Flight Investigation of the Effects of Apollo Heat-Shield Singularities on Ablator Performance.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1968
- Accession Number
- ADA309322
Entities
People
- Brian J. O'hare
- Thomas E. Walton Jr.
- William G. Witte
Organizations
- Langley Research Center