTFE propellant in the PPT.