High Temperature Investigation of Various Crew Escape Concepts for the Reentry Flight Regime

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Report Number: AFFDL TR 64-161
Author(s): Cohan, C. J., Campbell, G., Herman, W., Nugent, W., Heathman, J.
Corporate Author(s): General Dynamics Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-11
Pages: 300
Contract: AF 33(615)-1131
DoD Project: 1362 - Crew Escape for Flight Vehicles
DoD Task: 136203
Identifier: AD0461713

This report presents the results of an analysis of escape system separation techniques from a maximum heating re-entry trajectory. Four escape capsule concepts applicable to a lifting type flight vehicle were considered. These are (1) a separable-noise ballistic body; (2) a separablenose lifting body; (3) a pod capsule; (4) a turnaround capsule. The objective of the study was to determine the applicability of these capsules and various thermal protection schemes to providing escape capability from the maximum heating point of a typical lifting re-entry trajectory. The compatibility of escape techniques developed at the maximum heating point with providing escape capability throughout the complete mission profile was also investigated. It was determined that all concepts except the turnaround capsule could provide escape capability throughout the mission.

Provenance: Lockheed Martin Missiles & Fire Control

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