Accession Number:

ADP000225

Title:

Shock-Induced Flow Separation and the Orbiter Thermal Protection System,

Descriptive Note:

Corporate Author:

ROCKWELL INTERNATIONAL DOWNEY CA SHUTTLE ORBITER AND INTEGRATION DIV

Personal Author(s):

Report Date:

1981-07-01

Pagination or Media Count:

13.0

Abstract:

The concept of the Space Shuttle orbiters thermal protection system TPS is based on reusable tiles of various shapes and sizes, but none exceeding 8 inches. The tiles are top-coated, but the sides edges are not thermally protected and are susceptible to damage from aerothermodynamic heating. Such a problem occurs when large air-mass flows, created by local pressure gradients, circulate into the tile gaps. A typical problem is a pressure gradient created during entry by body flap detection. After a brief description of how the problem affects the Space Shuttle orbiter, a theoretical and experimental review of the phenomenon in which the major parameters involved in gap heating are discriminated and analyzed.

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE