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RL10

An RL10A-4 engine in London's Science Museum
Country of origin	United States of America
First flight	1962 (RL10A-1)
Manufacturer	Aerojet Rocketdyne
Application	Upper stage engine
Associated LV	Atlas Saturn I Titan IIIE Titan IV Delta III Delta IV DC-X (canceled) Space Shuttle (canceled) Space Launch System OmegA (canceled) Vulcan
Status	In production
Liquid-fuel engine
Propellant	Liquid oxygen / liquid hydrogen
Mixture ratio	5.88:1
Cycle	Expander cycle
Configuration
Nozzle ratio	84:1 or 280:1
Performance
Thrust, vacuum	110.1 kN (24,800 lbf)
Specific impulse, vacuum	465.5 seconds (4.565 km/s)
Dimensions
Length	4.15 m (13.6 ft) w/ nozzle extended
Diameter	2.15 m (7 ft 1 in)
Dry weight	301 kg (664 lb)
Used in
Centaur, DCSS, S-IV
References
References	[1]
Notes	Performance values and dimensions are for RL10B-2.

The RL10 is a liquid-fuel cryogenic rocket engine built in the United States by Aerojet Rocketdyne that burns cryogenic liquid hydrogen and liquid oxygen propellants. Modern versions produce up to 110 kN (24,729 lb_f) of thrust per engine in vacuum. Three RL10 versions are in production for the Centaur upper stage of the Atlas V and the DCSS of the Delta IV. Three more versions are in development for the Exploration Upper Stage of the Space Launch System and the Centaur V of the Vulcan rocket.^[2]

The expander cycle that the engine uses drives the turbopump with waste heat absorbed by the engine combustion chamber, throat, and nozzle. This, combined with the hydrogen fuel, leads to very high specific impulses (I_sp) in the range of 373 to 470 s (3.66–4.61 km/s) in a vacuum. Mass ranges from 131 to 317 kg (289–699 lb) depending on the version of the engine.^[3][4]

History

The RL10 was the first liquid hydrogen rocket engine to be built in the United States, with development of the engine by Marshall Space Flight Center and Pratt & Whitney beginning in the 1950s. The RL10 was originally developed as a throttleable engine for the USAF Lunex lunar lander.^[5]

The RL10 was first tested on the ground in 1959, at Pratt & Whitney's Florida Research and Development Center in West Palm Beach, Florida.^[6][7] The first successful flight took place on November 27, 1963.^[8][9] For that launch, two RL10A-3 engines powered the Centaur upper stage of an Atlas launch vehicle. The launch was used to conduct a heavily instrumented performance and structural integrity test of the vehicle.^[10]

Multiple versions of this engine have been flown. The S-IV of the Saturn I used a cluster of six RL10A-3S, a version which was modified for installation on the Saturn^[11] and the Titan program included Centaur D-1T upper stages powered by two RL10A-3-3 Engines.^[11][12]

Four modified RL10A-5 engines were used in the McDonnell Douglas DC-X.^[13]

A flaw in the brazing of an RL10B-2 combustion chamber was identified as the cause of failure for the 4 May 1999 Delta III launch carrying the Orion-3 communications satellite.^[14]

The DIRECT version 3.0 proposal to replace Ares I and Ares V with a family of rockets sharing a common core stage recommended the RL10 for the second stage of the J-246 and J-247 launch vehicles.^[15] Up to seven RL10 engines would have been used in the proposed Jupiter Upper Stage, serving an equivalent role to the Space Launch System Exploration Upper Stage.

Common Extensible Cryogenic Engine

In the early 2000s, NASA contracted with Pratt & Whitney Rocketdyne to develop the Common Extensible Cryogenic Engine (CECE) demonstrator. CECE was intended to lead to RL10 engines capable of deep throttling.^[16] In 2007, its operability (with some "chugging") was demonstrated at 11:1 throttle ratios.^[17] In 2009, NASA reported successfully throttling from 104 percent thrust to eight percent thrust, a record for an expander cycle engine of this type. Chugging was eliminated by injector and propellant feed system modifications that control the pressure, temperature and flow of propellants.^[18] In 2010, the throttling range was expanded further to a 17.6:1 ratio, throttling from 104% to 5.9% power.^[19]

Early 2010s possible successor

In 2012 NASA joined with the US Air Force (USAF) to study next-generation upper stage propulsion, formalizing the agencies' joint interests in a new upper stage engine to replace the Aerojet Rocketdyne RL10.

"We know the list price on an RL10. If you look at cost over time, a very large portion of the unit cost of the EELVs is attributable to the propulsion systems, and the RL10 is a very old engine, and there's a lot of craftwork associated with its manufacture. ... That's what this study will figure out, is it worthwhile to build an RL10 replacement?"

— Dale Thomas, Associated Director Technical, Marshall Space Flight Center^[20]

From the study, NASA hoped to find a less expensive RL10-class engine for the upper stage of the Space Launch System (SLS).^[20][21]

USAF hoped to replace the Rocketdyne RL10 engines used on the upper stages of the Lockheed Martin Atlas V and the Boeing Delta IV Evolved Expendable Launch Vehicles (EELV) that were the primary methods of putting US government satellites into space.^[20] A related requirements study was conducted at the same time under the Affordable Upper Stage Engine Program (AUSEP).^[21]

Improvements

The RL10 has evolved over the years. The RL10B-2 that was used on the DCSS had improved performance, an extendable carbon-carbon nozzle, electro-mechanical gimbaling for reduced weight and increased reliability, and a specific impulse of 465.5 seconds (4.565 km/s).^[22][23]

As of 2016, Aerojet Rocketdyne was working toward incorporating additive manufacturing into the RL10 construction process. The company conducted full-scale, hot-fire tests on an engine with a printed main injector in March 2016,^[24] and on an engine with a printed thrust chamber assembly in April 2017.^[25]

Current applications for the RL10

• Atlas V Centaur (rocket stage): The single engine centaur (SEC) version uses the RL10C-1,^[2] while the dual engine centaur (DEC) version retains the smaller RL10A-4-2.^[26] An Atlas V mission (SBIRS-5) marked the first use of the RL10C-1-1 version. The mission was successful but observed unexpected vibration, and further use of the RL10C-1-1 model is on hold until the problem is better understood.^[27] The engine was used again successfully on SBIRS-6.
• Delta Cryogenic Second Stage: The current DCSS has an RL10C-2-1 with an extensible nozzle.^[2][28][29]
• Interim Cryogenic Propulsion Stage : The Interim Cryogenic Propulsion Stage or ICPS is used for the SLS and is similar to the DCSS, except that the engine is an RL10B-2 and it is adapted to fit on top of the 8.4 meter diameter core stage with four RS-25 Space Shuttle Main Engines.
• Vulcan Centaur's Centaur V stage: On May 11, 2018, United Launch Alliance (ULA) announced that the RL10 upper stage engine had been selected for ULA's next-generation Vulcan Centaur rocket following a competitive procurement process.^[30] Centaur V will normally use the RL10C-1-1,^[2] but on Vulcan Centaur Heavy the RL10C-X will be used.^[31] Vulcan flew its successful maiden flight on January 8, 2024.^[32]

Engines in development

• Exploration Upper Stage (EUS): EUS will initially use four RL10C-3 engines. When RL10C-X becomes available, the C-3 engines will be swapped out for C-X.^[33]
• OmegA Upper Stage: In April 2018, Northrop Grumman Innovation Systems announced that two RL10C-5-1 engines would be used on OmegA in the upper stage.^[34] Blue Origin's BE-3U and Airbus Safran's Vinci were also considered before Aerojet Rocketdyne's engine was selected. OmegA development was halted after it failed to win a National Security Space Launch contract.^[35]

Advanced Cryogenic Evolved Stage

As of 2009^[update], an enhanced version of the RL10 was proposed to power the Advanced Cryogenic Evolved Stage (ACES), a long-duration, low-boiloff extension of existing ULA Centaur and Delta Cryogenic Second Stage (DCSS) technology for the Vulcan launch vehicle.^[36] Long-duration ACES technology is intended to support geosynchronous, cislunar, and interplanetary missions. Another possible application is as in-space propellant depots in LEO or at L₂ that could be used as way-stations for other rockets to stop and refuel on the way to beyond-LEO or interplanetary missions. Cleanup of space debris was also proposed.^[37]

Table of versions

Partial specifications

All versions

• Contractor: Pratt & Whitney
• Propellants: liquid oxygen, liquid hydrogen^[23]
• Design: expander cycle^[58]

RL10A

• Thrust (altitude): 15,000 lbf (66.7 kN)^[38]
• Specific impulse: 433 seconds (4.25 km/s)
Zdroj:https://en.wikipedia.org?pojem=RL10
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