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A Novel Plasma Preheating Test Device for Replicating Planetary Reentry Surface Temperatures in Hypersonic Impulse Facilities
A Novel Plasma Preheating Test Device for Replicating Planetary Reentry Surface Temperatures in Hypersonic Impulse Facilities
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机译：一种用于复制高超音速脉冲设施中行星折返表面温度的新型等离子体预热测试装置
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#$%^&*AU2019205004B120201001.pdf#####Abstract A new technique for preheating axisymmetric samples of heat shield material has been demonstrated through this work. Future applications for the technique are expected to be found in expansion tube facilities that can simulate the true flow energy under re-entry conditions. The relevance of this work sprung from the desire to find an economically feasible solution for studying thermally coupled hypersonic boundary layers for re-entry probes using shock and expansion wind tunnels. This aeroheating innovative work has been able to integrate the advantages of the high-enthalpy impulse facilities and expansion/shock tunnels for ablation studies in a hypersonic re-entry flow-field using a blunt-body. Hopefully, this research work will open a gateway that will provide extremely useful contributions to improving aeroheating test reliability in Hypersonic wind tunnels and impulsive facilities around the world. The technique is not limited to short duration facilities such as expansion tube. It has the potential to be applied to longer duration facility like shock tunnels and conventional blow-down wind tunnels. I shall be willing to work with those who have genuine interest for aerospace re-entry research. It can be individuals, companies, organisations, or international partnerships. This work contains the scientific ideas that work. The applications and findings have a lot to do with the high enthalpy and plasmatron facilities of the European Space Agency (ESA), and the Arc-Jet facilities of the National Aeronautics and Space Administration (NASA) Ames.
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