Accession Number : AD0728753

Title :   A Thermoviscoelastic Study of a Solid Rocket Propellant Grain.

Descriptive Note : Technical publication May 68-Aug 69,

Corporate Author : NAVAL WEAPONS CENTER CHINA LAKE CALIF

Personal Author(s) : Jeter,Edward L.

Report Date : JUN 1971

Pagination or Media Count : 70

Abstract : A numerical integration procedure is developed to solve a general axisymmetric plane strain cylinder problem involving thermorheologically simple viscoelastic material properties. Axisymmetric loadings due to internal pressure, centrifugal body forces, and thermal stresses are considered in the analysis, and use is made of the Moreland-Lee reduced time hypothesis in order to include the ability to solve problems undergoing transient temperature distributions. Provisions are also included for solving the problem of a viscoelastic cylinder with an elastic case. Several check solutions are compared with some exact results and known solutions, and a solution is given for solid rocket propellant grain during firing when the inside surface is ablating. Realistic solid propellant material properties are employed in the latter solution. (Author)

Descriptors :   (*ROCKET PROPELLANT GRAINS, THERMAL STRESSES), VISCOELASTICITY, SOLID ROCKET PROPELLANTS, COMBUSTION, ABLATION, THERMAL ANALYSIS, NUMERICAL ANALYSIS

Subject Categories : Thermodynamics
      Solid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE