RD-170
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RD-170
RD-170
RD-170 rocket engine.jpg
RD-170 rocket engine model on exhibition in Saint Petersburg's Museum of Space and Missile Technology.
Country of originSoviet Union/Russian Federation
First flight1985-04-13
ManufacturerNPO Energomash
ApplicationMain Engine
Associated L/VEnergia
SuccessorRD-171M
StatusActive
Liquid-fuel engine
PropellantLOX / RG-1
Mixture ratio2.63
CycleOxidizer-rich staged combustion
Configuration
Chamber4
Nozzle ratio36.87
Performance
Thrust (vac.)7,904 kN (1,777,000 lbf)
Thrust (SL)7,257 kN (1,631,000 lbf)
Throttle range100-40%
Thrust-to-weight ratio75:1
Chamber pressure24.52 MPa (3,556 psi)
Isp (vac.)337 s (3.30 km/s)
Isp (SL)309 s (3.03 km/s)
Burn time150 seconds
Dimensions
Length4.0 m (160 in)
Diameter3.8 m (150 in)
Dry weight9,750 kg (21,500 lb)
Used in
Energia
References
References[1][2][3][4]

The RD-170 (-170, -170, Rocket Engine-170) is the world's most powerful multi-combustion chambered liquid-fuel rocket engine, designed and produced in the Soviet Union by NPO Energomash for use with the Energia launch vehicle. The engine burns the Russian equivalent of RP-1 fuel and LOX oxidizer in four combustion chambers, all supplied by one single-shaft, single-turbine turbopump rated at 170 MW (230,000 hp) in a staged combustion cycle.[3][5] By comparison, the Rocketdyne F-1 engine (five of which were used on each Saturn V) is the world's most powerful single-combustion chamber rocket engine.

Shared turbopump

Several Soviet and Russian rocket engines use the approach of clustering small combustion chambers around a single turbine and pump. During the early 1950s, many Soviet engine designers, including Valentin P. Glushko, faced problems of combustion instability while designing bigger thrust chambers. At that time, they solved the problem by using a cluster of smaller thrust chambers.

Variants

RD-170

The RD-170 engine featured four combustion chambers and was developed for use on the Energia launch vehicle - both the engine and the launch vehicle were in production only for a short time.

RD-171

RD-171 model

Building on the technology from the Energia launch vehicle the Zenit (rocket family) was developed, which uses a RD-170 variant, the RD-171. While the RD-170 had nozzles which swiveled on one axis only, the RD-171 swivels on two axes.[2] RD-171 was intended to be used on Zenit rocket. Models called the RD-172[] and RD-173 were proposed upgrades that would provide additional thrust, and the RD-173 proposal was finalized as the RD-171M upgrade in 2006.[2]

RD-171MV

A modification of RD-171M being developed for the Irtysh rocket. Unlike RD-171M it's completely made from Russian components and features a new control system.[6] First test sample was manufactured in early 2019[7]

Dual-chamber derivative

The RD-180 uses only two combustion chambers instead of the four of the RD-170. The RD-180 used on the Atlas V replaced the three engines used on early Atlas rockets with a single engine and achieved significant payload and performance gains. This engine had also been chosen to be the main propulsion system for the first stage of the now cancelled Russian Rus-M rocket.[8]

Single-chamber derivative

The RD-191 is a single-chamber version used in the Russian Angara rocket.[9] Variants of RD-191 include RD-151 in South Korean Naro-1 rocket,[10]RD-181 in American Orbital ATK Antares rocket, and the proposed RD-193 for the Soyuz-2-1v project.[11]

Proposed variants

On 28 July 2011, NPO Energomash summarised the results of the work on Rus-M rocket engine and considered the possibility of construction several new variants of RD-170 family engines.[12] According to the information, new and proposed variants will be marked as:

  • RD-180M for manned Atlas V rocket (Not required, current RD-180 meets manned Atlas V requirements.)[13]
  • RD-180V for Rus-M rocket.
  • RD-175 with 9800 kN thrust for proposed Energia-K rocket.[14]

In 2017, Director General of RKK Energia Vladimir Solntsev referred to a "simplified" and "cheaper" version of the RD-171 engine in connection with the Soyuz-5 (Sunkar) project.[15]

Specifications

  • 4 combustion chambers, 4 nozzles
  • 1 set of turbines and pumps; turbine produces approximately 257,000 hp (192 MW); equivalent to the power output of 3 nuclear-powered icebreakers
  • Ignition: Pyrophoric start-up fuel capsule (triethylaluminium)[16]
  • Vacuum thrust: 7,887 kN (1,773,000 lbf)
  • Vacuum Isp: 338 s (3.31 km/s)
  • Sea-level Isp: 309 s (3.03 km/s)
  • Weight: 9,750 kilograms (21,500 lb)
  • Thrust-to-weight ratio: 82

See also

References

  1. ^ "RD-171M". NPO Energomash. Retrieved .
  2. ^ a b c Ponomarenko, Alexander. " -170 (11?521) ? -171 (11?520)" [RD-170 (11D521) and RD-171 (11D520)] (in Russian). Retrieved .
  3. ^ a b Wade, Mark. "RD-170". Encyclopedia Astronautica. Retrieved .
  4. ^ Krebs, Gunter Dick (2015-09-15). "Zenit family". Gunter's Space Page. Retrieved .
  5. ^ "South Korea to launch first space rocket on Aug. 19". Yonhap News Agency. 2009-08-25. Retrieved .
  6. ^ "? -171 " [Energomash has made a reference model of RD-171MV]. NPO Energomash (in Russian). 16 October 2018. Retrieved 2019.
  7. ^ @Rogozin (8 February 2019). " -171 ?-5 "" " " ? ? ? ?" [First sample RD-171MV for Soyuz-5 Irtish manufactured in Energomash is ready for testing.] (Tweet) (in Russian) – via Twitter.
  8. ^ Coppinger, Rob (2009-08-11). "The Bear's stars shine brighter". Flight International. Retrieved .
  9. ^ "Successful Tests of Angara Stage 1 Engine". Khrunichev. 2007-12-12. Archived from the original on 2007-12-30.
  10. ^ "First launch of KSLV-1 is conducted". 2009-08-25.
  11. ^ Zak, Anatoly. "RD-193". russianspaceweb.com. Retrieved .
  12. ^ " " (in Russian). August 1, 2011. Archived from the original on September 30, 2011. Retrieved 2011.
  13. ^ "Energomash 2011 catalog (Russian)". Roscosmos. Retrieved 2018.
  14. ^ "Russia's Energomash: new rocket engines in development". VoiceofRussia.com. The Voice of Russia. 2012-02-22. Retrieved .
  15. ^ "Russia charts new path to super rocket". russianspaceweb.com. Retrieved 2018.
  16. ^ http://lpre.de/energomash/RD-170/#flow_schematic_descr

External links


  This article uses material from the Wikipedia page available here. It is released under the Creative Commons Attribution-Share-Alike License 3.0.

RD-170
 



 



 
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