Solid Propellant Combustion in High-Velocity Gas Flow (Review)
V. A. Arkhipov1, V. E. Zarko2, I. K. Zharova1, A. S. Zhukov1, E. A. Kozlov1, D. D. Aksenenko3, A. V. Kurbatov3
1Tomsk State University, Tomsk, 634050 Russia
2Voevodsky Institute of Chemical Kinetics and Combustion, Siberian Branch of Russian Academy of Sciences, Novosibirsk 630090 Russia
3Altai Federal Research and Production Center, Biisk, 659323 Russia
Keywords: твердое топливо, эрозионное горение, коэффициент эрозии, сверхзвуковой поток, параметр Победоносцева, параметр Вилюнова, solid fuel, erosive burning, erosion coefficient , supersonic flow, Pobedonostsev parameter, Vilyunov parameter
Abstract
Combustion of solid propellant charges in rocket propulsion systems usually occurs under conditions of intense flow of combustion products (solid rocket motor), gaseous oxidizer (hybrid rocket motor) or air (ramjets and air-breathers).This causes the so-called erosive burning effects, resulting in a change in the burning law under the influence of the gas flow. The main approaches to modeling the erosive burning of solid fuels in high-velocity gas flow are considered. Methods for the criterial description of the results of experimental studies of the erosive burning of solid fuels under transonic and supersonic flow conditions are analyzed.
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