RS-27

American kerolox rocket engine

For the diesel locomotive, see ALCO RS-27.

RS-27

First stage of a Delta II rocket, including an RS-27

Country of origin| United States
Date| 1974
Designer| Rocketdyne
Manufacturer| Rocketdyne
Application| Booster
Predecessor| H-1
Successor| RS-27A, RS-56
Status| Retired
Liquid-fuel engine
Propellant| LOX / RP-1
Cycle| Gas Generator
Configuration
Chamber| 1
Performance
Thrust, vacuum| 1,023 kN (230,000 lbf)
Thrust, sea-level| 971 kN (218,000 lbf)
Chamber pressure| 4.9 MPa (49 bar)
Specific impulse, vacuum| 295 seconds (2.89 km/s)
Specific impulse, sea-level| 264 seconds (2.59 km/s)
Burn time| 274 Sec
Dimensions
Length| 3.63 m (11.9 ft)
Diameter| 1.07 m (3.51 ft)
Dry weight| 1,027 kg (2,264 lb)
Used in
Delta 2000, 3000, 5000, 6000, first stage[1]

The RS-27 was a liquid-propellant rocket engine developed in 1974 by Rocketdyne to replace the aging MB-3 in the Delta. Incorporating components of the venerable MB-3 and the H-1 designs, the RS-27 was a modernized version of the basic design used for two decades. It was used to power the first stage of the Delta 2000, 3000, 5000, and the first model of the Delta II, the Delta 6000.

The RS-27 was a modified Rocketdyne H-1 built to power the first stage of the Saturn I and Saturn IB and replaced the MB-3 engine that had been used on previous versions of the Delta launcher. NASA had a large supply of surplus H-1 engines in the early 1970s, as the Apollo program was ending.[2][3] In addition to its main engine, the RS-27 included two vernier engines to provide vehicle roll control during flight.[4] RS-27 was later developed into the RS-27A and RS-56.[5][6]

## References[edit]

1. ^ "Delta". Astronautix. Archived from the original on August 17, 2013. Retrieved March 5, 2015.
2. ^ "RS-27". Astronautix. Archived from the original on October 11, 2011. Retrieved March 5, 2015.
3. ^ Kyle, Ed. "Extended Long Tank Delta". SpaceLaunchReport.com. Retrieved March 5, 2015.
4. ^ J. K. Ganoung; H. Eaton (April 1, 1981). "The Delta Launch V The Delta Launch Vehicle- P ehicle- Past, Pr ast, Present, and F esent, and Future". The Space Congress Proceedings. 18: 6-6. Retrieved March 12, 2023.
5. ^ "Atlas IIA(S) Data Sheet". Space Launch Report. Retrieved 9 January 2016.
6. ^ "RS-27A". Astronautix. Archived from the original on 5 August 2014. Retrieved 10 January 2016.

* v
* t
* e

Rocket engines and solid motors for orbital launch vehicles

* Comparison of orbital rocket engines

Liquid
fuel|

| Cryogenic|

| Hydrolox
(LH2 / LOX)|

* China
* YF-73
* YF-75
* YF-75D
* YF-77
* YF-79
* YF-90
* Europe
* HM7B
* Vinci
* Vulcain
* India
* CE-7.5
* CE-20
* Japan
* LE-5
* LE-7
* LE-9
* Russia
* KVD-1 (RD-56)
* RD-0120
* RD-0146
* USA
* BE-3U
* BE-7
* J-2
* RL10
* RS-25
* RS-68

|

Methalox
(CH4 / LOX)|

* China
* Lingyun
* Longyun
* TQ-11
* TQ-12
* TQ-15A
* USA
* BE-4
* Raptor
* Archimedes
* Aeon 1
* Aeon R
* Russia
* RD-0169
* Europe
* Prometheus
* M-10

Semi-
cryogenic|

| Kerolox
(RP-1 / LOX)|

* China
* TH-11
* TH-12
* YF-100
* YF-102
* YF-115
* YF-130
* Welkin
* India
* SCE-200
* Russia
* NK-15
* NK-33, 44
* RD-58
* RD-0105, 0109
* RD-0107, 0108, 0110
* RD-0110R
* RD-0124
* RD-107, 108, 117, 118
* RD-120
* RD-170, 171
* RD-180
* RD-191, 151, 181
* RD-193
* S1.5400
* Spain
* TEPREL
* Ukraine
* RD-8
* RD-801
* RD-810
* USA
* F-1
* H-1
* Kestrel
* LR-79
* LR-89
* LR-105
* LR70-NA , S-3D
* Merlin
* RS-27
* RS-27A
* RS-56
* S-3D
* Rutherford
* XLR50

|

Storable|

| Hypergolic (Aerozine,
UH 25, MMH, or UDMH
/ N2O4, MON, or HNO3)|

* China
* YF-1, 2, 3
* YF-20, 21, 22, 24, 25
* YF-23
* YF-40
* YF-50D
* Europe
* Aestus
* Astris
* Vexin
* Viking
* India
* PS4
* Vikas
* Israel
* LK-4
* North Korea
* Paektusan LRE along other LREs
* Russia
* 17D61
* RD-0202 to 0206, 0208 to 0213
* RD-0207, 0214
* RD-0216, 0217, 0235
* RD-0233, 0234
* RD-0236
* RD-0237
* RD-0243 to 0245
* RD-0255 to 0257
* RD-215 to 219
* RD-250 to 252, 261, 262
* RD-253, 275
* RD-263, 268, 273
* RD-270
* S5.92
* S5.98M
* Ukraine
* RD-843
* RD-854, 861
* RD-855
* RD-856
* RD-864, 869
* USA
* AJ10
* LR-87
* LR-91
* TR-201
* XLR81*

|

Other|

* Russia
* RD-109, 119
* RD-211 to 214
* UK
* Gamma
* USA
* Curie
* XLR81*

Solid
fuel|

* China
* FG-02
* FG-36
* FG-46
* FG-47
* SpaB-65
* SpaB-140C
* Europe
* Mage 1
* P-4
* P-6
* PAP
* P80
* P120
* P230
* Topaze
* Waxwing
* Zefiro 9
* Zefiro 23
* Zefiro 40
* India
* S7
* S9
* S12
* S139
* S200
* Iran
* Salman
* Rafe
* Israel
* LK-1
* RSA-3
* Japan
* KM-V1
* KM-V2b
* M-14
* M-24
* M-34
* M-34c
* SRB-A
* USA
* AJ-60A
* Algol
* Castor 30
* GEM
* Orbus-6
* Orbus-21
* Orion
* Space Shuttle SRB
* Star 37
* Star 48
* UA120
* SRMU
* X-248
* X-254

* * Different versions of the engine use different propellant combinations
* Engines in italics are under development

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