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Research study : Thermal curtain permeability and thermal response test for SRB reentry

Author:
Fuller, C. E.
Published:
Nov 1, 1978.
Physical Description:
1 electronic document
Additional Creators:
Levie, J. K., III and Powell, R. T.
Online Version

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Summary:
Nine inch diameter samples of the material which will provide thermal and acoustic protection between the nozzle and outer skirt on the space shuttle solid rocket boosters were subjected to heating tests to determine the porosity of the material and the thermal response to a step change in heating. For the porosity measurements a steady state flow of air at 70 F, 500 F, and 1000 F was passed through a sample of the curtain material and measurements of the flow rates were made at different pressure drops across the sample. For the transient measurements, a sample of the curtain material was subjected to a step change in temperature as air was passed through the sample. Measurements of the heat flow through the sample were made as a function of time after the input of the heat pulse. The sample consisted of three layers of curtain panels. Each panel was made of combinations of quartz and fiberglass cloth between which a fiberfrax filler material had been stitched. The hardware design and test procedures were described. Data are provided in engineering units for the flow conditions and and temperatures at which measurements were conducted.
Other Subject(s):
Collection:
NASA Technical Reports Server (NTRS) Collection.
Note:
Document ID: 19790002919.
Accession ID: 79N11090.
RTR-035-1.
NASA-CR-150847.
Terms of Use and Reproduction:
No Copyright.
View MARC record | catkey: 15727318