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| RL-10 - Specifications |
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Engine Performance
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RL10A3-3A |
RL10A-4 |
RL10A4-2 |
RL10A-5 |
RL10B-2 |
Propellant Combination
Oxidizer
Fuel |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
| 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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