AKA: 11D58. Date: 1964-68. Number: 45 . Thrust: 83.40 kN (18,749 lbf). Unfuelled mass: 300 kg (660 lb). Specific impulse: 349 s. Burn time: 600 s. Diameter: 1.17 m (3.83 ft).
Kerosene changed from T-1 to RG-1 to achieve sufficient chamber cooling.
Engine: 300 kg (660 lb). Chamber Pressure: 78.00 bar. Area Ratio: 189. Propellant Formulation: Lox/RG-1. Thrust to Weight Ratio: 28.33.
|RD-58M Kosberg Lox/Kerosene rocket engine. Proton 8K824K / 11S824M; 11S824F; 11S86; 11S861; 17S40 stage 4 (block DM). In production. First flight 1974.|
|17D11 Kosberg Lox/Kerosene rocket engine. Buran OMS and verniers. Out of Production. Buran orbital propulsion system, including 2 x 17D12, 38 x 17D15, 8 x RDMT-200K|
|17D12 Kosberg Lox/Kerosene rocket engine. Out of Production. Version of RD-58 for Buran orbital propulsion system 17D11. Used synthetic kerosene ('Sintin') for higher specific impulse.|
|RD-58S Kosberg Lox/Kerosene rocket engine. Proton 8K82K / 11S861-01 stage 4 (block DM). Version 17D12 for Buran OMS. Version uses synthetic kerosene ('Sintin') for higher specific impulse. First flight 1994.|
|RD-58Z Kosberg Lox/Kerosene rocket engine. Zenit stage 3. Developed 1981-1990.|
|RD-58MF Kosberg Lox/Kerosene rocket engine. In Production. Multi-function variant of RD-58 for uprated upper stages applications (Zenit stage 3, Angara). Block-DM-SL for Sea-Launch may have used RD-58M.|
|Engine 11D68 detail|
Close-up view of the 11D68 Block D lunar crasher stage showing detail of the BOZ orientation/ullage thrusters that control the stage during coast, restart, and manoeuvre.
Credit: © Mark Wade