Delta Cryogenic Second Stage
 A 4-meter DCSS from a Delta IV Medium | |
| Manufacturer | Boeing IDS United Launch Alliance Mitsubishi Heavy Industries (Original Delta III design and manufacturing) |
|---|---|
| Country of origin | United States |
| Used on | Delta III Delta IV SLS Block I |
| Launch history | |
| Status | Active |
| Total launches | 21 |
| Successes (stage only) | 18 11 Delta IV 4 m 7 Delta IV 5 m |
| Failed | 2 (Delta III) |
| Lower stage failed | 1 (Delta III) |
| Delta III second stage | |
| Length | 8.8 meters (29 ft) |
| Diameter | 4 meters (13 ft) |
| Empty mass | 2,480 kilograms (5,470 lb) |
| Gross mass | 19,300 kilograms (42,500 lb) |
| Engines | 1 RL10B-2 |
| Thrust | 110.1 kilonewtons (24,800 lbf) |
| Specific impulse | 462 seconds (4.53 km/s) |
| Burn time | 700 seconds |
| Propellant | LH2/LOX |
| Delta IV 4-meter stage | |
| Length | 12.2 meters (40 ft) |
| Diameter | 4 meters (13 ft) |
| Empty mass | 2,850 kilograms (6,280 lb) |
| Gross mass | 24,170 kilograms (53,290 lb) |
| Engines | 1 RL10B-2 |
| Thrust | 110.1 kilonewtons (24,800 lbf) |
| Specific impulse | 462 seconds (4.53 km/s) |
| Burn time | 850 seconds |
| Propellant | LH2/LOX |
| Delta IV 5-meter stage | |
| Length | 13.7 meters (45 ft) |
| Diameter | 5 meters (16 ft) |
| Empty mass | 3,490 kilograms (7,690 lb) |
| Gross mass | 30,710 kilograms (67,700 lb) |
| Engines | 1 RL10B-2 |
| Thrust | 110.1 kilonewtons (24,800 lbf) |
| Specific impulse | 462 seconds (4.53 km/s) |
| Burn time | 1125 seconds |
| Propellant | LH2/LOX |
The Delta Cryogenic Second Stage (DCSS) is a family of cryogenic rocket stages used on the Delta III and Delta IV rockets, and which is planned to be used on the Space Launch System Block 1. The stage consists of a cylindrical liquid hydrogen (LH2) tank structurally separated from an oblate spheroid liquid oxygen (LOX) tank. The LH2 tank cylinder carries payload launch loads, while the LOX tank and engine are suspended below within the rocket's inter-stage. The stage is powered by a single Aerojet Rocketdyne-Pratt & Whitney RL10B-2 engine,[1] which features an extendable carbon-carbon nozzle to improve specific impulse.[2]
Delta III[]
The DCSS first flew on 3 Delta IIIs, and failed 2 of 2 times. The booster failed on the third flight, causing the loss of the DCSS before ignitions. An un-flown example is on display outside the Discovery Cube Orange County.[citation needed]
Delta IV[]
Two different versions are flown, depending on variant. Composite interstages used to mate the first and second stages together accommodate the different configurations.[2] For the Delta IV-M, a tapering interstage that narrows down in diameter from 5 meters to 4 meters is used on the 4-meter DCSS, while a cylindrical interstage is used on the 5-meter DCSS.[2]
Interim Cryogenic Propulsion Stage[]
The Interim Cryogenic Propulsion Stage, a minimally modified 5-meter DCSS, is used as the upper stage of the Space Launch System Block 1. The ICPS was mated to the SLS launch stack on July 6, 2021.[3][4]
References[]
- ^ Robert A. Braeunig (2 November 2009). "Space Launchers—Delta". Rocket and Space Technology (braeunig.us). Retrieved 26 January 2012.
- ^ Jump up to: a b c "Delta IV Payload Planners Guide" (PDF). United Launch Alliance. September 2007. pp. 1–5 to 1–6. Archived from the original (PDF) on 22 July 2011.
- ^ Chris Bergin (4 October 2011). "SLS trades lean towards opening with four RS-25s on the core stage". NASASpaceflight.com. Retrieved 26 January 2012.
- ^ Rosenberg, Zach. "Delta second stage chosen as SLS interim". Flight International, May 8, 2012.
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