In today's article we are going to delve into the fascinating world of RD-0120, exploring its various aspects, applications and meanings. RD-0120 is a topic that has aroused the interest of countless people over time, its relevance has been maintained over the years and it has been the subject of debate and analysis in different areas. On this occasion, we will delve into its history, its current implications and its impact on society. We will also examine the different perspectives that exist on RD-0120 and how these have evolved over time. We will begin by exploring its origin, going through its different interpretations until reaching its relevance today. Join us on this tour of RD-0120 and discover the importance that this topic has in our daily lives.
Country of origin | Soviet Union |
---|---|
Date | 1976-1987 |
First flight | 1987-05-15 |
Last flight | 1988-11-15 |
Designer | OKB-154 |
Manufacturer | Voronezh Mechanical Plant |
Application | Sustainer engine |
Associated LV | Energia |
Successor | RD-0122 |
Status | Retired |
Liquid-fuel engine | |
Propellant | LOX / LH2 |
Mixture ratio | 6.0 |
Cycle | Staged сombustion |
Configuration | |
Chamber | 1 |
Nozzle ratio | 85.70 |
Performance | |
Thrust, vacuum | 1,961.3 kN (440,900 lbf), 106% |
Thrust, sea-level | 1,526 kN (343,000 lbf), 106% |
Thrust-to-weight ratio | 57.93, vac., 106% thrust |
Chamber pressure | 21.9 MPa (3,180 psi) |
Specific impulse, vacuum | 455 s (4.46 km/s) |
Specific impulse, sea-level | 353.2 s (3.464 km/s) |
Burn time | 500 s |
Gimbal range | ±7° |
Dimensions | |
Length | 4,550 mm (179 in) |
Diameter | 2,420 mm (95 in) |
Dry weight | 3,450 kg (7,610 lb) |
Used in | |
Energia core stage | |
References | |
References |
The Soviet RD-0120 (also designated 11D122) was the Energia core rocket engine, fueled by LH2/LOX, roughly equivalent to the Space Shuttle Main Engine (SSME). These were attached to the Energia core rather than the orbiter, so were not recoverable after a flight, but created a more modular design (the Energia core could be used for a variety of missions besides launching the shuttle). The RD-0120 and the SSME have both similarities and differences. The RD-0120 achieved a slightly higher specific impulse and combustion chamber pressure with reduced complexity and cost (but it was single-use), as compared to the SSME. It uses a fuel-rich staged combustion cycle and a single shaft to drive both the fuel and oxidizer turbopumps. Some of the Russian design features, such as the simpler and cheaper channel wall nozzles, were evaluated by Rocketdyne for possible upgrades to the SSME. It achieved combustion stability without the acoustic resonance chambers that the SSME required.