RL-10
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The RL-10 was America's first liquid hydrogen fueled rocket engine. Six RL-10 engines were used in the S-IV second stage of the Saturn I rocket. One or two RL-10 engines are used in the Centaur upper stages of Atlas and Titan rockets. There were proposals to use RL-10 powered Centaur upper stages on Saturn I, Saturn IB and Saturn V rockets, and the Space Shuttle.
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[edit] Original RL-10 specifications
Thrust (altitude): 15,000 lbf (66.7 kN)
Burn Time: 470 s
Design: Expander cycle
Specific impulse: 433 s (4.25 kN·s/kg)
Engine weight - dry: 298 lb (135 kg)
Height: 68 in (1.73 m)
Diameter: 39 in (0.99 m)
Nozzle expansion ratio: 40 to 1
Propellants: LOX & LH2
Propellant flow: 35 lb/s (16 kg/s)
Contractor: Pratt & Whitney
Vehicle application: Saturn I / S-IV 2nd stage - 6-engines
Vehicle application: Centaur upper stage - 2-engines
[edit] Current design
The RL-10 has been upgraded over the years. The most recent model, the RL-10B-2, powers the Delta IV second stage, as well as the Delta III second stage. It has been significantly modified from the original RL-10 to improve performance. Some of the enhancements include an extendable nozzle and electro-mechanical gimbaling for reduced weight and increased reliability. Current specific impulse is 462 s (equivalent to an exhaust velocity of 4.53 km/s).
RL-10B-2 Specifications [1]
- Thrust (altitude): 24,750 lbf (110.1 kN)
- Design: Expander cycle
- Burn time: 1,152 seconds
- Specific impulse: 462 s (4.53 kN·s/kg)
- Engine weight - dry: 664 lb (301 kg)
- Height: 163 in (4.14 m)
- Diameter: 87 in (2.21 m)
- Expansion ratio: 250 to 1
- Mixture ratio: 5.88 to 1
- Propellants: Liquid oxygen & liquid hydrogen
- Propellant flow: Oxidizer 41.42 lb/s (20.6 kg/s), fuel 7.72 lb/s (3.5 kg/s)
- Contractor: Pratt & Whitney
- Vehicle application: Delta III, Delta IV second stage (1 engine)
[edit] Future use of the RL-10
With the announcement in 2005 of the decision to use an Apollo-like spacecraft configuration for the proposed Orion spacecraft, NASA decided that the new two-stage Lunar Surface Access Module (LSAM) would be powered by liquid hydrogen and liquid oxygen for the LSAM's descent stage (later changed for both stages, as the original plans for using liquid oxygen and liquid methane for the ascent stage has not yet been perfected). Because of the choice of propellents, along with the need of landing the spacecraft in the polar regions of the Moon from an equatorial orbit, NASA decided to use the RL-10 as the main powerplant for the descent stage engine.
Current specifications call for four RL-10 engines to be used on the descent stage and a single RL-10 for the ascent stage. Currently, the RL-10B-2 engines used on the Delta III and Delta IV can thrust at 20% of maximum thrust. Because of the need for the LSAM to hover above the lunar surface, along with providing a smooth landing, the new RL-10 engines must be able to thrust as low as 10%. The use of the RL-10 will allow NASA to keep costs on the lunar program down by using existing hardware, albeit modified to enhance performance or allow for manned spaceflight.
