Accession Number : AD0848594
Title : Heat Conduction and Stress Analysis of Solid Propellant Rocket Motor Nozzles.
Descriptive Note : Technical rept.,
Corporate Author : ROHM AND HAAS CO HUNTSVILLE AL REDSTONE RESEARCH LABS
Personal Author(s) : Brisbane, John J.
Report Date : FEB 1969
Pagination or Media Count : 194
Abstract : A series of three computer programs has been developed that greatly simplify the stress analysis of solid propellant rocket nozzles. The first of these programs is an axisymmetric finite element heat conduction program that is used to generate the time dependent temperature distributions in the nozzle. The second program is an axisymmetric finite element stress analysis program which uses the temperature distribution determined by the first program in addition to mechanical loadings to determine the stresses, strains, and displacements throughout the nozzle. The third program is a data reduction program which has, as output, plots of stress and strain contours in the nozzle. The heat conduction and stress analysis programs may be used separately if desired. If they are used together, information is passed from the first to the second by magnetic tape. (Author)
Descriptors : (*SOLID PROPELLANT ROCKET ENGINES, NOZZLES), (*NOZZLES, THERMAL ANALYSIS), THERMAL CONDUCTIVITY, THERMAL STRESSES, NOZZLE AREA RATIO, NOZZLE INSERTS, THERMAL INSULATION, MATHEMATICAL MODELS, COMPUTER PROGRAMMING, COMPUTER PROGRAMS, INSTRUCTION MANUALS, PUNCHED CARDS.
Subject Categories : Computer Programming and Software
Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE