Probe Method for Sampling Solid-Propellant Combustion Products at Temperatures and Pressures Typical of a Rocket Combustion Chamber
A. G. Tereshenko, O. P. Korobeinichev, P. A. Skovorodko*, A. A. Paletsky, E. N. Volkov
Institute of Chemical Kinetics and Combustion,
Siberian Division, Russian Academy of Sciences, Novosibirsk 630090; korobein@ns.kinetics.nsc.ru.
*Institute of Thermal Physics,
Siberian Division, Russian Academy of Sciences, Novosibirsk 630090
Abstract
The paper describes a new probe method for determining the quantitative composition of solid-propellant combustion products at temperatures of 25003200 K and pressures of 48 MPa under conditions typical of rocket motor conditions. A twostep probe is described, which allows a sample to be frozen without passing through the main shocks inside the sampler. The gas dynamics and the kinetics of chemical reactions were simulated to asses the correctness of sampling. It is shown that during sampling from a flame, the relative change in concentrations for most of the stable components does not exceed 3, and for H2 and O2, it does not exceed 12. The method permits additional operations with a sample, in particular, separation of CO and N2 with subsequent analysis on a timeofflight mass spectrometer. The CO and CO2 concentrations in the combustion products of the model composite solid propellant ammonium dinitramide ADN with polycaprolactone pCLN were determined at a pressure of 4 MPa. P. 81-91
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