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Delta Cryogenic Second Stage information


Delta Cryogenic Second Stage
A 4-meter DCSS from a Delta IV Medium
ManufacturerBoeing 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 originUnited States
Japan (Delta III, original)
Used onDelta III
Delta IV
SLS Block I
Launch history
StatusActive
Total launches45
Successes
(stage only)
42
18 Delta IV 4 m
23 Delta IV 5 m
Failed2 (Delta III)
Lower stage
failed
1 (Delta III)
First flightAugust 27, 1998
Last flightApril 9, 2024
Delta III second stage
Height8.8 meters (29 ft)
Diameter4 meters (13 ft) (LH2 tank) 3.2 meters (10 ft) (LOX tank)[1]
Empty mass2,480 kilograms (5,470 lb)
Gross mass19,300 kilograms (42,500 lb)
Powered by1 RL10B-2
Maximum thrust110.1 kilonewtons (24,800 lbf)
Specific impulse462 seconds (4.53 km/s)
Burn time700 seconds
PropellantLH2/LOX
Delta IV 4-meter stage
Height12.2 meters (40 ft)
Diameter4 meters (13 ft) (LH2 tank) 3.2 meters (10 ft) (LOX tank)[1]
Empty mass2,850 kilograms (6,280 lb)
Gross mass24,170 kilograms (53,290 lb)
Powered by1 RL10B-2
Maximum thrust110.1 kilonewtons (24,800 lbf)
Specific impulse462 seconds (4.53 km/s)
Burn time850 seconds
PropellantLH2/LOX
Delta IV 5-meter stage
Height13.7 meters (45 ft)
Diameter5 meters (16 ft) (LH2 tank) 3.2 meters (10 ft) (LOX tank)[1]
Empty mass3,490 kilograms (7,690 lb)
Gross mass30,710 kilograms (67,700 lb)
Powered by1 RL10B-2
Maximum thrust110.1 kilonewtons (24,800 lbf)
Specific impulse462 seconds (4.53 km/s)
Burn time1125 seconds
PropellantLH2/LOX
Interim Cryogenic Propulsion Stage (SLS Block 1)[2]
Height13.7 meters (45 ft)
Diameter5 meters (16 ft) (LH2 tank) 3.2 meters (10 ft) (LOX tank)[1]
Empty mass3,800 kilograms (8,400 lb)
Gross mass32,748 kilograms (72,197 lb)
Powered by1 RL10B-2
Maximum thrust110.1 kilonewtons (24,800 lbf)
Specific impulse462 seconds (4.53 km/s)
Burn time1125 seconds
PropellantLH2/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]

  1. ^ a b c d "Delta IV Launch Services User's Guide" (PDF). United Launch Alliance. Retrieved April 12, 2024.
  2. ^ Braeunig, Robert. "SPECIFICATIONS & TECHNICAL DATA: Space Launch System". Retrieved January 19, 2024.
  3. ^ Robert A. Braeunig (2 November 2009). "Space Launchers—Delta". Rocket and Space Technology. Retrieved 26 January 2012.
  4. ^ Cite error: The named reference DIVPayloadGuide was invoked but never defined (see the help page).

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