Aerothermal Tests of the Space Shuttle External Tank Insulating Material.

摘要

Aerothermal tests were conducted to evaluate the performance of a candidate material for the insulation of the Space Shuttle external tank. Material samples were exposed to total temperatures and heating rates designed to simulate those experienced during the ascent phase of the Shuttle trajectory. These conditions were obtained in the VKF Hypersonic Wind Tunnel (C),where a large wedge was used to hold the sample and the wedge angle was varied to produce the desired heating rates and pressures on the wedge surface. Photographic coverage of the material performance was obtained at wedge angles from 0to 38deg. Selected test results are presented which show the ablation/erosion characteristics of the material. (Author)