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RD-120


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A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z RD-120 Glushko LOx/Kerosene rocket engine. Zenit stage 2. In production. High altitude engine used in the Zenit second stage. First production Russian engine to be test fired in the United States (3 test burns were made). First flight 1985.

AKA: 11D123. Status: In production. Date: 1976-85. Number: 60 . Thrust: 833.00 kN (187,265 lbf). Unfuelled mass: 1,125 kg (2,480 lb). Specific impulse: 350 s. Burn time: 315 s. Height: 3.87 m (12.70 ft). Diameter: 1.95 m (6.38 ft).

Mass is wet mass.

Engine: 1,125 kg (2,480 lb). Chamber Pressure: 162.80 bar. Area Ratio: 106.7. Thrust to Weight Ratio: 75.55. Oxidizer to Fuel Ratio: 2.6.

Subtopics RD-146 Glushko LOx/Kerosene rocket engine. Angara stage 2. Design concept 1993-on. Sea-level variant of RD-120 engine. Proposed in initial study for Angara by RKK Energia in1993. Kerosene RG-1. RD-120K Glushko LOx/Kerosene rocket engine. Soyuz M stage 1, 2. Proposed for X-34. Sea-level variant of RD-120. As of 1996 RD-120 prototype with 1.8 m diameter had been built, development time estimated for three years. RD-182 Glushko LOx/LCH4 rocket engine. Riksha (-1, -2) stage 1. Developed 1994-. Methane variant of RD-120K engine. Thrust range and Isp range due to throat diameter and chamber pressure. Gimbaling +/- 6 degree in two planes. RD-169 Glushko LOx/LCH4 rocket engine. Riksha-0 stage 1. Design concept 1990's. LOX/Methane engine derived from RD-120. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead. RD-120M Glushko LOx/Kerosene rocket engine. PacAstro-2 stage 1. Out of Production. Sea-level variant of RD-120 engine, similar to RD-120K. Gimbaling +/- 6 degree in two planes. RD-185 Glushko LOx/LCH4 rocket engine. Riksha-0 stage 2. Developed 1996-. Upper stage version of RD-169 with larger nozzle. Gimbaling +/- 4 degree in two planes. RD-190 Glushko LOx/LCH4 rocket engine. Riksha-0 stage 1. Developed 1996-. The RD-190 consists of 6 RD-169 engines. Each chamber can be gimbaled individually in two planes by +/- 8 degree. RD-182M Glushko LOx/LNG rocket engine. Vozdushnyy Start stage 1. Developed 1998-. Variant of RD-182 engine for liquid natural gas (mainly CH4). Proposed initial candidate for project Vozdushnyy Start of Kompomash. RD-120.01 Glushko LOx/Kerosene rocket engine. Design concept. RD-120.03 Glushko LOx/Kerosene rocket engine. Design concept. Country: Russia. Engines: RD-120. Propellants: Lox/Kerosene. Stages: Zenit-B. Agency: Glushko bureau. Bibliography: 287, 325, 347, 412, 7500. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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