RD-0124

RD-0124
Credit - KBKhA

Manufacturer Name: RD-0124. Government Designation: 14D451M. Other Designations: 14D23. Designer: Kosberg. Developed in: 1993-. Application: Rus Soyuz 2 stage 3. Propellants: Lox/Kerosene. Thrust(vac): 294.300 kN (66,161 lbf). Isp: 359 sec. Isp (sea level): 331 sec. Burn time: 300 sec. Mass Engine: 480 kg (1,050 lb). Diameter: 2.40 m (7.80 ft). Length: 1.58 m (5.17 ft). Chambers: 4. Chamber Pressure: 162.00 bar. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 62.50. Country: Russia. Status: In development. First Flight: 2001. Last Flight: 2006. Flown: 19.

Engine to succeed RD-0110 in second stage of Soyuz-2/Rus LV. Uses staged combustion; chamber pressure increased from 70 to 160 atmospheres, specific impulse from 326 to 359 seconds, payload by 950 kg from current 6900/7200 kg (Plesetsk/Baikonur).

RD-0124 used on Rocket Stages

Used on stage: Angara A-2. on launch vehicle: Angara 1.2.

Used on stage: Angara A-2. on launch vehicle: Angara 3A.

Used on stage: Soyuz ST-2. on launch vehicle: Soyuz FG.

Used on stage: Soyuz ST-2. on launch vehicle: Soyuz ST.

Used on stage: Soyuz ST-2. on launch vehicle: Soyuz ST / Fregat ST.

Bibliography and Further Reading

Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...

Haeseler, Dietrich, CADB-information leaflets, International Aerospace Show Berlin 1998 (ILA 98) via Dietrich Haeseler.

Novosti Kosmonavtiki, "Podprobnosti o RN 'Rus'", 1996, Issue 6, page 20.

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