Accession Number : ADA309322

Title :   Flight Investigation of the Effects of Apollo Heat-Shield Singularities on Ablator Performance.

Descriptive Note : Technical note,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Personal Author(s) : Walton, Thomas E., Jr. ; Witte, William G. ; O'Hare, Brian J.

PDF Url : ADA309322

Report Date : SEP 1968

Pagination or Media Count : 64

Abstract : The Apollo ablative heat shield material was studied under perturbed heating conditions caused by several simulated Apollo heat shield singularities. The recovered spacecraft, which contained simulations of the Apollo singularities, experienced an order of magnitude less recession in the unperturbed areas than had been predicted. A recalculation of the surface recession utilizing revised rate controlled oxidation constants obtained from arc jet tests produced results compatible with the measured surface recession. With the exception of the upstream lip of both simulated umbilical fairings, no appreciable increase in surface recession attributable to the singularities was noted. The effects of simulated Apollo singularities on ablator performance were minor.

Descriptors :   *ABLATION, *HEAT SHIELDS, *MANNED SPACECRAFT, SIMULATION, EXPERIMENTAL DATA, ATMOSPHERE ENTRY, RATES, OXIDATION, PERTURBATIONS, ELECTRIC ARCS, SPACE SIMULATION CHAMBERS, ABLATIVE MATERIALS.

Subject Categories : Manned Spacecraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE