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Response of Nitramine and Non-Nitramine based Composite Propellant to Pulse Triggered Combustion Instability

JAYESH UPADHYAY, AJAY PATIL, AMIT KUMAR, ARVIND KUMAR, MANOJ GUPTA

Abstract


Combustion instability (CI) is a major concern during design and development of propulsion system for various rockets & missiles. This work aims to investigate effect of nitramine on combustion response of low alumunised composite propellant. To study the CI, two different propellant compositions with and without RDX were analysed for their response to ejecta using ejecta pulser. The ejecta pulser injects the teflon ball or ejecta in solid rocket motor which may trigger CI in the motor or in worst case may result in catastrophic motor failure. Both the motors were pulsed at 65% of burn time. The response of the motor to this pressure pulse was analyzed and quantified in terms of rate of change of acoustic energy (αM) which determines the stability of motor. The αM values for propellant compositions with RDX and without RDX were found to be +17.69 and +31.47 respectively which shows that the nitramine based composite propellant are less susceptible to combustion instability as compared to non-nitramine composite propellant.

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