Linear pressure coupled frequency response of heterogeneous solid propellants

Murphy, Jeffrey J.; Krier, Herman

doi:10.1016/s0082-0784(98)80085-4

Cited by 8 publications

(1 citation statement)

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“…[7][8][9][10][11][12][13][14] Yet, as far as examining how initial temperature affects the calculated pressurecoupled response is concerned, very few studies performed to date examined these effects.…”

Section: Initial Oscillatory Combustion Model Theory and Resultsmentioning

confidence: 99%

Modeling Effects of Initial Temperatures on a Propellant's Pressure-Coupled Response Using a Psedo Propellant Model

Spurling¹

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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A parametric analysis is performed using the Zeldovich-Novozhilov (ZN) method combined with a pseudo-propellant model (Petite Ensemble) to illuminate the linkage between a propellant's initial temperature, propellant oxidizer size distribution, and resulting pressure-coupled response. Previous testing of an Ammonium-Perchlorate Hydroxyl-Terminated Polybutadiene (AP/HTPB) propellant in a temperature conditioned T-burner combined with modeling using global propellant parameters in a ZN model has shown a direct link between a propellants' initial temperature and its pressure-coupled response. The results from this analysis, compared to data taken by a temperature conditioned T-burner and the previous modeling effort displays this linkage between initial temperature and pressure-coupled response as well. While the temperature sensitivity parameter has the largest effect on pressure-coupled response, the larger particle size fraction of oxidizer is the most influential on increasing propellant temperature sensitivity. NomenclatureA = Non-dimensional function used in linear frequency response analysis ̅ = Multiplicative factor used in Arrhenius pyrolysis law, (cm/s)/(atm) ns B = Non-dimensional function used in linear frequency response analysis c = Specific heat of the solid propellant � = Activation energy at the propellant surface (cal/mol) f = Frequency (Hertz) i = The imaginary component of a complex number (i = √−1) M = The number of pseudo-propellants contained in the complete propellant m j = Mass fraction of the j th component n = Non-dimensional pressure exponent for steady pressure conditions n s = Non-dimensional pressure exponent for pyrolysis law. η = Thermal diffusivity (m 2 /s) σ p = Burn rate temperature sensitivity at a constant pressure (%/K) ̅ = Mean pressure (MPa) r j = burn rate of the j th component Rp = Pressure-coupled response function, non-dimensional ℜ = Universal gas constant (1.987 cal/mol•K) S j = Ballistic property of the j th component ̅ p = Burn rate (mm/s) ̅ = Mean Burn rate (mm/s) ρ p = Propellant density (kg/cm 2 ) T s = Burning surface temperature (K) T o = Initial bulk propellant temperature (K) z 1,2 = Complex characteristic roots ( �1 ± �(1 + 4 Ω)� 2 ⁄ ) Ω = Non-dimensional frequency (2 ̅ 2 ⁄ ) Downloaded by PRINCETON UNIVERSITY on August 11, 2015 | http://arc.aiaa.org |

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