Hybrid rocket engine on the methane clathrate

1Levenko, AS, 2Prysiazhnyi, VI, 3Pauk, OL, 4Drozdenko, AS
1Air-Space Agency Magellan, Kyiv
2National Center of Space Facilities Control And Test, Kyiv
3The State Enterprise “Production Association Yuzhny Machine-Building Plant named after A. M. Makarov”, Dnipropetrovsk
4Dnipropetrovsk Rocket Space Engineering College, Dnipropetrovsk National University after Oles Honchar, Dnipropetrovsk
Kosm. nauka tehnol. 2017, 23 ;(1):05-12
https://doi.org/10.15407/knit2017.01.005
Section: Space Energy, Power and Propulsion
Publication Language: Russian
Abstract: 
This article presents the results of theoretical research the possibility of establishing an efficient rocket engine on solid
methane-matter as a fuel (methane clathrate), and a liquid analog of cryogenic oxygen as the oxidizing agent (high-test
peroxide, HTP).
Keywords: hybrid-propellant rocket engine, hydrogen peroxide, methane hydrate
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