Shock-Induced Flow Separation and the Orbiter Thermal Protection System,
Abstract
The concept of the Space Shuttle orbiter's 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1981
- Accession Number
- ADP000225
Entities
People
- Serge-albert Waiter