Abstract
Results from an ongoing study of the performance of thermal-protection systems for a conical, drag-braketype aeroassisted orbital transfer vehicle (AOTV) are presented. Three types of heat shields are considered: rigid ceramic insulation, flexible ceramic blankets, and ceramic cloths. The results for the rigid insulation apply to other types of AOTVs as well. Charts are presented in parametric form so that they may be applied to a variety of missions and vehicle configurations. The parameters considered include: braking-maneuver heat flux and total heat load, heat-shield material and thickness, heat-shield thermal mass and conductivity, absorptivity and emissivity of surfaces, thermal mass of support structure, and radiation transmission through thin heat shields. Results of temperature calculations show trends with, and sensitivities to, these parameters. The emphasis is on providing useful information in estimating the minimum required mass of these heat-shield materials.
Published Version
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