Heating analysis for a Lunar Transfer Vehicle at near-equilibrium flow conditions

Details Heating analysis for a Lunar Transfer Vehicle at near-equilibrium flow conditions Heating analysis for a Lunar Transfer Vehicle at near-equilibrium flow conditions

Jan 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993aiaa.meetz....g&link_type=abstract

AIAA, Aerospace Sciences Meeting and Exhibit, 31st, Reno, NV, Jan. 11-14, 1993, 13 p.

Statistics

Computation

Aerothermodynamics, Equilibrium Flow, Ferry Spacecraft, Lunar Orbits, Orbit Transfer Vehicles, Boundary Layers, Computational Grids, Convective Heat Transfer, Earth Orbital Environments, Radiative Heat Transfer, Upwind Schemes (Mathematics)

Scientific paper

A heating analysis for a 15.2 m diameter Lunar Transfer Vehicle (LTV) at 0 and 10.6 deg angle of attack for a nominal trajectory through the earth's atmosphere is described. The analysis utilizes the Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA) with thin-layer, Navier-Stokes, thermochemical nonequilibrium options. Radiative heating levels are calculated using the Langley Optimized RAdiative Nonequilibrium (LORAN) and the Non-EQuilibrium AIr Radiation (NEQAIR) codes. At peak heating, the shock layer is substantially in equilibrium. Comprehensive spatial and spectral grid convergence studies have been implemented to quantify grid effects on the convective and radiative heating levels. Axisymmetric tests including the coupled effects of radiative energy transfer show negligible change to the convective heating and a 20 percent reduction in the radiative heating.

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