The effect of compositional variables upon oscillatory combustion of solid rocket propellants

✍ Scribed by M.D. Horton; D.W. Rice

• Publisher: Elsevier Science
• Year: 1964
• Tongue: English
• Weight: 526 KB
• Volume: 8
• Category: Article
• ISSN: 0010-2180
• DOI: 10.1016/0010-2180(64)90053-7

✦ Synopsis

In this test programme, a laboratory scale burner was used to study the oscillatory combustion o[ a composite propellant system. The results show that the variation o [ binders (polysulphide, polyurethane and polybutyl-acrylic acid) had a comparatively small effect upon the oscillatory combustion o[ the propellant system. Various burning rate modifiers (ammonium perchlorate particle size, copper chromite and lithium fluoride) greatly affected the oscillatory combustion o[ a polybutyl-acrylic acid propellant. Nomenclature * Velocity of sound in combustion gas E, The activation energy which describes gasification of the solid propellant [ Frequency of oscillations during growth period of oscillations ]a Frequency of oscillations during decay period j Exponent describing temperature sensitivity of burning rate (r=E,T 0 L Length of combustion gas column during growth or decay of oscillations m Exponent describing pressure sensitivity of burning rate (r=r0p") P Mean chamber pressure r Burning rate of solid propellant T~ Surface temperature of burning propellant V Flame velocity Y Real part of specific acoustic admittance of combustion zone % Exponential growth rate constant of oscillations e,~ 'Exponential' decay rate constant Amplitude of fractional perturbation in pressure at the combustion zone o-Amplitude of fractional perturbation in density accompanying 7 Ratio of specific heats of gas p Density of gas P~ Density of propellant