Problems and ways of their solutions in the development of a lowthrust liquid jet engine for a stage 3 liquid jet system of «Cyclone-4» launch vehicle
Heading:
| 1Durachenko, VM, 1Shpak, AV, 1Kolesnychenko, SA, 1Aheyeva, LI, 1Dolinkevich, AS, 1Unchur, KO 1Yangel Yuzhnoye State Design Office, Dnipro, Ukraine |
| Space Sci. & Technol. 2020, 26 ;(1):18-29 |
| https://doi.org/10.15407/knit2020.01.018 |
| Publication Language: Russian |
Abstract: The article deals with the issues of a low-thrust liquid jet engine as a part of stage 3 liquid jet system of “Cyclone-4” launch vehicle development. Features of the developed engine are its efficiency at low pressure in the chamber, operation stability during hydraulic shocks and pressure drops in the Liquid Propellant Rocket Thrusters (LPRT) inlet at the cruise engine start-up and stop, as well as pressurizing gas presence in propellants. We set out main problematic issues encountered during the designing and development test of this engine as well as describe the results of the qualification test.
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| Keywords: firing tests, liquid jet engine, liquid jet system, main engine, thrust |
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9. Poluhin D., Oreschenko V., Morozov V. (1987). Launch vehicles and spacecraft with LPRT propulsion system pneumohydrosystems qualification. Moscow.