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Title: Shock-wave characterization of energetic booster-rocket propellant WAK-2 and its simulant UGS

Abstract

A series of shock-loading experiments on an energetic propellant and its simulant was conducted on a light-gas gun. The purpose of this work was to characterize the shock sensitivity of WAK-2, which is a composite-modified, double-based, booster-rocket propellant and its simulant UGS. The initial objectives were to obtain Hugoniot data, to investigate the pressure threshold at which a reaction occurs, and to measure spall threshold at various impact velocities. The Hugoniot data obtained for the propellant fits the Hugoniot curve provided by the manufacturer of the propellant. A Hugoniot curve developed for the simulant was found to match that of the propellant. The initial density, {rho}{sub 0}, initial bulk sound velocity, C{sub 0}, and constant S values for the energetic propellant WAK-2 and its simulant UGS were 1.85 g/cm{sup 3}, 2.2 mm/{mu}s and 2.66, respectively. The ignition threshold pressure of the WAK-2 was found to be in the range of 3 kbar. A violent reaction was observed for a sample impacted at a pressure of 22 kbar. In spall tests, impact pressures in the range of 1.1 to 3.1 kbar were applied to the propellant/simulant. The propellant exhibited spall strengths {approximately}0.33 kbar, with its simulant being somewhat weaker, {approximately}0.22 kbar.more » Scanning electron microscopy and electron microprobe analysis were used to characterize the microstructures of the materials and to determine the details of the spall events. 20 refs., 19 figs., 9 tabs.« less

Authors:
Publication Date:
Research Org.:
Sandia National Labs., Albuquerque, NM (USA)
Sponsoring Org.:
DOE/EH
OSTI Identifier:
5435322
Report Number(s):
SAND-89-0917
ON: DE90002633
DOE Contract Number:  
AC04-76DP00789
Resource Type:
Technical Report
Country of Publication:
United States
Language:
English
Subject:
09 BIOMASS FUELS; 45 MILITARY TECHNOLOGY, WEAPONRY, AND NATIONAL DEFENSE; PROPELLANTS; SENSITIVITY; DBP; IGNITION; MECHANICAL PROPERTIES; MICROSTRUCTURE; NITRO COMPOUNDS; RANKINE-HUGONIOT EQUATIONS; SCANNING ELECTRON MICROSCOPY; SHOCK WAVES; BUTYL PHOSPHATES; CRYSTAL STRUCTURE; ELECTRON MICROSCOPY; EQUATIONS; ESTERS; MICROSCOPY; ORGANIC COMPOUNDS; ORGANIC NITROGEN COMPOUNDS; ORGANIC PHOSPHORUS COMPOUNDS; PHOSPHORIC ACID ESTERS; 090000* - Biomass Fuels; 450100 - Military Technology, Weaponry, & National Defense- Chemical Explosions & Explosives

Citation Formats

Weirick, L J. Shock-wave characterization of energetic booster-rocket propellant WAK-2 and its simulant UGS. United States: N. p., 1989. Web.
Weirick, L J. Shock-wave characterization of energetic booster-rocket propellant WAK-2 and its simulant UGS. United States.
Weirick, L J. Sun . "Shock-wave characterization of energetic booster-rocket propellant WAK-2 and its simulant UGS". United States.
@article{osti_5435322,
title = {Shock-wave characterization of energetic booster-rocket propellant WAK-2 and its simulant UGS},
author = {Weirick, L J},
abstractNote = {A series of shock-loading experiments on an energetic propellant and its simulant was conducted on a light-gas gun. The purpose of this work was to characterize the shock sensitivity of WAK-2, which is a composite-modified, double-based, booster-rocket propellant and its simulant UGS. The initial objectives were to obtain Hugoniot data, to investigate the pressure threshold at which a reaction occurs, and to measure spall threshold at various impact velocities. The Hugoniot data obtained for the propellant fits the Hugoniot curve provided by the manufacturer of the propellant. A Hugoniot curve developed for the simulant was found to match that of the propellant. The initial density, {rho}{sub 0}, initial bulk sound velocity, C{sub 0}, and constant S values for the energetic propellant WAK-2 and its simulant UGS were 1.85 g/cm{sup 3}, 2.2 mm/{mu}s and 2.66, respectively. The ignition threshold pressure of the WAK-2 was found to be in the range of 3 kbar. A violent reaction was observed for a sample impacted at a pressure of 22 kbar. In spall tests, impact pressures in the range of 1.1 to 3.1 kbar were applied to the propellant/simulant. The propellant exhibited spall strengths {approximately}0.33 kbar, with its simulant being somewhat weaker, {approximately}0.22 kbar. Scanning electron microscopy and electron microprobe analysis were used to characterize the microstructures of the materials and to determine the details of the spall events. 20 refs., 19 figs., 9 tabs.},
doi = {},
url = {https://www.osti.gov/biblio/5435322}, journal = {},
number = ,
volume = ,
place = {United States},
year = {1989},
month = {10}
}

Technical Report:
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