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RD-0242
Credit - KBKhA
Engine Model: RD-0242. Manufacturer Name: RD-0242. Designer: Kosberg. Developed in: 1977-83. Application: sea-based missile booster stage (Burlak ?). Propellants: N2O4/UDMH. Thrust(vac): 123.600 kN (27,786 lbf). Isp: 303 sec. Burn time: 60 sec. Mass Engine: 120 kg (260 lb). Diameter: 0.27 m (0.89 ft). Length: 0.88 m (2.89 ft). Chambers: 1. Chamber Pressure: 196.20 bar. Thrust to Weight Ratio: 105.03. Country: Russia. Status: Developed 1977-83.

First concept planned N2O4/kerosene as propellant, but changed to N2O4/UDMH. 50 engines ready for sale. Single ignition, 297 development tests, max. duration 420 s.

Engine Model: RD-0242-HC. Manufacturer Name: RD-0242-HC. Designer: Kosberg. Developed in: 1998-. Propellants: Lox/Kerosene. Thrust(vac): 125.000 kN (28,101 lbf). Isp: 312 sec. Mass Engine: 120 kg (260 lb). Chambers: 1. Chamber Pressure: 196.20 bar. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 106.21. Country: Russia. Status: Developed 1998-.

Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

Engine Model: RD-0242M. Manufacturer Name: RD-0242M. Designer: Kosberg. Developed in: 1998-. Propellants: N2O4/MMH. Thrust(vac): 98.100 kN (22,054 lbf). Isp: 336 sec. Burn time: 600 sec. Mass Engine: 185 kg (407 lb). Diameter: 0.80 m (2.62 ft). Length: 1.60 m (5.24 ft). Chambers: 1. Chamber Pressure: 153.00 bar. Thrust to Weight Ratio: 54.07. Country: Russia. Status: Design concept 1998-.

Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH (adaptation to western market ?). Reusable for 6 ignitions total. Throttling to 80%. 15 ignitions tested with one single engine.

Engine Model: RD-0242M1. Manufacturer Name: RD-0242M1. Designer: Kosberg. Developed in: 1998-. Propellants: N2O4/MMH. Thrust(vac): 98.100 kN (22,054 lbf). Isp: 343 sec. Burn time: 600 sec. Mass Engine: 229 kg (504 lb). Diameter: 1.25 m (4.10 ft). Length: 2.34 m (7.67 ft). Chambers: 1. Chamber Pressure: 153.00 bar. Thrust to Weight Ratio: 43.68. Country: Russia. Status: Design concept 1998-.

Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH (adaptation to western market ?). Reusable for 6 ignitions total. Throttling to 80%.

Bibliography:

  • Burya article, Lavochkin web site.
  • Haeseler, Dietrich, CADB-information leaflets, International Aerospace Show Berlin 1998 (ILA 98) via Dietrich Haeseler.
  • Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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