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This report is a continuation of a study of the effects of internal heat transfer on the temperature of hollow spacecraft and the requirements for thermal modeling. Considered herein is the effect of internal heat transfer by radiation on the temperature distribution. The equation governing the heat transfer of a spherical shell exposed to parallel radiation is derived; conduction and radiation are considered. The general equation is simplified by assuming steady state, and a numerical method is given to solve the steady state equation. A computer program is described which employs the method. Solutions of the steady state equation are graphically presented and discussed. The requirements for temperature preservation in thermal modeling are derived. The possibility of thermal modeling without temperature preservation is discussed. It is observed that for an inside emissivity to outside emissivity ratio greater than one, the requirement for duplication of the other dimensionless ratio can be relaxed.