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Preliminary analysis of ballistic requirements for LOVA propellants for new generation tank ammunition
Author(s) -
Bartosz Fikus,
Zbigniew Leciejewski,
Jakub Michalski,
Zbigniew Surma,
Radosław Trębiński
Publication year - 2020
Publication title -
materiały wysokoenergetyczne / high energy materials
Language(s) - English
Resource type - Journals
ISSN - 2083-0165
DOI - 10.22211/matwys/0139e
Subject(s) - propellant , ammunition , aerospace engineering , burn rate (chemistry) , mechanical engineering , propulsion , projectile , internal ballistics , materials science , ballistics , engineering , nuclear engineering , aeronautics , metallurgy
At the end of 2016, the Scientific-Industrial Consortium (Mesko S.A., Polska Grupa Zbrojeniowa S.A., Warsaw University of Technology, Military University of Technology, Military Institute of Armament Technology) set up an R&D project to develop and manufacture a demonstrator of new generation critical components for a 120 mm Polish tank munition. The critical elements for the project included a combustible charge case, an insensitive propellant and tungsten rods for subcalibre projectiles. The task of the Military University of Technology was to develop the basic technology and fabricate insensitive LOVA propellants on a laboratory scale (research team of the Faculty of Advanced Technologies and Chemistry) and carry out the ballistic and simulation tests of a 120 mm tank gun using ammunition incorporating the developed LOVA propellant (research team of the Faculty of Mechatronics, Armamen and Aerospace). The article also includes an analysis of available literature on energy and ballistic properties of LOVA and JA-2 propellants. Closed-vessel tests of JA-2 propellant (manufactured by Nitrochemie AG, designation LO5460) were also carried out. The tests were carried out in a 200 cm3 closed vessel. Based on the propellant gas pressure/time records, the propellant force and co-volume, and dynamic vivacity curves were determined. A linear combustion rate coefficient was determined using the measured results of the propellant grain geometry. The authors’ own data enabled the carrying out of preliminary simulation tests of the 120 mm propellant system.

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