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Exploratory Evaluation Of Filament-Wound Composites For Tankage Of Rocket Oxidizers And Fuels

Report Number: AFML TR 65-381
Author(s): Sanger, M. J.; Molho, R.; Howard, W. W.
Corporate Author: Aerojet-General Corporation
Laboratory: Air Force Materials Laboratory
Date of Publication: 1966-01
Pages: 194
Contract: AF 33(615)-1671
Project: 7381
Task: 738101
AD Number: AD0477455

This work was undertaken to provide information on materials and fabrication techniques for the design of filament-wound tankage for storable propellants, and to define a space experiment for validating the recommended materials and techniques. Resins and liner materials were studied, under accelerated exposure conditions, in the unreinforced form and as composites. Fabrication techniques were evaluated, and dynamic tests of subscale tankage were conducted. The environmental tests indicated that the materials and fabrication techniques selected for the tankage produced satisfactory filament-wound containers for storable propellants. A technique developed for bonding a metallic liner to the filament-wound chamber provided a solution to the problem of strain compatibility under pressure cycling at optimum strain levels for glass-filament-reinforced structures. Designs were developed for a prototype tank, and analysis showed that a spheroidal configuration with a length-to-diameter ratio of 1.0 was acceptable from the standpoint of space limitations and weight economy. A space experiment was defined for use in determining the efficiency of a filament-wound storable propellant tank over a period of 1 year in an earth-orbit environment.

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