Thermal analysis of the thermal protection system for the re-entry vehicle

Ohtake, Kunihiko

doi:10.1016/s0045-7825(97)00153-9

Cited by 8 publications

(2 citation statements)

References 3 publications

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“…He has considered the air as a perfect gas model and analyses are based on laminar flow conditions. Ohtake [17] have studied the thermal analysis of thermal protection system for the re-entry vehicle. He has performed flow and structure analysis using Finite element methods.…”

Section: Literature Surveymentioning

confidence: 99%

Numerical Simulation of the Orion CEV Reentry Vehicle

Patel

Venkatasubbaiah

2015

J. Aerosp. Eng.

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Aerothermodynamics analysis of Orion Crew Exploration Vehicle (CEV) re-entry vehicle at high altitude and low altitude has been studied numerically. At high altitude in the rarefied flow regime non-continuum technique such as Direct Simulation Monte Carlo (DSMC) method is used to solve the Boltzmann equation of kinetic theory. Results are reported at different altitudes in the rarefied regime for ideal gas and real gas model. The effects of nose radius and free stream velocity are presented. The estimation of bow shock strength and peak heat flux is higher for ideal gas compared to real gas model. The flow field characteristics have shown significant change with increase in free stream velocity. The Reynolds averaged Navier-stokes methods along with sparart-Allmaras turbulent model are used to compute flow field in high density region at low altitude. Effect of the free stream velocity and altitude at high density on flow field and heat flux generation on surface of re-entry vehicle studied. Present results are matching very well with the experimental results available from the literature for both regime.

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Section: Literature Surveymentioning

confidence: 99%

Numerical Simulation of the Orion CEV Reentry Vehicle

Patel

Venkatasubbaiah

2015

J. Aerosp. Eng.

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“…1 (Pezzella, 2012). Such vehicles include hypervelocity projectiles, reentry vehicles (Ohtake, 1998;Huang et al, 2012b), and hypersonic aircraft (Huang et al, 2011). Fig.…”

Section: Introductionmentioning

confidence: 99%

A survey of drag and heat reduction in supersonic flows by a counterflowing jet and its combinations

Huang

2015

J. Zhejiang Univ. Sci. A

115

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Drag reduction and thermal protection is very important for hypersonic vehicles, and a counterflowing jet and its combinations is one of the most promising drag and heat release reduction strategies. In the current survey, research progress on the drag and heat release reduction induced by a counterflowing jet and its combinations is summarized. Three combinatorial configurations are considered, namely the combination of the counterflowing jet and a forward-facing cavity, the combination of the counterflowing jet and an aerospike, and the combination of the counterflowing jet and energy deposition. In conclusion, some recommendations are provided, especially for jet instability protection, for the tradeoff between drag and heat release reductions, and for the critical points for the operational and geometric parameters in the flow mode transition.

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