Encyclopedia Astronautica
RD-0110MD



wrd0110m.jpg
RD-0110M
Credit: KBKhA
Kosberg Lox/LNG rocket engine. 245 kN. Developed 1994-on. Prototype engine for tests with propellants LOX/liquified natural gas. Tests performed from 30 April 1998 on, test duration 20s.

Chambers: 4. Chamber Pressure: 54.00 bar. Area Ratio: 82.2.

Status: Developed 1994-on.
Thrust: 245.00 kN (55,078 lbf).
Burn time: 20 s.
First Launch: 1994-.

More... - Chronology...


Associated Countries
See also
Associated Manufacturers and Agencies
  • Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. More...

Associated Propellants
  • Lox/LNG Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Liquefied natural gas - mainly methane,with traces of sulfur, etc. More...

Home - Browse - Contact
© / Conditions for Use