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Rocket Engines

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11D-513
11D-57
11D-58
Aerospike
Aestus
HM7B
LE-5
LE-7
MA-5
NK-31 / 39
NK-33 / 43
RD-120
RD-170
RD-180
RL-10
RL-60
RS-27
RS-68
RS-72
RS-76
SSME
Viking
Vulcain

  RL-10 - Specifications
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Engine Performance

RL10A3-3A RL10A-4 RL10A4-2 RL10A-5 RL10B-2
Propellant Combination
     Oxidizer
     Fuel
Liquid Oxygen (LOX)
Liquid Hydrogen (LH
2)
Liquid Oxygen (LOX)
Liquid Hydrogen (LH
2)
Liquid Oxygen (LOX)
Liquid Hydrogen (LH
2)
Liquid Oxygen (LOX)
Liquid Hydrogen (LH
2)
Liquid Oxygen (LOX)
Liquid Hydrogen (LH
2)
Engine Cycle:  Expander  Expander  Expander  Expander  Expander
Average Thrust: 16,500 lb
73,260 N
20,800 lb
92,500 N
22,300 lb
99,200 N
14,600 lb
65,200 N
24,750 lb
109,890 N
Chamber Pressure: (Pc) 475 psia 578 psia 610 psia 485 psia 640 psia
Mixture Ratio: 5.5 : 1 5.5 : 1 5.5 : 1 6.0 : 1 5.85 : 1
Isp: 444.4 sec 449 sec 451 sec 365 sec 464 sec
Nozzle Area Ratio: 61 : 1 84 : 1 84 : 1 4.3 : 1 285 : 1
Gimbal Capability: + 4 degrees + 4 degrees + 4 degrees + 9 degrees + 4 degrees
Engine Mass: 310 lb
140 kg
375 lb
170 kg
375 lb
170 kg
316 lb
143 kg
610 lb
277 kg
Engine Thrust to Weight 53 55 59 46 41
Mixture Ratio Control: 4.8-5.8 4.8-5.8 4.8-5.8 5.0-6.0 Fixed
Throttle Range: (%Pc) 100 % (only) 100 % (only) 100 % (only) 100 % to 30% 100 % (only)
Restart Capability: Yes Yes Yes Yes Yes
Engine Size:
     Length / Diameter
70/40 in 90/46 in 90/46 in 42/40 in 163/87 in
Flight Status Flight Qualified Flight Qualified Flight Qualified Flight Demonstrated Flight Qualified
Launch Vehicles: Titan Third Stage & Atlas I and II Second Stage (Centaur) Atlas IIA & Atlas IIAS Second Stage (Centaur) Atlas III & Atlas V Second Stage (Centaur) DC-X & DC-XA Main Propulsion Delta III & Delta IV Second Stage

* Engine performance provided by Pratt & Whitney.


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