FEASIBILITY DEMONSTRATION OF LARGE SEGMENTED SOLID PROPELLANT ROCKET MOTOR WITH DUAL TVC SYSTEM AND THERMAL GRAIN STRUCTURAL ANALYSIS
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 12, 1962
- Accession Number
- AD0276642
Entities
People
- J.w. Jones
Organizations
- Lockheed Propulsion Company