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 | |
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| Launch history | |
| Status | Active |
| Total launches | 45 |
| Successes (stage only) | 42 |
| Failed | 2 (Delta III) |
| Lower stage failed | 1 (Delta III) |
| First flight | 27 August 1998 |
| Last flight | 9 April 2024 |
| Delta III second stage | |
| Height | 8.8 m (29 ft) |
| Diameter | 4 m (13 ft) (LH2 tank) 3.2 m (10 ft) (LOX tank)[1] |
| Empty mass | 2,480 kg (5,470 lb) |
| Gross mass | 19,300 kg (42,500 lb) |
| Powered by | 1 × RL10B-2 |
| Maximum thrust | 110.1 kN (24,800 lbf) |
| Specific impulse | 462 s (4.53 km/s) |
| Burn time | 700 seconds |
| Propellant | LH2/LOX |
| Delta IV 4-meter second stage | |
| Height | 12.2 m (40 ft) |
| Diameter | 4 m (13 ft) (LH2 tank) 3.2 m (10 ft) (LOX tank)[1] |
| Empty mass | 2,850 kg (6,280 lb) |
| Gross mass | 24,170 kg (53,290 lb) |
| Powered by | 1 × RL10B-2 |
| Maximum thrust | 110.1 kN (24,800 lbf) |
| Specific impulse | 462 s (4.53 km/s) |
| Burn time | 850 seconds |
| Propellant | LH2/LOX |
| Delta IV 5-meter second stage | |
| Height | 13.7 m (45 ft) |
| Diameter | 5 m (16 ft) (LH2 tank) 3.2 m (10 ft) (LOX tank)[1] |
| Empty mass | 3,490 kg (7,690 lb) |
| Gross mass | 30,710 kg (67,700 lb) |
| Powered by | 1 × RL10B-2 |
| Maximum thrust | 110.1 kN (24,800 lbf) |
| Specific impulse | 462 s (4.53 km/s) |
| Burn time | 1,125 seconds |
| Propellant | LH2/LOX |
| Interim Cryogenic Propulsion Stage | |
| Height | 13.7 m (45 ft) |
| Diameter | 5 m (16 ft) (LH2 tank) 3.2 m (10 ft) (LOX tank) |
| Empty mass | 3,800 kg (8,400 lb) |
| Gross mass | 32,748 kg (72,197 lb) |
| Powered by | 1 × RL10B-2 |
| Maximum thrust | 110.1 kN (24,800 lbf) |
| Specific impulse | 462 s (4.53 km/s) |
| Burn time | 1,125 seconds |
| Propellant | LH2/LOX |
The Delta Cryogenic Second Stage (DCSS) is a family of cryogenic-fuelled rocket stages used on the Delta III, Delta IV, and on the Space Launch System Block 1 launch vehicles. The DCSS employs a unique two-tank architecture where the cylindrical liquid hydrogen (LH2) tank carries payload launch loads and forms the upper section. An oblate spheroid tank filled with liquid oxygen (LOX) and the engine are suspended from the LH2 tank and covered by the interstage during initial launch.
The DCSS is powered by a single RL10B-2 engine built by Aerojet Rocketdyne,[2] which features an extendable carbon–carbon nozzle to improve specific impulse.[3]
The DCSS was designed by the National Space Development Agency of Japan, based on the second stage it developed for the H-IIA rocket. The initial versions for the Delta III were built by Mitsubishi Heavy Industries in Japan. For the Delta IV, production was transferred to Boeing Integrated Defense Systems and later to United Launch Alliance.
- ^ a b c "Delta IV Launch Services User's Guide" (PDF). United Launch Alliance. Retrieved 12 April 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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