Burning rate of solid propellant

Kendrick et al, Effects of a Magnetic Field on Burning Rate of Solid Propellant , Rept No... 

Atwood, A. I., Boggs, T. L, Curran, P. O., Parr, T. P., and Hanson-Parr, D. M., Burn Rate of Solid Propellant Ingredients, Part 1 Pressure and Initial Temperature Effects, and Part 2 Determination of Burning Rate Temperature Sensitivity, Journal of Propulsion and Power, Vol. 15, No. 5, 1999, pp. 740-752. 

E.W. Price, "Catastrophic Changes in Burning Rates of Solid Propellants During Combustion Instability , ARS J 30, 707(1960) C) R. Denison E. Baum, "A Simplified Model for Unstable Burning in Solid Propellants ,... 

The discussion of the important design considerations of solid-propellant motors presented in Section I has shown the importance of the steady-state burning rate of the propellant. The particular mission for a rocket motor to... 

Strand Burning Rate of Solid Rocket Propellants (1299—1304)... 

PATR 2488(1958)(New formulas for rapid calcn of linear burning rates of solid proplnts) 32)J. Delacarte et al, MP 41, 223 65(1959)(Contribution to study of rates of burning and other props of composite proplnts) 33)J Taylor, "Solid Propellant and Exothermic Compositions , Interscience, NY(1959), 55-6 34)C.Napoly, MP 42, 229-46(1960)(4 refs)(Relations between linear rate of burning, apparent potential and pressures for proplnts consisting of only NC, NG and Centralite) 35)Anon, "Ordnance Proof Manual , Aberdeen Proving Ground, Md,7-24 36)L.Shulman et al, PATR FRL-TR 41(1961)... 

Princeton Univ Press, Princeton, NJ(1956),pp 470-513(70 refs) 24)C.Hugget, "Combustion of Solid Propellants , in the above book by Lewis et al,pp 514-74(98 refs) 25)F.A.Warren, "Rocket Propellants , Reinhold, NY(1958), 88-107 l37-40(Burning and burning rate of rocket propellants) 26)J.Taylor, "Solid Propellant and Exothermic Compositions , Interscience, NY(1959), 100-4(Burning rate of rocket proplnts) 27)J. 

Osbom RJ. Burdick, "Continuous Measurement of the Burning Rates of Solid Rocket Propellants , Report No 1-64-3, JPC 369, Jet Propulsion Center, Purdue University (1964)... 

A bomb used to determine the -> Burning Rate of solid rocket propellants. 

Alex is an -> aluminum powder formed by explosion of electrically heated aluminum wires in inert atmospheres with particle sizes between 50 and 200 nm. Due to a passivation layer of a thickness between 2 to 4 nm a substantial amount of the particles is already converted to alumina the formation of which should be avoided by in-situ coating. In addition to the diffusion controlled oxidation at lower temperatures, a partial oxidation of the particles can occur by a fast chemically controlled reaction. Alex can increase the burning rate of solid composite rocket propellants up to a factor of 2. An increase of detonation velocity is not confirmed but Alex might improve -> air blast or fragment velocities of some high explosives. 

Composition Variables on Acceleration-Induced Burning-Rate Augmentation of Solid Propellants , NASA TND-6923 (1972) 13) G.W. 

In addition to the energy requirements of solid propellants, Eq. (3) shows that consideration must be given to the mass-flow rate of the combustion products through the nozzle. Because all solids burn on the exposed surface, the mass flow of propellant combustion products is given by the equation... 

In an attempt to understand the combustion mechanism of catalyzed double-base propellants, several investigators have conducted experiments to measure the burning rates of strands of liquid nitrate esters. The various measurement techniques were very similar to that employed in a conventional solid propellant strand burner. The liquid esters were placed in a tubular container, and the liquid surface regression speeds were measured by optical methods or by the fuse-wire method used in solid-propeUant strand burners. The only important difference between the solid and the liquid strand burning-rate measurements is that the liquid strand burning speed is very much dependent on the diameter of the container. 

Bastress, E. K., Modification of the Burning Rates of Ammonium Perchlorate Solid Propellants by Particle Size Control, Ph.D. Thesis, Department of Aeronautical Engineering, Princeton University, Princeton, NJ (1961). 

Klager, K., and Zimmerman, G. A., Steady Burning Rate and Affecting Factors Experimental Results , Nonsteady Burning and Combustion Stability of Solid Propellants (Eds. De Luca, L., Price, E. W, and Summerfield, M.), Progress in Astronautics and Aeronautics, Vol. 143, Chapter 3, AIAA, Washington DC, 1992. 

Zel dovich noted (Ref 6) that in order for a stationary burning rate of propellant to be recovered after a pressure fluctuation, enough time must elapse to allow a layer of the propellant to heat up. When the pressure varies rapidly, and there is insufficient time for the solid to heat up, the derivative du/dp (rate of burning velocity increase for a given pressure rise) and the pressure exponent become larger than during steady burning. Therefore, in a small chamber at low pressure, when the characteristic hydrodynamic time of pressure variation is shorter than the burn-up time of the heated layer, stability can be lost... 

Figure 2. Pressure dependence of burning rate of a composite solid propellant with 75% AP + 25% polyester resin (99)...

Different classes of solid propellants DB, CMDB, and fuel rich (FR) have been developed in order to meet the requirements of various missions in terms of specific impulse (Lsp) and wide range of burn rates with low pressure index (n). High density, low temperature sensitivity and good mechanical properties constitute other essential requirements of these propellants. The salient features of such performance parameters are ... 

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