Back DCSS Bulgarian Delta Cryogenic Second Stage Finnish Delta Cryogenic Second Stage French Delta Cryogenic Second Stage ID Delta Cryogenic Second Stage Italian Delta IV 2. pakāpe (4 m) Latvian/Lettish Delta Cryogenic Second Stage Polish Delta Cryogenic Second Stage Portuguese
 A 4-meter DCSS from a Delta IV Medium | |
| Manufacturer | Boeing IDS United Launch Alliance Mitsubishi Heavy Industries (Original Delta III design and manufacturing) JAXA/NASDA (H-IIA/DCSS upper stage design, original version) |
|---|---|
| Country of origin | United States Japan (Delta III, original) |
| Used on | Delta III Delta IV SLS Block I |
| Launch history | |
| Status | Active |
| Total launches | 45 |
| Successes (stage only) | 42 18 Delta IV 4 m 23 Delta IV 5 m |
| Failed | 2 (Delta III) |
| Lower stage failed | 1 (Delta III) |
| First flight | August 27, 1998 |
| Last flight | April 9, 2024 |
| Delta III second stage | |
| Height | 8.8 meters (29 ft) |
| Diameter | 4 meters (13 ft) (LH2 tank) 3.2 meters (10 ft) (LOX tank)[1] |
| Empty mass | 2,480 kilograms (5,470 lb) |
| Gross mass | 19,300 kilograms (42,500 lb) |
| Powered by | 1 RL10B-2 |
| Maximum 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 | |
| Height | 12.2 meters (40 ft) |
| Diameter | 4 meters (13 ft) (LH2 tank) 3.2 meters (10 ft) (LOX tank)[1] |
| Empty mass | 2,850 kilograms (6,280 lb) |
| Gross mass | 24,170 kilograms (53,290 lb) |
| Powered by | 1 RL10B-2 |
| Maximum 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 | |
| Height | 13.7 meters (45 ft) |
| Diameter | 5 meters (16 ft) (LH2 tank) 3.2 meters (10 ft) (LOX tank)[1] |
| Empty mass | 3,490 kilograms (7,690 lb) |
| Gross mass | 30,710 kilograms (67,700 lb) |
| Powered by | 1 RL10B-2 |
| Maximum thrust | 110.1 kilonewtons (24,800 lbf) |
| Specific impulse | 462 seconds (4.53 km/s) |
| Burn time | 1125 seconds |
| Propellant | LH2/LOX |
| Interim Cryogenic Propulsion Stage (SLS Block 1)[2] | |
| Height | 13.7 meters (45 ft) |
| Diameter | 5 meters (16 ft) (LH2 tank) 3.2 meters (10 ft) (LOX tank)[1] |
| Empty mass | 3,800 kilograms (8,400 lb) |
| Gross mass | 32,748 kilograms (72,197 lb) |
| Powered by | 1 RL10B-2 |
| Maximum 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 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,[3] which features an extendable carbon–carbon nozzle to improve specific impulse.[4]
- ^ a b c d "Delta IV Launch Services User's Guide" (PDF). United Launch Alliance. Retrieved April 12, 2024.
- ^ Braeunig, Robert. "SPECIFICATIONS & TECHNICAL DATA: Space Launch System". Retrieved January 19, 2024.
- ^ Robert A. Braeunig (2 November 2009). "Space Launchers—Delta". Rocket and Space Technology. Retrieved 26 January 2012.
- ^ Cite error: The named reference
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