Download or read book An Experimental Investigation of Possible Aluminum Additive Contributions to Unstable Combustion in Solid Rocket Propellants written by Leland A. Watermeier and published by . This book was released on 1962 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: Composite - double base rocket propellant slabs which contained different concentrations and particle sizes of aluminum were burned in a transparent-walled chamber. The chamber was exhausted to the atmosphere. The slabs were ignited in cigarette fashion and burned under ambient nitrogen pressures of 200-800 psi. Experimental runs were made under steady flow conditions and under oscillating conditions with a siren rotating over the exhaust part. Motion pictures were taken of the burning process at high framing rates. Data on droplet burning and concentrations in various regions above the propellant surfaces were obtained from individual frames of the film. (Author).

Download or read book An Experimental Investigation of Unstable Combustion in Solid Propellant Rocket Motors written by Wilmot Grant Brownlee and published by . This book was released on 1959 with total page 302 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book U S Government Research Reports written by and published by . This book was released on 1962 with total page 1170 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Study of Instrumentation for a Space Simulation Chamber written by H. R. FARRAH and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: AD-282 519Div. 10 U (TISTM/MS) OTS price $5.60 Ballistic Research Labs., Aberdeen Proving Ground, Md. AN EXPERIMENTAL INVESTIGATION OF POSSIBLE ALUMINUM ADDITIVE CONTRIBUTIONS TO UNSTABLE COMBUSTION IN SOLID ROCKET PROPELLANTS, by Leland A. Watermeier, William P. Aungst, and Samuel P. Pfaff. July 62, 61p. incl. illus. tables, 13 refs. (BRL rept. no. 1168) (Proj. 517-06-002) Unclassified report DESCRIPTORS: *Rocket propellants, *Combus tion, Aluminum, Solid rocket propellants, Photographic analysis, Additives, Powder metals. Composite - double base rocket propellant slabs which contained different concentrations and particle sizes of aluminum were burned in a transparent-walled chamber. The chamber was exhausted to the atmosphere. The slabs were ignited in cigarette fashion and burned under ambient nitrogen pressures of 200-800 psi. Experimental runs were made under steady flow conditions and under oscillating conditions with a siren rotating over the exhaust port. Motion pictures were taken of the burning process at high framing rates. Data on droplet burning and concentrations in various regions above the propellant surfaces were obtained from individual frames of the film. (Author).

Download or read book Technical Abstract Bulletin written by Defense Documentation Center (U.S.) and published by . This book was released on 1963 with total page 824 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of the Effect of Aluminum Size and Loading on the Burning Rate of Solid Propellants Under Acceleration written by G. Burton Northam and published by . This book was released on 1969 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical Publications Announcements with Indexes written by United States. National Aeronautics and Space Administration and published by . This book was released on 1962 with total page 1556 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Ninth Symposium International on Combustion written by Sam Stuart and published by Elsevier. This book was released on 2013-09-11 with total page 1118 pages. Available in PDF, EPUB and Kindle. Book excerpt: Ninth Symposium (International) on Combustion covers the proceedings of the Ninth Symposium (International) on Combustion, held at Cornell University in Ithaca, New York on August 27 to September 1, 1962, under the auspices of the Combustion Institute. The book focuses on the processes and reactions involved in combustion. The selection first offers information on flame strength of propane-oxygen flames at low pressures in turbulent flow and mixing and flow in ducted turbulent jets. Topics include radial profile of the jetting velocity, radial growth of the jet, and mixing zones of a ducted jet. The text then elaborates on turbulent flame studies in two-dimensional open burners; turbulent mass transfer and rates of combustion in confined turbulent flames; and flame stabilization in a boundary layer. The publication examines the theoretical study of properties of laminar steady state flames as a function of properties of their chemical components and spectra of alkali metal-organic halide flames. The text then takes a look at the thermal radiation theory for plane flame propagation in coal dust clouds; flame characteristics of the diborane-hydrazine system; and studies of the combustion of dimethyl hydrazine and related compounds. The selection is a dependable reference for readers interested in the processes and reactions involved in combustion.

Download or read book A Theoretical and Experimental Comparison of Aluminum as an Energetic Additive in Solid Rocket Motors with Thrust Stand Design written by Derek Damon Farrow and published by . This book was released on 2011 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt: The use of aluminum as an energetic additive in solid rocket propellants has been around since the 1950's. Since then, much research has been done both on the aluminum material itself and on chemical techniques to properly prepare aluminum particles for injection into a solid propellant. Although initial interests in additives were centered on space limited applications, performance increases opened the door for higher performance systems without the need to remake current systems. This thesis aims to compare the performance for aluminized solid rocket motors and non-aluminized motors, as well as focuses on design considerations for a thrust stand that can be created easily at low cost for initial testing. A theoretical model is created for predicting propellant performance and the results are compared with experimental data taken from the thrust stand as well as existing data. What is seen at the end of testing is the non-aluminized grains follow the same trends as previously conducted tests and firings. The aluminized grains follow their expected trend but at a lower performance level due to grain degradation. However, the aluminized grains still show a specific impulse increase of 6%-23% over the nonaluminized grains.

Download or read book Keywords Index to U S Government Technical Reports written by United States. Department of Commerce. Office of Technical Services and published by . This book was released on 1962 with total page 990 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Keywords Index to U S Government Technical Reports permuted Title Index written by United States. Department of Commerce. Office of Technical Services and published by . This book was released on 1962 with total page 860 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation of Unstable Combustion in Sold Propellant Rocket motors by W Grant Brownlee and Frank E Marble written by W. Grant Brownlee and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical Publications Announcements written by United States. National Aeronautics and Space Administration and published by . This book was released on 1962 with total page 624 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Aluminum on Solid Propellant Combustion Instability written by C. L. Oberg and published by . This book was released on 1966 with total page 103 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical and experimental program to investigate the effects of aluminum on solid-propellant combustion instability was conducted. The analytical phase was devoted to a determination of the energy dissipation rate associated with possible damping mechanisms. The relative magnitude of these damping mechanisms are developed and discussed. The effects of aluminum on nonacoustic instability were also considered in the analytical phase. It is shown that the nonacoustic problem could be treated by employing conventional acoustic methods. This information was used to propose a mechanism for quasi-periodic shedding of aluminum from the burning surface. This analysis was followed by an experimental phase. Measurements were made employing a T-burner in which a pressure pulse could be generated. Measurements were made on propellants containing up to 15-percent aluminum at mean-pressure levels up to 600 psi and over a frequency range of 200 to 2000 cps. A discussion is presented of the results of these experiments, particularly with respect to the damping mechanisms considered in the analysis. Some information applicable to nonacoustic instability was obtained as well. (Author).

Download or read book Technical Publications Announcements with Indexes written by United States. National Aeronautics and Space Administration and published by . This book was released on 1962 with total page 796 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation of Chemical Reaction Between Propellant Tank Material and Rocket Fuels Or Oxidizers when Impacted by Small High velocity Projectiles written by Robert P. Dengler and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation of Longitudinal Combustion Instability in a Rocket Motor Using Premixed Gaseous Propellants written by Roy Pelmas and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Longitudinal combustion instability in a premixed gaseous propellant rocket motor was studied. The chamber length was varied continuously between 3 and 48 inches. A porous media injection plate was used to approximate uniform one-dimensional propellant injection. A showerhead injector was used to determine the influence of combustion zone recirculation on combustion instability. Two propellant combinations were used, methane (40% O + 60% N) and H - air. Results, in the form of instability maps, are presented for combination of the propellants and injection schemes. The two existing gas rocket instability driving mechanisms are presented and discussed. The influence of chemical kinetics on the instability seems to be unimportant and the driving mechanism is an oscillating heat transfer to the injector couples with a pressure oscillation in the combustion chamber to produce unstable combustion. (Author).