 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 | [1] |
| 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
sunting| Version | Status | First flight | Dry mass | Thrust | Isp (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 lbf) | 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 lbf) | 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 lbf) | 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 lbf) | 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 lbf) | 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 lbf) | 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 lbf) | 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 lbf) | 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 lbf) | >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 lbf) | 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
suntingOriginal RL10
sunting- 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
sunting
- 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]
Lihat pula
sunting- BE-3 – mesin berbahan bakar hidrogen yang saat ini dioperasikan oleh Blue Origin
- SpaceX Raptor – mesin berbahan bakar metana yang dikembangkan oleh SpaceX
- Merlin – mesin operasional berbahan bakar minyak tanah oleh SpaceX
- BE-4 (Blue Engine 4) – mesin berbahan bakar metana yang dikembangkan oleh Blue Origin
- Wahana peluncur antariksa
- Mesin roket
- RD-0124
- YF-40
- YF-73
- YF-75
- YF-79
- AJ-10
- CE-20
- CE-7.5
- LE-5
- M10 (mesin roket)
- RD-0146
- RD-8 (mesin roket)
Referensi
sunting- 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 asli tanggal 2012-03-04. Diakses tanggal 28 February 2012.
- ^ "Salinan arsip". Diarsipkan dari 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 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 asli tanggal 2013-04-13. Diakses tanggal 2015-11-09. ;
- 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.
Wikimedia Commons memiliki media mengenai RL10.
 | Artikel bertopik teknologi ini adalah sebuah rintisan. Anda dapat membantu Wikipedia dengan mengembangkannya. |
 | Artikel bertopik roket ini adalah sebuah rintisan. Anda dapat membantu Wikipedia dengan mengembangkannya. |
