Shuttle crew escape tube study

Abstract

An investigation was performed to examine the feasibility of an escape tube as an aid in crew bailout from the Shuttle Orbiter at subsonic speeds. The deployable escape tube extended from the main side hatch downwards. Wind-tunnel tests with scaled models demonstrated that successful bailout was possible when the tube exit was at least 1 foot below the wing leading edge. The aerodynamics of the Orbiter were only slightly degraded with the tube deployed. Several tube designs were investigated, the most promising of which was an inflatable elastic/fabric 'Airmat' configuration. Loads on the tube were within capability of current airmat technology.