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Combustion termination of solid rocket motors

Authors: H. J. TABACK; E. E. DAY; T. P. BROWNE;

Combustion termination of solid rocket motors

Abstract

To explore the feasibility of terminating combustion without the hazardous flame and debris associated with venting, a series of sixteen 5-in.-diam motors was fired. Two techniques were investigated: 1) injection of liquid into the combustion chamber, and 2) explosive discharge of coolants from a canister located inside the chamber. The minimum quantity of water required for reliable termination was found to be less than 0.5 pt. Pressure decay rates between 12,000 and 25,500 psi/sec during water injection were observed. The ability to stop, restart, and again stop burning on command was demonstrated. Explosive quenching by shock-wave disruption of burning, followed by deposition of a subliming heat absorbing salt, is confirmed by experimental observations. Design features of this potentially lightweight and convenient technique are discussed.

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selected citations
These citations are derived from selected sources.
This is an alternative to the "Influence" indicator, which also reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).
BIP!Citations provided by BIP!
popularity
This indicator reflects the "current" impact/attention (the "hype") of an article in the research community at large, based on the underlying citation network.
BIP!Popularity provided by BIP!
influence
This indicator reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).
BIP!Influence provided by BIP!
impulse
This indicator reflects the initial momentum of an article directly after its publication, based on the underlying citation network.
BIP!Impulse provided by BIP!
5
Average
Top 10%
Average
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