Thermal emission characteristics of combustion products from rocket engines. Part 2. Investigating the influence of various factors for SPRE
V.A. Kuzmin, I.A. Zagrai, N.A. Shmakova
Vyatka State University, Kirov,Russia
Keywords: solid-propellant rocket engine, thermal radiation, heterogeneous combustion products, emission characteristics, radiation energy flux density, emissivity factor
Abstract
Computational experiments in the field of thermal radiation emitted by combustion products of rocket engines allow tracing the effect of determining factors on the emission characteristics, which serves to plan, predict, and interpret a physical experiment. The paper considers the influence of the condensed phase (aluminum oxide particles), the gas phase and its individual components (H2O and CO2) on spectral and integral radiation energy flux densities and emissivity factors in various sections of the flow of heterogeneous combustion products of a model solid-propellant rocket engine (SPRE). A comparison of the emission characteristics of incomplete combustion products and combustion products is performed for the chamber and initial section of the plume of the first-stage SPRE of Trident II (D5). The calculations of spectral radiation intensity of an initial section of the plume are compared with the results of other authors.
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