Abstract
Radiative aerothermodynamics of large scale space vehicle of segmental-conical shape is investigated for Earth entry trajectory with orbital velocity at zero and non-zero angles of attack. Brief description of used radiative gasdynamic model of physically and chemically nonequilibrium, viscous, heat conductive and radiation gas of complex chemical composition is presented. Examples of radiative gasdynamic interaction for two-dimensional axysimmetric flow are presented. It is shown that coupling of radiation and gasdynamics for the segmental-conical space vehicle significant for high altitude part of trajectory. Results of three dimensional calculations of radiative heating of surface of segmental-conical space vehicle under angle of attack D =24 0 are presented. Calculations were performed with the use of multigroup spectral model taking into account most significant radiative mechanisms of absorption and emission.
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