Calculated Results for the Transient Heating and Metaling Process of Glass Shields with Various Material Properties at the Stagnation Point of a Re- Entering ICBM.

摘要

A ballistic vehicle re-entering the earth's atmosphere at high speeds possesses a large amount of kinetic energy which is converted into aerodynamic heat. The terrific heat which surrounds the missile body requires that the body be coated with some type of material that can withstand this intense heat. Theoretical and experimental investigations have proved that certain type glasses make a very good protective covering for a re-entry vehicle. For the approximately spherical surface in the vicinity of the forward stag- nation point of an ICBM, this report presents calculated results pertaining to the transient heating and ablation processes of 26 homogeneous, opaque, and non- decomposing glass shields, each shield having a unique set of thermal properties. The effect of the thermal properties on the heating and ablation results was investigated by varying each thermal property over a practical range of values. A similar study of the effect of the thermal properties on the heating and ablation results has been made for an IRBM re-entry.