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Fundamental Studies Relating to Systems Analysis of Solid Propellants, October l, 1959-December 31, 1959

Blatz, P. J. and Knauss, W. G. and Schapery, R. A. and Stimpson, L. D. and Williams, M. L. (1960) Fundamental Studies Relating to Systems Analysis of Solid Propellants, October l, 1959-December 31, 1959. California Institute of Technology , Pasadena, CA. (Unpublished)

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Previous reports of this series have attempted to define some of the important parameters affecting the structural integrity of solid propellant rocket grains. Three general areas have been discussed, namely material properties, analytical procedures, and criteria for mechanical failure. This particular report is devoted to a more detailed examination of the properties of a filled viscoelastic resin, and their representation by appropriate mechanical models. In addition, a comparison of two methods of computing viscoelastic strains in a pressurized cylinder is presented. In the category of material properties, linear viscoelastic model theory is reviewed, and certain important relations among sets of experimental data are deduced. A justification for the application of this theory is provided by the analytic representation of available dynamic data in terms of a well-known distribution function. Since the inception of this work additional experimental data on propellants has become available. In the category of analytical procedures, the usual approach of representing material properties by a four-element model, as determined from the dynamic data in a limited frequency range, is compared with the more sophisticated Fourier transform method in which the entire frequency range is utilized. The two approaches are applied to calculate the viscoelastic hoop strain at the inner boundary of an internally pressurized infinitely long hollow cylinder subjected to a ramp-type pressure pulse. In this example, the dilatation is assumed elastic or frequency independent and the distortion viscoelastic. In the following quarter, primary effort will be devoted to the determination of a criterion for mechanical failure of propellants. Two steps are involved. One is the analytical representation of ultimate strain as a function of temperature on strain rate by means of a mechanical model. In addition to the usual distribution of relaxation (or retardation) times, this model will be supplied with a distribution of ultimate strain. Step two involves the choice of a suitable criterion for compounding ultimate strain or ultimate stress components into a single parameter, which, when exceeded at a given rate and temperature, denotes the onset of fracture or mechanical failure.

Item Type:Report or Paper (Technical Report)
Additional Information:15 January 1960. Progress Report No. 5 - GALCIT 101 Subcontract no. RU-293 October 1, 1959 - December 31, 1959. This research is supported by The Thiokol Chemical Corp., Redstone Division.
Group:Graduate Aeronautical Laboratories (Solid Mechanics), GALCIT
Funding AgencyGrant Number
Thiokol Chemical CorporationRU-293
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Other Numbering System NameOther Numbering System ID
GALCIT Report SM101-5
Record Number:CaltechAUTHORS:20151203-165233805
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:62591
Deposited On:04 Dec 2015 16:50
Last Modified:23 Nov 2021 00:29

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