RL10

RL10
	An RL10 at the U.S. Space & Rocket Center with cutaway showing tubing through the bell.
Negara asal	United States of America
Terbang pertama	1962 (RL10A-1)
Perancang	Pratt & Whitney/MSFC
Pembuat	Pratt & Whitney Space Propulsion ; Pratt & Whitney Rocketdyne; Aerojet Rocketdyne
Penggunaan	Upper stage engine
Kendaraan terkait	Atlas; Titan; Delta IV; Saturn I
Status	In production
Mesin propelan cair
Propelan	Liquid oxygen / Liquid hydrogen
Rasio campuran	5.5 or 5.85:1
Siklus	Expander cycle
Konfigurasi
Rasio pipa	84:1 or 280:1
Kinerja
Daya dorong (hampa)	110 kN (25.000 lbf)
Isp (vac.)	450 hingga 4.655 detik (4,41 hingga 45,65 km/s)
Lama pembakaran	700 seconds
Dimensi
Panjang	414 m (1.358 ft) (nozzle extended)
Diameter	213 m (699 ft)
Berat kering	277 kg (611 pon)
Digunakan pada
	Centaur; S-IV; DCSS
Referensi
Referensi
Catatan	Performance values and dimensions are for RL-10B-2.

RL10 adalah sebuah mesin roket bahan bakar cair kriogenik yang digunakan pada Centaur, S-IV dan tahap atas DCSS. Dibangun di Amerika Serikat oleh Aerojet Rocketdyne (sebelumnya oleh Pratt & Whitney Rocketdyne), RL10 membakar cryogenic hidrogen cair & propelan oksigen cair, dengan masing-masing mesin memproduksi 64,7-110 kN (14,545-24,729 lbf) daya dorong dalam ruang hampa tergantung pada versi digunakan. RL10 adalah mesin roket yang pertama menggunakan cairan hidrogen yang akan dibangun di Amerika Serikat, dan pengembangan mesin oleh Marshall Space Flight Center dan Pratt & Whitney dimulai pada tahun 1950, dengan penerbangan pertama terjadi pada tahun 1961.

Variants

Version	Status	First flight	Dry mass	Thrust	I_sp (vac)	Length	Diameter	T:W	O:F	Expansion ratio	Chamber pressure	Burn time	Associated stage	Notes
RL10A-1	Retired	1962	131 kg (289 pon)	667 kN (150.000 lb_f)	425 s (4,17 km/s)	173 m (568 ft)	153 m (502 ft)	52:1		40:1		430 s	Centaur A	Prototype ^[2]^[3]^[4]
RL10A-3	Retired	1963	131 kg (289 pon)	656 kN (147.000 lb_f)	444 s (4,35 km/s)	249 m (817 ft)	153 m (502 ft)	51:1	5:1	57:1	3.275 bar (327.500 kPa)	470 s	Centaur B/C/D/E S-IV	^[5]
RL10A-4	Retired	1992	168 kg (370 pon)	925 kN (208.000 lb_f)	449 s (4,40 km/s)	229 m (751 ft)	117 m (384 ft)	56:1	5.5:1	84:1		392 s	Centaur IIA	^[6]
RL10A-4-1	Retired	2000	167 kg (368 pon)	991 kN (223.000 lb_f)	451 s (4,42 km/s)		153 m (502 ft)	61:1		84:1		740 s	Centaur IIIA	^[7]
RL10A-4-2	In production	2002	167 kg (368 pon)	991 kN (223.000 lb_f)	451 s (4,42 km/s)		153 m (502 ft)	61:1		84:1		740 s	Centaur IIIB Centaur V1 Centaur V2	^[8]
RL10A-5	Retired	1993	143 kg (315 pon)	647 kN (145.000 lb_f)	373 s (3,66 km/s)	107 m (351 ft)	102 m (335 ft)	46:1	6:1	4:1		127 s	DC-X	^[9]
RL10B-2	In production	1998	277 kg (611 pon)	110 kN (25.000 lb_f)	462 s (4,53 km/s)	414 m (1.358 ft)	213 m (699 ft)	40:1	5.85:1	280:1	4.412 bar (441.200 kPa)	700 s	Delta Cryogenic Second Stage	^[1]
RL10B-X	Cancelled		317 kg (699 pon)	934 kN (210.000 lb_f)	470 s (4,6 km/s)		153 m (502 ft)	30:1		250:1		408 s	Centaur B-X	^[10]
CECE	In development		160 kg (350 pon)	667 kN (150.000 lb_f)	>445 s (4,36 km/s)	153 m (502 ft)								Base demonstrator ^[11]^[12]
RL10C-1	In testing	12/2014	191 kg (421 pon)	10.631 kN (2.390.000 lb_f)	4.485 s (43,98 km/s)	222 m (728 ft)	144 m (472 ft)	57:1	5.88:1	130:1		2000	Centaur	^[13]^[14]

Specifications

Original RL10

Thrust (altitude): 15,000 lbf (66.7 kN)^[3]
Burn Time: 470 s^[3]
Design: Expander cycle^{[butuh rujukan]}
Specific impulse: 433 detik (4,25 km/s)^{[butuh rujukan]}
Engine weight - dry: 298 lb (135 kg)
Height: 68 in (1.73 m)
Diameter: 39 in (0.99 m)
Nozzle expansion ratio: 40 to 1
Propellants: Liquid Oxygen & Liquid Hydrogen
Propellant flow: 35 lb/s (16 kg/s)
Contractor: Pratt & Whitney
Vehicle application: Saturn I / S-IV 2nd stage - 6-engines
Vehicle application: Centaur upper stage - 2-engines

Current design

RL10B-2 Specifications

Thrust (altitude): 24,750 lbf (110.1 kN)^[15]
Design: Expander cycle^[16]
Specific impulse: 464 detik (4,55 km/s)^[15]
Engine weight - dry: 610 lb (277 kg)^[15]
Height: 163 in (4.14 m)^[15]
Diameter: 87 in (2.21 m)^[15]
Expansion ratio: 250 to 1
Mixture ratio: 5.85 to 1 ^[15]
Propellants: Liquid oxygen & liquid hydrogen^[15]
Propellant flow: Oxidizer 41.42 lb/s (20.6 kg/s), fuel 7.72 lb/s (3.5 kg/s)^[15]
Contractor: Pratt & Whitney
Vehicle application: Delta III, Delta IV second stage (1 engine)

RL10A-4-2

The other current model, the RL10A-4-2, is the engine used on Centaur upper stage for Atlas V.^[15]

Referensi

Notes

^ ^a ^b Mark Wade (17 November 2011). "RL-10B-2". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.
^ Mark Wade (17 November 2011). "RL-10A-1". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.
^ ^a ^b ^c Bilstein, Roger E. (1996), "Unconventional Cryogenics: RL-10 and J-2", Stages to Saturn; A Technological History of the Apollo/Saturn Launch Vehicles, Washington, D.C.: National Aeronautics and Space Administration, NASA History Office, diakses tanggal 2011-12-02
^ "Atlas Centaur". Gunter's Space Page. Diakses tanggal 29 February 2012.
^ Mark Wade (17 November 2011). "RL-10A-3". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.
^ Mark Wade (17 November 2011). "RL-10A-4". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.
^ Mark Wade (17 November 2011). "RL-10A-4-1". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.
^ Mark Wade (17 November 2011). "RL-10A-4-2". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.
^ Mark Wade (17 November 2011). "RL-10A-5". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.
^ Mark Wade (17 November 2011). "RL-10B-X". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.
^ "Commons Extensible Cryogenic Engine". Pratt & Whitney Rocketdyne. Diarsipkan dari versi asli tanggal 2012-03-04. Diakses tanggal 28 February 2012.
^ "Salinan arsip". Diarsipkan dari versi asli tanggal 2014-07-03. Diakses tanggal 2015-11-09.
^ "Cryogenic Propulsion Stage" (PDF). NASA. Diakses tanggal 11 October 2014.
^ [1]
^ ^a ^b ^c ^d ^e ^f ^g ^h ⁱ "RL10B-2" (PDF). Pratt & Whitney Rocketdyne. 2009. Diarsipkan dari versi asli (PDF) tanggal 2012-03-26. Diakses tanggal January 29, 2012.
^ Sutton, A M; Peery, S D; Minick, A B (January 1998). "50K expander cycle engine demonstration". AIP Conference Proceedings. 420: pp. 1062–1065. doi:10.1063/1.54719. Diarsipkan dari versi asli tanggal 2013-04-13. Diakses tanggal 2015-11-09. Pemeliharaan CS1: Teks tambahan (link)

Bibliography

Connors, Jack (2010). The Engines of Pratt & Whitney: A Technical History. Reston. Virginia: American Institute of Aeronautics and Astronautics. ISBN 978-1-60086-711-8.

Pranala luar

[EA10B2-1] Mark Wade (17 November 2011). "RL-10B-2". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.

[EA10A1-2] Mark Wade (17 November 2011). "RL-10A-1". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.

[S2S-3] Bilstein, Roger E. (1996), "Unconventional Cryogenics: RL-10 and J-2", Stages to Saturn; A Technological History of the Apollo/Saturn Launch Vehicles, Washington, D.C.: National Aeronautics and Space Administration, NASA History Office, diakses tanggal 2011-12-02

[GSPAC-4] "Atlas Centaur". Gunter's Space Page. Diakses tanggal 29 February 2012.

[EA10A3-5] Mark Wade (17 November 2011). "RL-10A-3". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.

[EA10A4-6] Mark Wade (17 November 2011). "RL-10A-4". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.

[EA10A41-7] Mark Wade (17 November 2011). "RL-10A-4-1". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.

[EA10A42-8] Mark Wade (17 November 2011). "RL-10A-4-2". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.

[EA10A5-9] Mark Wade (17 November 2011). "RL-10A-5". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.

[EA10BX-10] Mark Wade (17 November 2011). "RL-10B-X". Encyclopedia Astronautica. Diakses tanggal 27 February 2012.

[PWRCECE-11] "Commons Extensible Cryogenic Engine". Pratt & Whitney Rocketdyne. Diarsipkan dari versi asli tanggal 2012-03-04. Diakses tanggal 28 February 2012.

[12] "Salinan arsip". Diarsipkan dari versi asli tanggal 2014-07-03. Diakses tanggal 2015-11-09.

[CPS-13] "Cryogenic Propulsion Stage" (PDF). NASA. Diakses tanggal 11 October 2014.

[14] [1]

[pwr_rl10b-2.pdf-15] ^ ^a ^b ^c ^d ^e ^f ^g ^h ⁱ "RL10B-2" (PDF). Pratt & Whitney Rocketdyne. 2009. Diarsipkan dari versi asli (PDF) tanggal 2012-03-26. Diakses tanggal January 29, 2012.

[2-16] Sutton, A M; Peery, S D; Minick, A B (January 1998). "50K expander cycle engine demonstration". AIP Conference Proceedings. 420: pp. 1062–1065. doi:10.1063/1.54719. Diarsipkan dari versi asli tanggal 2013-04-13. Diakses tanggal 2015-11-09. Pemeliharaan CS1: Teks tambahan (link)

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RL10

Variants

Specifications

Original RL10

Current design

Referensi

Pranala luar

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