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Interior Perforation Flow Field Study of Partially Cut 7-Perforated Stick Propellants

Treść / Zawartość
Identyfikatory
Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
Partially cut 7-perforated propellants are used in gun charges because of their good flame spreading, high progressivity and loading density. To investigate the complex flow field in a partially cut multi-perforation stick propellant, a steady three-dimensional model for compressible viscid internal perforation and the vent gas region flow field was established and simulated by ANSYS Fluent. The results illustrate that the cut vent can decrease the internal perforation pressure and end face gas velocity. Moreover, the mass that escaped through the vent to the outside was 85.3% of the whole internal burning propellant gas. When the width of the cut slot was larger than half the diameter, the internal pressure decreased weakly and the progressive intensity decreased slightly as the cut slot was increased. As the same side intervals were increased or the perforation diameters were decreased, the end face gas velocity and the internal and external perforation pressure differences increased, and the propellant combustion area progressive intensity increased. As the web thickness increased, the internal pressure increased, and gas velocity exhibited an upward tendency and reached peak values when 2e1 = 0.84 mm, whilst the progressive intensity increased slightly.
Rocznik
Strony
564--582
Opis fizyczny
Bibliogr. 16 poz., rys., tab.
Twórcy
  • Nanjing University of Science and Technology, China
  • Nanjing University of Science and Technology, China
Bibliografia
  • [1] Char, J.M.; Kuo, K.K. Study of Combustion Processes of Single-Perforated Stick Propellants. J. Propul. Power 1989, 5: 262-268.
  • [2] Hsieh, W.H.; Kuo, K.K. A Study of Flame Spreading and Combustion Phenomena of Stick Propellants. Pennsylvania State University Park Report, PA, USA, 1988.
  • [3] Hsieh, W.H.; Char, J.M.; Zanotti, C.; Kuo, K.K. Erosive and Strand Burning of Stick Propellants. Part I. Measurements of Burning Rates and Thermal-wave Structures. J. Propul. Power 1990, 6: 392-399.
  • [4] Hsieh, W.H.; Kuo, K.K. Erosive and Strand Burning of Stick Propellants. Part II. Theoretical Modeling of Erosive-burning Processes. J. Propul. Power 1990, 6: 400-406.
  • [5] Zhao, X.; Zhang, X. Study of Stick-propellant Gun Interior Ballistic Considering Internal Perforation Erosive Burning. Int. Symp. Ballistics, Proc., 29th, Edinburgh, UK, 2016, 880-887.
  • [6] Zhao, X.; Zhang, X. Investigation of Stick Propellant Internal Perforation Erosive Burning on Interior Ballistics Performances. Def. Sci. J. 2017, 67: 19-25.
  • [7] Rashad, M.; Zhang, X.; Elsadek, H. Interior Ballistic Two-phase Flow Model of Guided-projectile Gun System Utilizing Stick Propellant Charge. WSEAS Trans. Appl. Theor. Mech. 2014, 9: 124-135.
  • [8] Routh, R.; Robbins, F.W.; Koszoru, A.A. A New High-Progressivity/High-Density Propulsion Concept: Partially Cut Multiperforated Stick Propellant. U.S. Army Ballistic Research Lab., Aberdeen Proving Ground Report BRL-TR-3189, USA, 1991.
  • [9] Routh, C.R; Horst, A.W. Detailed Characterization of Hypervelocity Firings in a Long 120-mm Gun. U.S. Army Ballistic Research Lab., Aberdeen Proving Ground Report BRL-TR-3190, USA, 1991.
  • [10] Routh, C.R.; Robbins, F.W.; Horst, A.W. Experimental Hypervelocity Firings Using Stick and Granular Propellant Configurations. U.S. Army Ballistic Research Lab., Aberdeen Proving Ground, Report BRL-TR-3921, USA, 1991.
  • [11] Xu, H.T.; Xiao, Z.; He, W.D. Combustion Characteristics of Partially Cut Multiperforated Stick Propellant. (in Chinese) Chin. J. Energ. Mater. (Hanneng Cailiao) 2014, 22(2): 251-255.
  • [12] Xiao, Z.; Xu, H.; He, W. Influence of Venting Parameters on Erosive Burning of Partially Cut Multi-perforated Stick Propellants. Sci. Tech. Energetic Materials 2015, 76(1): 42-46.
  • [13] Xiao, Z.; He, W.; Xu, H. Emulation and Calculation of the Burning Surface of 3D Grains of Partially Cut Multi-perforated Stick Propellant Using the Level Set Method. Propellants Explos. Pyrotech. 2016, 41: 148-153.
  • [14] Venkateswaran, S.; Deshpande, M.; Merkle, C.L. The Application of Preconditioning to Reacting Flow Computations. AIAA CFD Conf., 12th, San Diego, CA, AIAA 95-1673, 1995, 306-316.
  • [15] Willcox, M.A.; Brewster, M.Q.; Tang, K.C.; Stewart, D.S.; Kuznetsov, I. Solid Rocket Motor Internal Ballistics Simulation Using Three-Dimensional Grain Burnback. J. Propul. Power 2007, 3, 575-584.
  • [16] Summerfield, M.; Price, E.W; De Luca, L. Nonsteady Burning and Combustion Stability of Solid Propellants. AIAA, Washington, DC, 1992, pp. 717-779; ISBN 978-1-56347-014-1.
Uwagi
Opracowanie rekordu ze środków MNiSW, umowa Nr 461252 w ramach programu "Społeczna odpowiedzialność nauki" - moduł: Popularyzacja nauki i promocja sportu (2020).
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-a806a6f6-60a2-441e-85ce-5d5ffc0fce75
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