Theoretical model describes conditions leading to instability in solid rocket motor in terms of combustion characteristics of propellant and characteristics of chamber; characteristics of chamber are defined quantitatively in terms of its characteristic length; theory is applied successfully to interpret existing combustion chamber characteristic length instability data and to define relationship between characteristic length instability and acoustic instability through acoustic admittance parameter; how theory can be employed to establish transient combustion characteristics of propellant.
Interpretation of L combustion instability in terms of acoustic instability theory
AIAA J
AIAA Journal ; 5 , n 6
1967
6 pages
Article (Journal)
English
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Springer Verlag | 1968
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