RD-250

RD-250 (РД-250)
Country of origin USSR
First flight December 16th, 1965
Designer OKB-456
Manufacturer PA Yuzhmash
Associated L/V R-36, Tsyklon-2 and Tsyklon-3
Status Out of Production
Liquid-fuel engine
Propellant N2O4 / UDMH
Mixture ratio 2.6
Cycle Oxidizer Rich Staged Combustion
Configuration
Chamber 2
Performance
Thrust (vac.) 788 kN (177,000 lbf)
Thrust (SL) 882 kN (198,000 lbf)
Chamber pressure 8.33 MPa (1,208 psi)
Isp (vac.) 301 s (2.95 km/s)
Isp (SL) 270 s (2.6 km/s)
Dimensions
Dry weight 788 kg (1,737 lb)
Used in
R-36, Tsyklon-2 and Tsyklon-3 first stage
References
References [1][2][3][4][5][6]

The RD-250 (GRAU Index 8D518) is the base version of a dual nozzle family of liquid rocket engines, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle. The RD-250 was developed by OKB-456 for Yangel's PA Yuzhmash ICBM, the R-36 (missile) (8K67). Its variations were also used on the Tsyklon-2 and Tsyklon-3 launch vehicles. It was supposed to be used on the Tsyklon-4, but since the cancellation of the project it should be considered as out of production.

Versions

The engine has seen different versions made:

Modules

Some of these engines were bundled into modules of multiple engines. The relevant modules and auxiliary engines are:


Comparison

RD-250 Family of Engines[1]
Engine RD-250 RD-250P RD-250M RD-250PM RD-252 RD-262
GRAU 8D518 8D518P 8D518M 8D518PM 8D724 11D26
Module RD-251 RD-251P RD-251M RD-262 N/A N/A
Module GRAU 8D723 8D723P 8D723M 11D69 N/A N/A
Development 1962-1966 1967-1968 1966-1968 1968-1970 1962-1966 1968-1970
Propellant N2O4/UDMH
Combustion chamber pressure 8.336 MPa (1,209.0 psi) 8.924 MPa (1,294.3 psi)
Thrust, vacuum 881.6 kN (198,200 lbf) 881.6 kN (198,200 lbf) 881.6 kN (198,200 lbf) 881.7 kN (198,200 lbf) 940.8 kN (211,500 lbf) 941.4 kilonewtons (211,600 lbf)
Thrust, sea level 788.5 kN (177,300 lbf) 788.5 kN (177,300 lbf) 788.5 kN (177,300 lbf) 788.7 kN (177,300 lbf) N/A N/A
Isp, vacuum 301 s (2.95 km/s) 301 s (2.95 km/s) 301 s (2.95 km/s) 301.4 s (2.956 km/s) 317.6 s (3.115 km/s) 318 s (3.12 km/s)
Isp, sea level 270 s (2.6 km/s) 270 s (2.6 km/s) 270 s (2.6 km/s) 269.6 s (2.644 km/s) N/A N/A
Length 2,600 mm (100 in) 2,600 mm (100 in) 2,600 mm (100 in) N/A 2,190 mm (86 in) 2,190 mm (86 in)
Diameter 1,000 mm (39 in) 1,000 mm (39 in) 1,000 mm (39 in) N/A 2,590 mm (102 in) 2,590 mm (102 in)
Dry weight 728 kg (1,605 lb) 728 kg (1,605 lb) 728 kg (1,605 lb) N/A 715 kg (1,576 lb) 715 kg (1,576 lb)
Use R-36 (8K67) 1st stage R-36P (8K67P) 1st stage R-36-O (8K67-O) and Tsyklon-2 1st stage Tsyklon-3 1st stage R-36, R36P, R-36-O, Tsyklon-2 2nd stage Tsyklon-3 2nd stage

See also

References

  1. 1 2 "NPO Energomash list of engines". NPO Energomash. Retrieved 2015-06-20.
  2. "RD-250". Encyclopedia Astronautica. Retrieved 2015-06-20.
  3. 1 2 "RD-251". Encyclopedia Astronautica. Retrieved 2015-06-20.
  4. 1 2 "RD-252". Encyclopedia Astronautica. Retrieved 2015-06-20.
  5. Pillet, Nicolas. "Tsiklone - Le premier étage" [Tsyklon - The first stage] (in French). Kosmonavtika.com. Retrieved 2016-07-04.
  6. Pillet, Nicolas. "Tsiklone - Le deuxième étage" [Tsyklon - The second stage] (in French). Kosmonavtika.com. Retrieved 2016-07-04.
  7. "RD-262". Encyclopedia Astronautica. Retrieved 2015-06-20.
  8. "RD-261". Encyclopedia Astronautica. Retrieved 2015-06-20.

External links

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