Burning, solid propellant

Scanning Electron Microscopy in the Study of Solid Propellant Combustion. Part 111. The Surface Structure and Profile Characteristics of Burning Composite Solid Propellants , NavWeps-Cent r TP 5142-Part 3 (1971) 48) B.T. 

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

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... 

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... 

Evolution did not use this element, only in certain plants is it important as a trace element. The element became well-known because of heat-resistant borosilicate glasses. Boranes are chemically interesting as B-H bonds react very specifically. Perborates are used in laundry detergents (Persil). The hardness of cubic boron nitride approaches that of diamond. Amorphous (brown) boron burns very quickly and gives off much heat and is therefore used in solid-propellant rockets and in igniters in airbags. 

Fizz zone. In the burning of propellants, the zone in which the solid propellant is converted to gaseous intermediates (see p. 182). 

Nonsteady Burning and Combustion Stability of Solid Propellants, Hrsg. De Luca, L., Price, E. W., Summerfield, M., Progress in Astronautics and Aeronautics, Vol. 143, AIAA, Washington, DC, USA, 1992... 

Diffusion flames can best be described as the combustion state controlled by mixing phenomena—that is, the diffusion of fuel into oxidizer, or vice versa—until some flammable mixture ratio is reached. According to the flow state of the individual diffusing species, the situation may be either laminar or turbulent. It will be shown later that gaseous diffusion flames exist, that liquid burning proceeds by a diffusion mechanism, and that the combustion of solids and some solid propellants falls in this category as well. 

Komai, L, Kobayashi, K., and Kato, K., Burning Rate Characteristics of Glycidyl Azide Polymer (GAP) Fuels and Propellants, Solid Propellant Chemistry, Combustion, and Motor Interior Ballistics (Ed. Yang, V, Brill, T. B., and Ren, W.-Z.J, Progress in Astronautics and Aeronautics, Vol. 185, Chapter 2.9, AlAA, Virginia, 2000. 

Steinz, J. A., Stang, P. L., and Summer-field, M., The Burning Mechanism of Ammonium Perchlorate-Based Composite Solid Propellants, Aerospace and Mechanical Sciences Report No. 830, Princeton University, 1969. 

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. 

Lengelle, G., Bizot, A., Duterque, J., and Trubert, J. F., Steady-State Burning of Homogeneous Propellants, Fundamentals of Solid-Propellant Combustion (Eds. Kuo, K. K., and Summerfield, M.), Progress in Astronautics and Aeronautics, Vol. 90, Chapter 7, AlAA, New York (1984). 

Steinberger, R., and Carder, K. E., Mechanism of Burning of Nitrate Esters, Bulletin of the 10 th Meeting of the JANAF Solid Propellant Center, Dayton, June 1954, pp. 173-187. 

Summerfield, M., Sutherland, G. S., Webb, W. J., Taback, H. J., and Hall, K. P., The Burning Mechanism of Ammonium Perchlorate Propellants, ARS Progress in Astronautics and Rocketry, Vol. 1, Solid Propellant Rocket Research, Academic Press, New York (1950), pp. 141-182. 

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). 

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. 

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