Accession Number:

AD0276642

Title:

FEASIBILITY DEMONSTRATION OF LARGE SEGMENTED SOLID PROPELLANT ROCKET MOTOR WITH DUAL TVC SYSTEM AND THERMAL GRAIN STRUCTURAL ANALYSIS

Descriptive Note:

Corporate Author:

LOCKHEED PROPULSION CO REDLANDS CALIF

Personal Author(s):

Report Date:

1962-06-12

Pagination or Media Count:

1.0

Abstract:

An engineering approximation and confirmatory experiments to the correct theoretical temperature distribution in a propellant grain are given. The limit elastic solutions to several thermal stress problems are presented. Experimental results of cyclic thermal inputs to a uniaxial, end-constrained bar are presented. A comprehensive discussion of theory and experiment relative to the time-temperature shift phenomena is presented. In a preliminary investigation into the photoviscoelastic properties of plasticized epoxy, uniaxial strain were obtained as a function of stress, time, and temperature under dead weight loading. A comparison was obtained between plasticized and unplasticized epoxy in four-point star grain configurations under transient temperature in restraining cases. Two general approximate methods of analysis for the viscoelastic material with temperature-dependent properties under transient temperature fields are given. The methods are demonstrated using a known flat plate solution for comparison and a case-bonded propellant grain. Author

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Distribution Statement:

APPROVED FOR PUBLIC RELEASE