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Studies on the Ballistic Parameters of a Deterred Triple Base Propellant Used in Large Caliber Ammunition

Dahiwale Sunil M., Bhongale Chetan J., Roy Shubhankar, Navle Pradeep B., Asthana Shrinandan N.

Central European Journal of Energetic Materials

2019

Vol. 16, no. 3

449--467

In this work, the energetic plasticizer N-n-butyl-N-(2-nitroxyethyl)nitramine (Bu-NENA) was used as a deterrent coating for a triple base propellant (TBP) that finds application in large caliber guns. Closed vessel (CV) evaluation was performed to study the ballistic performance of the deterred propellant. A TBP containing nitrocellulose (NC), nitroglycerine (NG) and nitroguanidine (NQ) was coated with an energetic plasticizer using a solution of Bu-NENA. The Bu-NENA coated propellant exhibited inhibition to burning resulting in a reduction in the values of the ballistic parameters viz. (dP/dt)max, burning rate coefficient (β) and relative vivacity (RV), while the pressure index (α) and rise time were increased. The trends obtained during this work display the potential of Bu-NENA as deterrent.

Effects of the Burning Rate Index on the Pressure Time Profile of Progressive Burning Tubular Rocket Propellant Configurations

Shekhar H.

Central European Journal of Energetic Materials

2015

Vol. 12, no. 2

347--357

A theoretical ballistic analysis of tubular rocket propellants burning in the progressive mode was carried out with the objective of ascertaining the effects of the burning rate index on the average pressure and the total burning time of the pressure time profiles. A constant ‘H’ is introduced to obtain close-form expressions for the initial pressure, the maximum pressure, the area under the pressure time profile, the total burning time and the average pressure. The derivation of the total burning time for a progressive burning tubular rocket propellant is a new approach described in this paper. It is observed that the average pressure during propellant combustion varies with the burning rate index. A higher burning rate index of the propellant leads to a lower average pressure for lower burning rate propellants (8 mm/s at 7 MPa) and a higher average pressure for higher burning rate propellants (10 mm/s at 7 MPa). A unique situation occurs for an intermediate burning rate propellant (9 mm/s at 7 MPa), where the maximum pressure was obtained theoretically for a specific value of the burning rate index (0.69).