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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN Imprimer: 2150-766X
ISSN En ligne: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v3.i1-6.610
pages 634-641

DIAGNOSTIC TOOLS FOR STUDIES ON BURN-RATE BEHAVIOR OF ADVANCED SOLID PROPELLANTS

S. N. Asthana
High Energy Materials Research Laboratory, Pune 411 021, India
A. N. Nazare
Explosives Research & Development Laboratory, Pune 411 021 India
S. S. Dhar
Explosives Research & Development Laboratory, Pune 411 021 India
P. G. Shrotri
High Energy Materials Research Laboratory, Pune 411 021, India
Haridwar Singh
High Energy Materials Research Laboratory, Pune 411 021; University of Hyderabad, Hyderabad

RÉSUMÉ

This paper reports the comparative burn-rate data obtained by Crawford bomb and acoustic emission techniques for double-base (DB) composite modified double-base (CMDB) composite (CP) nitramine-based minimum signature compositions and glycidyl azide prepolymer (GAP) based propellants. The acoustic technique gave higher burn rates for aluminized compositions (CP and CMDB) and lower burn rates in the case of non-aluminized propellants and minimum signature compositions with minor quantities of Al. Results obtained by both techniques were in close agreement for GAP-based compositions. A correlation between strand-burner data and test-motor burn rates has been established during this study to predict rocket motor performance. The effect of mass flow rate on overall ballistic performance has also been evaluated for selected high-energy compositions.


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