2008
DOI: 10.2514/1.30442
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Spectroscopic Analysis of Titan Atmospheric Plasmas

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Cited by 5 publications
(3 citation statements)
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“…It has also been predicted that, below an entry speed of about 7 km/s, nearly all of the radiative heating is due to the CN violet (B 2 Σ + → X 2 Σ + ) and red (A 2 Π → X 2 Σ + ) bands [3]. An accurate estimate of this radiative heat flux is therefore necessary for a proper design of the thermal protection system (TPS) [4][5][6][7][8]. Moreover, the radiation emission is strongly dependent on the non-equilibrium conditions present behind the shock wave, which requires implementation of thermochemical models for accurate prediction of the emitted radiation.…”
Section: Introductionmentioning
confidence: 99%
“…It has also been predicted that, below an entry speed of about 7 km/s, nearly all of the radiative heating is due to the CN violet (B 2 Σ + → X 2 Σ + ) and red (A 2 Π → X 2 Σ + ) bands [3]. An accurate estimate of this radiative heat flux is therefore necessary for a proper design of the thermal protection system (TPS) [4][5][6][7][8]. Moreover, the radiation emission is strongly dependent on the non-equilibrium conditions present behind the shock wave, which requires implementation of thermochemical models for accurate prediction of the emitted radiation.…”
Section: Introductionmentioning
confidence: 99%
“…A comparison of our rotational and vibrational temperatures for the CN violet system with those obtained by Labracherie [12] in a free piston wind tunnel and reflected shock has been made and shows good agreement for the rotational temperature. Emission spectroscopy measurements carried out at the VKI (Von kàrmàn Institute) Minitorch facility, which is an inductively coupled plasma (ICP) wind tunnel, have recently been presented by Playez and Fletcher [13] for the spectroscopic analysis of Titan atmospheric plasmas. Unfortunately, they did not explore the CH and NH spectra for comparison purposes.…”
Section: Introductionmentioning
confidence: 99%
“…The study for high-temperature aerospace applications on hypersonic vehicles being a thermal protection system has significantly increased in recent years due to their excellent and unique property [1]. Both ZrB 2 and HfB 2 have extremely high melting points (3245 and 3380°C, respectively) and relatively high thermal conductivities, making them potentially enabling for shape stable leading edge and surfaces components for which extreme aero thermal heating rates lead to the failure of conventional aerospace materials [2]. These components will reach temperature that may exceed 2000°C during service.…”
Section: Introductionmentioning
confidence: 99%