Heat Transfer Through Cryogenic Propellant Tank Insulation During Ground-Hold Conditions

摘要

A theroetical formulation is presented for predicting transient(leading to steady state)heat-transfer characteris- tics through the thermal insulation of cryogenic rocket propellant tanks. Only the cylindrical sides of the problems tanks are studies while the rocket is on the launch pad in a holding condition. Effects of direct solar radiation, Earth-reflected/emitted radiation, and wind velocity are considered for estimation of heat loads to the propellants.