RD-0124 home
topic index
RD-0124
Credit - KBKhA
Engine Model: RD-0124. 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).

Engine Model: RD-0124-14D23. Manufacturer Name: RD-0124-14D23. Government Designation: 14D23. Designer: Kosberg. Application: Angara stage 2 verniers. Kvant-1 stage 1 vernier. Propellants: Lox/Kerosene. Thrust(vac): 298.640 kN (67,137 lbf). Isp: 331 sec. Burn time: 300 sec. Chambers: 4. Chamber Pressure: 173.50 bar. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Designed 1986-1990.

Variant of RD-0124 with shortened nozzle for sea-level operation. 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.

Engine Model: RD-0124M. Manufacturer Name: RD-0124M. Designer: Kosberg. Developed in: 1998-. Propellants: Lox/Kerosene. Thrust(vac): 294.300 kN (66,161 lbf). Isp: 348 sec. Burn time: 300 sec. Mass Engine: 360 kg (790 lb). Diameter: 1.43 m (4.69 ft). Length: 2.10 m (6.80 ft). Chambers: 1. Chamber Pressure: 161.90 bar. Thrust to Weight Ratio: 83.33. Country: Russia. Status: Developed 1998-.

Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber.

Engine Model: RD-0124M1. Manufacturer Name: RD-0124M1. Designer: Kosberg. Developed in: 1998-. Propellants: Lox/Kerosene. Thrust(vac): 294.300 kN (66,161 lbf). Isp: 359 sec. Burn time: 300 sec. Mass Engine: 393 kg (866 lb). Diameter: 1.50 m (4.90 ft). Length: 2.60 m (8.50 ft). Chambers: 1. Chamber Pressure: 157.00 bar. Thrust to Weight Ratio: 76.33. Country: Russia. Status: Developed 1998-.

Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber with larger nozzle extension compared to RD-0124M.

RD-0124 used on Rocket Stages
Bibliography:

  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
  • Novosti Kosmonavtiki, "Podprobnosti o RN 'Rus'", 1996, Issue 6, page 20.
  • Haeseler, Dietrich, CADB-information leaflets, International Aerospace Show Berlin 1998 (ILA 98) via Dietrich Haeseler.
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.

© Mark Wade, 1997 - 2008 except where otherwise noted.