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

• Autorzy: Shekhar H.
• Języki publikacji: EN

Abstrakty

EN

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).

Słowa kluczowe

EN

rocket propellant; burning rate; pressure time; progressive burning; tubular configuration

• Czasopismo: Central European Journal of Energetic Materials
• Rocznik: 2015
• Tom: Vol. 12, no. 2
• Strony: 347--357
• Opis fizyczny: Bibliogr. 11 poz., rys., tab.

Twórcy

autor

Shekhar H.

• High Energy Materials Research Laboratory, Sutarwadi, Pune – 411 021, India

Bibliografia

• [1] Shekhar H., Modelling of Burning Surface Regression of Taper Convex Star Propellant Grain, Def. Sci. J., 2000, 50(2), 207-211.
• [2] Shekhar H., Parametric Studies on Star Port Propellant Grain for Ballistic Evaluations, Def. Sci. J., 2005, 55(4), 459-469.
• [3] Shekhar H., Close-form Solution for Burning Surface Evolution and Performance Prediction of Finocyl Shaped Propellant Grain, 2007 International Autumn Seminar on Propellant, Explosives and Pyrotechnics (2007 IASPEP), Xi’an, China, 2007, 907-911.
• [4] Shekhar H., Burn Back Equations for High Volumetric Loading Single Grain Dual Thrust Rocket Propellant Configuration, Def. Sci. J., 2011, 61(2), 165-170.
• [5] Shekhar H., Design of Funnel Port Tubular Propellant Grain for Neutral Burning Profile in Rockets, Def. Sci. J., 2009, 59(5), 494-498.
• [6] Shekhar H., Design of Gas Generator Propellant Grains for Missile Applications, Manthan – a quarterly Magazine by Bihar Brains, 2009, 8, 8-11.
• [7] Shekhar H., Estimation of Pressure Index and Temperature Sensitivity Coefficient of Solid Rocket Propellants by Static Evaluation, Def. Sci. J., 2009, 59(6), 666-669.
• [8] Kubota N., Aoki I., Burning Rate Characterization of GAP/HMX Energetic Composite Materials, Propellants Explos. Pyrotech., 2000, 25(4), 168-171.
• [9] Babuk V.A., Dolotkazin I.N., Glebov A.A., Burning Mechanisms of Aluminized Solid Rocket Propellants Based on Energetic Binders, Propellants Explos. Pyrotech., 2005, 30(4), 281-290.
• [10] Guo X., Li F., Song H., Liu G., King L., Li M., Combustion Characteristics of a Novel Grain Binding High Burning Rate Propellant, Propellants Explos. Pyrotech., 2008, 33(4), 255-260.
• [11] Shekhar H., Mathematical Formulation and Validation of Muraour’s Linear Burning Rate Law for Solid Rocket Propellants, Cent. Eur. J. Energ. Mater., 2012, 9(4), 353-364.