Computation of radiative heat fluxes with allowance for strong blowing for a space vehicle entering the Venusian atmosphere

The influence of radiative heat exchange on the motion of a space vehicle descending in a planet's atmosphere is investigated. In contrast to previously published studies, allowance is made for evaporation of the heat shield, the loss of its mass in flight, and strong blowing of evaporation products, which reduces the heat fluxes reaching the instrument module. The technique proposed is demonstrated via computing the entry and landing of a space vehicle on the Venusian surface by performing two maneuvers: aerocapture and subsequent aerobraking.