AN EVALUATION OF THERMAL PROTECTION FOR APOLLO

Abstract

Results of experimental and analytical investigations associated with thermal protection for Apollo are presented. The experimental investigation was directed toward the evaluation of ablation materials for both convective and radiative heating and of the influence of char thickness on the performance of a charring ablator. The analytical investigation consisted of a thermal analysis to predict the required thermal protection weight for a flight condition. These investigations indicated that advanced charring ablators having low density are best suited for the thermal shield for Apollo. Such materials achieve high efficiency by combining the desirable features of ablation and reradiation. This efficiency is not seriously affected by the presence of radiative heating and is attained with only moderate char thickness. The efficiency is decreased for the vehicle afterbody because of exposure to lower heating rates which require more insulation weights. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1961
Accession Number
AD0326915

Entities

People

  • Kenneth L. Wadlin
  • Robert T. Swann
  • Roger W. Peters
  • William A. Brooks Jr.

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Ablation
  • Ablative Materials
  • Boundary Layer
  • Ceramic Matrix Composites
  • Charring
  • Composite Materials
  • Computer Programs
  • Experimental Data
  • Heat Energy
  • Heat Transfer
  • Low Density
  • Materials
  • Pyrolysis
  • Stagnation Point
  • Surface Temperature
  • Thermal Conductivity
  • Thermal Radiation

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Rocket Propulsion.
  • Thermal Physics or Thermal Science.

Technology Areas

  • Microelectronics