RD-215

The RD-215 (GRAU Index 8D513) was a dual nozzle liquid rocket engine, burning AK-27 (a mixture of 73% nitric acid and 27% N2O4 + iodine passivant) and UDMH. It was used in a module of two engines (four nozzles) known as the RD-216 (GRAU Index 8D514).[2] The RD-215 was developed by OKB-456 for Yangel's Yuzhmash R-14 (8K65) ballistic missile. Its variations were also used on the Kosmos-1, Kosmos-3 and Kosmos-3M launch vehicles.[1]

RD-215 (РД-215)
Country of originUSSR
Date1958-1960
DesignerOKB-456, V.Glushko
Associated L/VR-14, Kosmos-3 and Kosmos-3M
StatusRetired
Liquid-fuel engine
PropellantAK-27I / UDMH
Mixture ratio2.5
Configuration
Chamber2
Nozzle ratio18.8
Performance
Thrust (vac.)887 kN (199,000 lbf)
Thrust (SL)740 kN (170,000 lbf)
Chamber pressure7.355 MPa (1,066.8 psi)
Isp (vac.)289 s (2.83 km/s)
Isp (SL)246 s (2.41 km/s)
Dimensions
Length2,205 mm (86.8 in)
Diameter2,260 mm (89 in)
Dry weight575 kg (1,268 lb)
Used in
R-14, Kosmos-3 and Kosmos-3M first stage
References
References[1][2][3][4][5][6]

Versions

The family incorporate many versions:[1][7]

  • RD-215: GRAU Index 8D513. Original design for the R-14 (8K65). Used also on the Kosmos-1 and Kosmos-3[2][1]
  • RD-215U: GRAU Index 8D513U. Improved engine for the R-14U (8K65U).[1]
  • RD-215M: GRAU Index 8D513M. Improved version used on the Kosmos-3M.[1]
  • RD-217: GRAU Index 8D515. Modified design for the R-16 (8K64) first stage.
  • RD-219: GRAU Index 8D713. Modified design for the R-16 (8K64) second stage.

Modules

These engines were bundled into modules of pairs of engines. The serial production modules were:[1][3]

  • RD-216: GRAU Index 8D514. Bundle of two RD-215, used on the R-14 (8K65), Kosmos-1 and Kosmos-3 first stage.[2][1]
  • RD-216U: GRAU Index 8D514U. Bundle of two RD-215U, used on the R-14U (8K65U) first stage.[1]
  • RD-216M: GRAU Index 8D514M. Bundle of two RD-215M, used on the Kosmos-3M first stage.[1]
  • RD-218: GRAU Index 8D712. Bundle of three RD-217, powers the R-16 (8K64) first stage.
RD-215 Family of Engines[1]
Engine RD-215 RD-215U RD-215M
GRAU 8D5148D514U8D514M
Development 1958-19601960-19611966-1968
Propellant AK-27I (73% nitric acid, 27% N2O4, and iodine passivant) / UDMH[2]
Combustion chamber pressure 7.355 MPa (1,066.8 psi)
Thrust, vacuum 887 kN (199,000 lbf)887 kN (199,000 lbf)890 kN (200,000 lbf)
Thrust, sea level 740 kN (170,000 lbf)740 kN (170,000 lbf)742.8 kN (167,000 lbf)
Isp, vacuum 289 s (2.83 km/s)289 s (2.83 km/s)291.3 s (2.857 km/s)
Isp, sea level 246 s (2.41 km/s)246 s (2.41 km/s)248 s (2.43 km/s)
Burn time 146sN/AN/A
Length 2,205 mm (86.8 in)2,205 mm (86.8 in)2,205 mm (86.8 in)
Diameter 2,260 mm (89 in)2,260 mm (89 in)2,260 mm (89 in)
Dry weight 575 kg (1,268 lb)575 kg (1,268 lb)570 kg (1,260 lb)
Use R-14 (8K65), Kosmos-1 and Kosmos-3R-14U (8K65U)Kosmos-3M
gollark: VSCode.
gollark: Whatever, I can probably still do it.
gollark: Oh wait, calendars are actually hard.
gollark: Sure. Let me load up my IDE.
gollark: I don't know if this is conveniently available as a service, but I could probably make a simple web application for it.

See also

References
  1. "NPO Energomash list of engines". NPO Energomash. Retrieved 2015-06-26.
  2. "RD-216". Encyclopedia Astronautica. Retrieved 2015-06-26.
  3. "R-14". Encyclopedia Astronautica. Retrieved 2015-06-26.
  4. Zak, Anatoly. "Cosmos-1, 3, 3M and 3MU". RussianSpaceWeb.com. Retrieved 2016-07-05.
  5. Krebs, Gunter Dirk (2016-04-22). "Kosmos-1/-3/-3M". Gunter's Space Page. Retrieved 2016-07-05.
  6. Nicolas, Pillet (2013-07-20). "Cosmos-3 Description du lanceur" [Kosmos 3 Launcher Description] (in French). Kosmonavtika. Retrieved 2016-07-05.
  7. http://www.astronautix.com/r/rd-215.html
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