Accession Number : AD0786924
Title : Nonlinear Analysis of Solid Rocket Combustion Instability. Volume I.
Descriptive Note : Final rept.,
Corporate Author : ULTRASYSTEMS INC IRVINE CALIF
Personal Author(s) : Levine,Jay N. ; Culick,F. E. C.
Report Date : AUG 1974
Pagination or Media Count : 187
Abstract : The primary objective of the current effort was to improve the utility, efficiency and accuracy of the previously developed nonlinear longitudinal combustion instability program. A finite difference procedure has been substituted for the method of characteristics solution of the governing equations of motion. The range of allowable motor and grain geometries has been greatly extended. In addition, the two-phase analysis has been extended to multiple particle sizes. A comparison with data from a small laboratory pulse motor has demonstrated that the present nonlinear model is capable of quantitatively predicting limiting amplitude when the combustion response of the propellant is adequately characterized. The program has also been modified to make it applicable to T-burners. A vent model which accounts for acoustic radiation losses has been developed. Separate nonlinear particle damping and uncoupled nonlinear combustion response studies have been carried out. (Modified author abstract)
Descriptors : *Combustion stability, *Solid rocket propellants, *Solid propellant rocket engines, Propellant grains, Burning rate, Computer programming, Nozzle gas flow, Mathematical models, Equations of motion, Nonlinear systems, Instability, Particles, Damping, Finite difference theory
Subject Categories : Air Breathing Engines(unconventional)
Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE