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astronautix.com RD-858
RD-858
RD-858

Credit: Dietrich Haeseler. 36,613 bytes. 462 x 362 pixels.

Manufacturer Name: RD-858. Designer: Yangel. Developed in: 1964-72. Application: LK lunar lander main engine. Used on spacecraft: LK. Propellants: N2O4/UDMH Thrust(vac): 2,050 kgf. Thrust(vac): 20.10 kN. Isp: 315 sec. Burn time: 470 sec. Mass Engine: 53 kg. Diameter: 1.1 m. Length: 1.1 m. Chambers: 1. Chamber Pressure: 78.50 bar. Oxidizer to Fuel Ratio: 2.03. Country: Ukraine. Status: Hardware. References: 348 .

The LK used a propulsion system designed by the Yangel Design Bureau. This consisted of the main engine RD-858 and the back-up engine RD-859: 

Engine                      RD-858                   RD-859
No of chambers:                1                      2
Operating regime    nominal         throttled            
Thrust in vacuum    2050 kg         858 kg           2045 kg
                    20104 N         8414 N           20055 N
spec. vac. impulse  315 s           285 s            312 s
                    3089 Ns/kg      2795 Ns/kg       3060 Ns/kg
Mixture ratio O/F   2.03            1.6              2.0
Thrust variation    +/- 9.8 %       +/- 35 %         +/- 9.8 %
Mixture ratio deviation        3 %                   3 %
Chamber pressure    80 kg/cm^2      33.8 kg/cm^2     80 kg/cm^2   
                    78.5 bar        33.15 bar        78.5 bar
Operation time      50 + 350 s      100 s            400 s
Propellants               N2O4 / UDMH                N2O4 / UDMH
Engine mass                  53 kg                   57 kg
Propulsion system height                  1090 mm
Propulsion system width                   1102 mm
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Last update 12 March 2001.
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