Vortex shedding, combustion response and damping can cause combustion instability under some conditions. In this paper, several mechanisms that cause combustion instability, including the geometry of the solid rocket motors (SRMs), the combustion response of the propellant, particle damping, and nozzle damping, are investigated. Specifically, the influence of the slot of the grains on the chamber acoustic mode, the content of aluminum on the combustion response and particle distribution, and the nozzle throat diameter on the nozzle damping are parametrically analyzed, respectively. Moreover, the critical parametric test in the SRM with a large length-to-diameter ratio is carried out. The results prove that the evaluation method promoted in this study can be used in the prediction of combustion instability in the SRMs.
Critical Parametric Studies of Combustion Instability in Solid Rocket Motors
18.07.2023
988881 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Combustion Instability in Solid Rocket Motors
NTIS | 1989
|Combustion instability in solid propellant rocket motors
Engineering Index Backfile | 1958
|Combustion instability in solid propellant rocket motors -- Review
Engineering Index Backfile | 1963
|Nonlinear Triggering of Combustion Instability in Solid Rocket Motors
British Library Conference Proceedings | 2012
|