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RD-0106

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RD-0106O Credit: KBKhA

AKA: 8D715. Date: 1959-62. Number: 69 . Thrust: 304.00 kN (68,341 lbf). Specific impulse: 330 s. Burn time: 140 s.

Chambers: 4. Propellant Formulation: Lox/T-1.

RD-0107 Kosberg LOx/Kerosene rocket engine. R-9, Molniya 8K78, Voskhod 11A57 stage 3. Out of Production. Gas generator cycle.

RD-0108 Kosberg LOx/Kerosene rocket engine. Voskhod 11A57, Molniya 8K78 stage 3. First flight 1960.

RD-0110 Kosberg LOx/Kerosene rocket engine. Soyuz 11A511, Molniya-M 8K78M. Precursor RD-0107 used in 11A57 Voskhod stage 2. Modified to increase reliability. First flight 1964.

RD-0124 Kosberg LOx/Kerosene rocket engine. In development. Engine to succeed RD-0110 in second stage of Soyuz. Used staged combustion; chamber pressure increased from 70 to 160 bar, specific impulse from 326 to 359 seconds. First flight 2001. Proposed for small launcher Kvant-1 by RKK Energia for stage 1 steering engine. Also proposed by RKK Energia in initial studies in 1993 for Angara upper stage.

RD-0110MD Kosberg LOx/LNG rocket engine. Developed 1994-on. Prototype engine for tests with propellants LOX/liquefied natural gas. Tests performed from 30 April 1998 on, test duration 20s.