Abstract The triggering combustion instability in the solid rocket motor is investigated from a nonlinear dynamical system perspective. A coupling model taking both the nonlinear acoustics in the chamber and the unsteady combustion of the solid propellant into consideration is adopted. Its typical responses to different excitations are compared systematically for varying parameters. The boundaries for the different responses in the parameter space are then investigated from the bifurcation analysis. It is shown that the triggering region of the solid rocket motor, corresponding to the bistable region of the coupling model, is confined by two curves consisting of bifurcation points, which intersects at a high order bifurcation point, the cusp point. The complex geometry of bistable region in multi-dimensional parameter space indicates the influences of parameters on the triggering combustion instability of the solid rocket motor can be quite different. The results suggest a comprehensive consideration on different parameters is needed in evaluating the combustion instability of an solid rocket motor.
Highlights The nonlinear responses of solid rocket motor are investigated via a coupling model. The bistable region with triggering instability is calculated by the hysteresis cycle. The bistablity analysis is extended from 1-parameter space to the 2-parameter space. The subcritical instability and supercritical instability are shown to be connected by a cusp point.
Nonlinear characteristics of the triggering combustion instabilities in solid rocket motors
Acta Astronautica ; 176 ; 371-382
2020-06-09
12 pages
Article (Journal)
Electronic Resource
English
Triggering of Longitudinal Combustion Instabilities in Rocket Motors: Nonlinear Combustion Response
Online Contents | 1996
|Nonlinear Triggering of Combustion Instability in Solid Rocket Motors
British Library Conference Proceedings | 2012
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