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Specific Design Features of Solid Propellant Rocket Motors for Shoulder-Launched Weapon Systems

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Konferencja
Scientific Aspects of Armament and Safety Technology. 8th International Armament Conference ; 6-8.10. 2010 ; Pułtusk, Poland
Języki publikacji
EN
Abstrakty
EN
Solid propellant rocket motors for Shoulder Launched Infantry Weapon Systems (SLWS) are characterized with a very short burning time, high-pressure combustion and a wide spectrum of design solutions for rocket motor structure. Interior ballistic behaviour of such rocket motors depends on many factors such as design structure, propellant grain shape, propellant grain joint to the rocket motor case, type and location of the igniter, spinning mode and nozzle design. Erosive burning also plays important role due to high combustion gases mass flow rate. Numerical simulation of the igniter combustion gases flow through the hollow of the propellant grain tubes with gas temperature distribution was carried out in this paper. Results confirmed assumptions that igniter interior gas flow affected duration of the pressure rise. A mathematical model approach for prediction of the curve p = f(t) which was included in a model of the corrected propellant grain burning surface for two types of short-time rocket motors has been presented. A good agreement with measured curves was achieved.
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  • University of Sarajevo, Mechanical Engineering Faculty, Defence Technologies Department, Vilsonovo setaliste 9, 71000 Sarajevo, Bosnia and Herzegovina
Bibliografia
  • [1] http://upload.wikimedia.org/wikipedia/commons/c/c5/AT4_rocket_launch er.jpg
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  • [9] Terzic J., Prediction of idealized internal ballistic properties of a rocket motor with DB solid propellant, Master thesis, University of Sarajevo, Faculty of Mechanical Engineering, 2002.
  • [10] Zecevic B., Influence of the variable radial acceleration to internal ballistics of rocket motors with DB propellants, Dissertation, University of Sarajevo, Faculty of Mechanical Engineering, 1999.
  • [11] Razdan K.M. and Kuo K.K., Erosive Burning of Solid Propellants, Fundamentals of Solid-Propellant Combustion, Edited by Kuo K.K. And Summerfield, Progress in Astronautics and Aeronautics, vol. 90, AIAA, 1984.
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  • [14] Willcox M.A., Quinn Brewster M., Tang K.C., Scott Stewart D., and Kuznetsov I., Solid Rocket Motor Internal Ballistics Simulation Using Three-Dimensional Grain Burnback, Journal of Propulsion and Power vol. 23, no. 3, May–June 2007.
  • [15] Terzic J. and Zecevic B., Prediction of performances of rocket motors. SPPMEF Program, University of Sarajevo, Defence Technologies Department, 2002.
  • [16] COMET Version 2.00 - Tutorials, ICCM - Institute of Computational Continuum Mechanics GmbH, Hamburg, March 2001.
  • [17] http://en.wikipedia.org/wiki/M72_LAW
  • [18] http://www.armyrecognition.com/forum/viewtopic.php?t=551
  • [19] http://www.mycity-military.com/Kopnena-vojska/Rucni-Protivoklopni-Raketni-Bacaci-tipa-RPG_4.html
  • [20] Coats D.E., Levine J.N., Cohen N.S., Nickerson G.R., Tyson T.J., A Computer Program for the Prediction of Solid Propellant Rocket Motor Performance, vol. 1, Air Force Rocket Propulsion Laboratory, July 1975. B. Zecevic, J. Terzic, M. Baskarad, A. Catovic, S. Serdarevic-28 Kadic, Z. Pekic
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-article-BWA0-0047-0009
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