Investigation Of Propellant Actuated Devices For Use In Emergency Crew Escape Systems For Advanced Aerospace Vehicles. Phase III. Design Study.

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Report Number: AFFDL TR 65-26 Part 2
Author(s): Bleikamp, R. H., Lake, E. R., McGovern, D. R.
Corporate Author(s): McDonnell Aircraft Corp St Louis MO
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1965-04
Pages: 194
Contract: AF 33(615)-1292
DoD Project: 1362 - Crew Escape for Flight Vehicles
DoD Task: 136205
Identifier: AD0464738

This report describes the results of the third and final phase of a study related to the design of PAD (Propellant Actuated Devices) for use in a separable crew escape module applicable to a life/glide re-entry vehicle. Based on results of Phases I and II, preliminary designs have been established for each PAD as a function of component performance criteria. Prime consideration was given to successful abort at any point during the mission profile. It was found possible throughout the entire Phase III effort to evolve component designs for each PAD function without exceeding to any great extent the present state-of-the-art. As a result, the areas mentioned for future research and development are generally concerned with characterization of the more promising new explosives and propellants, and the presentation of several concepts, which, if developed, would offer secondary improvements in the overall system weight, reliability, or cost.

Provenance: Lockheed Martin Missiles & Fire Control

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