Научная электронная библиотека ULRICH'S Periodicals Directory

Сибирский государственный университет
науки и технологий имени академика М.Ф. Решетнева

Сибирский аэрокосмический журнал
ISSN 2712-8970 (Print) ISSN 2782-5760 (on-line)

Сведения об образовательной организации

UDK 621.472
USE OF DIFFERENT OXIDIZERS FOR AFTERBURNING OF HYDROGEN HEATED BY SOLAR ENERGY IN ROCKET ENGINE
S. L. Finogenov*, A. I. Kolomentsev, O. I. Kudrin
Moscow Aviation Institute (National research university) “MAI” 4, Volokolamskoe shosse, А-80, GSP-3, Moscow, 125993, Russian Federation *E-mail: sfmai2015@mail.ru
Solar thermal propulsion (STP) with heating of hydrogen in high-temperature “concentrator–absorber” system with the possibility of its subsequent afterburning with cold oxidizer is considered. Such components as fluorine and hydrogen peroxide are suggested as oxidizers. These oxidizers create high-energetic propellant compounds with hydro-gen and have high stoichiometric ratios, that allow to reduce required overall dimensions of solar energy mirror con-centrator, as one of the most critical elements of STP. Results of parameters optimization of concentrator-absorber sys-tem by criterion of maximum of payload weight in the task of payload injection into geostationary orbit for the cases of isothermal (uniform) single-stage absorber and non-isothermal absorber with heating stages (non-uniform heating) use with reference to use of metal or film concentrator are presented. It is shown that requirements to accuracy of concen-trator and its tracking system to the Sun are rather high. Decrease of dimensions of solar concentrator at afterburning of heated hydrogen simplifies its creation and improves operation in space conditions, in particular improves inertial characteristics of the STP as a part of space vehicle and simplify orientation to the Sun. Comparative characteristics of the STP use as space vehicle subsystem for the cases of metal and film concentrators are presented at isothermal and not isothermal heating of hydrogen and its afterburning by the considered oxidizers. The required area of concentrator in the case of fluorine use can be significantly reduced (up to 25 % and more) in comparison with oxygen-hydrogen STP. Use of hydrogen peroxide in some tasks allows 10…12 % reduction of the concentrator area as compared to oxy-gen-hydrogen STP. It is shown that payload injected into geostationary earth orbit, in the case of fluorine-hydrogen STP with film concentrator and non-uniform heating, can be increased up to 70 % and higher in comparison with the use of oxygen-hydrogen liquid propellant rocket engine.
Keywords: solar thermal propulsion, hydrogen afterburning, concentrator-absorber system, oxidizer, fluorine, hydrogen peroxide.
References

References

 

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Finogenov Sergei Leonardovich – Senior Researcher, Dept. 202 “Rocket Engines”, Moscow Aviation Institute (National Research University). E-mail sfmai2015@mail.ru.

Kolomentsev Alexander Ivanovich – Cand. Sc., Professor, Dept. 202 “Rocket Engines”, Moscow Aviation Institute (National Research University). E-mail sfmai2015@mail.ru.

Kudrin Oleg Ivanovich – Dr. Sc., Professor, Academician, Russian Academy of Natural Sciences, Professor of Dept. 202 “Rocket Engines”, Moscow Aviation Institute (National Research University).