Accession Number : ADP004529
Title : Acoustic Energy Balance Method,
Corporate Author : UTAH UNIV SALT LAKE CITY DEPT OF MECHANICAL AND INDUSTRIAL ENGINEERING
Personal Author(s) : Flandro,G. A.
Report Date : OCT 1984
Pagination or Media Count : 16
Abstract : A useful analytical model for nonlinear rocket instability must adequately represent the following characteristics: (1) steep fronted waves, (2) limit cycle operation, and (3) triggering phenomena. To include all of these important attributes requires retention of terms to third order in the perturbation parameter representing the system amplitude. This leads to an extremely complicated analysis; means must be found to develop useful analytical models that retain some physical clarity. Application of energy methods often results in simplification of the formulation. In this paper the energy method is combined with a simplified representation of the wave structure to produce an approximate model for axial pressure fluctuations in a tubular port which demonstrates all of the nonlinear characteristics of importance. Effects of nonlinear combustion and losses in shock waves are included.
Descriptors : *SOLID PROPELLANT ROCKET ENGINES, *COMBUSTION STABILITY, *ACOUSTIC WAVES, *MATHEMATICAL MODELS, COMBUSTION, SHOCK WAVES, NONLINEAR PROPAGATION ANALYSIS, PRESSURE, PARAMETRIC ANALYSIS, OSCILLATION, ENERGY, BALANCE, LOSSES, SYMPOSIA
Distribution Statement : APPROVED FOR PUBLIC RELEASE