RD-181
 |
|
| Country of origin |
 Russia
|
|---|---|
| Date | 2001 |
| Designer | NPO Energomash |
| Manufacturer | NPO Energomash / Proton-PM (in transition) |
| Application | Main engine |
| Predecessor | RD-170 |
| Status | In use |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 |
| Mixture ratio | 2.6 |
| Cycle | Oxidizer-rich Staged combustion |
| Configuration | |
| Nozzle ratio | 37 |
| Performance | |
| Thrust (vac.) | 2.090 MN (470,000 lbf) at 100% throttle |
| Thrust (SL) | 1.920 MN (432,000 lbf) at 100% throttle |
| Throttle range | 27–105% |
| Thrust-to-weight ratio | 89 |
| Chamber pressure | 25,800 kPa (3,740 psi) |
| Isp (vac.) | 337 s (3.30 km/s) |
| Isp (SL) | 310.7 s (3.047 km/s) |
| Burn time | 325 s (Angara A5 core stage) |
| Gimbal range | 8° |
| Dimensions | |
| Length | 4,000 mm (160 in) |
| Diameter | 1,450 mm (57 in) |
| Dry weight | 2,290 kg (5,050 lb) |
| References | |
| References | |
The RD-191 is a high performance single-combustion chamber rocket engine, developed in Russia. It is derived from the RD-170 originally used in the Energia launcher.
The RD-191 is fueled by a kerosene / LOX mixture and uses an oxygen-rich staged combustion cycle.
Burn ignition is provided by a chemical method, by feeding into the combustion chamber special starting fuel which is self-igniting on contact with liquid oxygen. The engine is capable of throttling down to 30% of nominal thrust; the design also allows for a short-duration enhanced thrust (up to 105% of nominal level) in emergency situations. A Cardan suspension provides for yaw and pitch controls by gimballed thrust deflection up to 8 degrees.
A modern design, the engine incorporates sensors monitoring burn conditions. The measurements are used for telemetry and an emergency protection system.
The engine fulfills two additional functions, heating helium gas for pressurization of propellant tanks and generating hydraulic power for hydraulic actuators to deflect the nozzle and aerodynamic rudders.
On September 5, 2008, the creator of the engine, NPO Energomash, reported that the engine has completed the full cycle of development and burn tests and is ready for manufacturing and delivery. The primary launch vehicle utilizing this engine is the Angara rocket, currently being developed.
As of 2010, the engine has passed all development phases and its nine prototypes have accumulated over 23,000 seconds in 105 firing tests, with one of them reaching the maximum running time of 3,635 seconds in 12 tests. Currently, interdepartmental tests are under way and manufacturing of the engines for flight development tests has started. The flight tests will begin with a launch of the Angara-1.2 light-class rocket, and then of the Angara-A5 heavy launcher. Despite problems with funding, work on the RD-191 engine is in line with the Angara rocket family's master schedule.
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Wikipedia