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Abstract

Studies of the thermal protection requirements of Venusian and Jovian atmos pheric descent probes have identified a need for data on the performance of in sulations in a high pressure, high temperature environment. A test program was conducted to measure the thermal conductivity of several materials in CO₂ and He by the flat guarded hot plate method. Five materials were first evaluated to temperatures of 250°C and pressures of 30 atmospheres of CO₂ and then screened. The remaining two materials, FA Fiberglass and Min-K TE 1400, were then tested to 350°C and 125 atmospheres of CO₂. The Min-K was also tested over a similar pressure and temperature range in He. The measured thermal conductivities show a significant pressure effect, with a marked increase be tween 30 and 55 atmospheres of CO₂.

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References

Wilbers, O.J. , Schelden, B.G. , and Conti, J.C. , "Martian Soft Lander Insulation Study," AIAA Progress in Astronautics and Aeronautics, 24 (1971).

Crowley, D.P. and Levine, P. , "Insulator Testing Under Venus Environmental Conditions," Avco Systems Division, AIAA Paper 72-368 (April 1972 ).

Barger, A.R. , "Atmospheric Models for Use in Entry and Descent Studies of a Multiple Probe Mission, Venus Planetary Environmental Models," Part I, MCR-69-488 , Martin Marietta Corp., Denver, CO (September 1969).

Tye, R.P. , "Effects of Edge Losses on the Thermal Conductivity of Thermal Insulations at High Temperatures," Rev. Int. Hautes Temper. et Refract. , 7, 308-312 (1970).

American Society for Testing and Materials Standard C177-71 (1971).

Thermal Conductivity of Insulations in Planetary Atmospheric Environments

Abstract

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