- J-2 (rocket engine)
Rocketdyne's J-2 was America's largest production liquid hydrogenfueled rocket engine before the Space Shuttle main engines (SSME), and is being revived in support of NASA's return to the Moon.
The J-2 was a major component of the
Saturn Vrocket. Five J-2 engines were used on the S-II, the second stage of the Saturn. One J-2 engine was used on the S-IVB, the third stage of the Saturn V, and the second stage of the Saturn IB. There were proposals to use various numbers of J-2 engines in the upper stages of the planned Nova rocket.
A unique characteristic of the J-2 engine (at the time) was its ability to re-start after shutdown. The J-2 engine on the S-IVB was intended to burn twice. The first burn, lasting for about two minutes, placed the Apollo spacecraft into earth orbit, and then shut down. After the crew members verified that the spacecraft was operating nominally, the J-2 was re-ignited for
translunar injection. This 6.5 minute burn accelerated the Apollo spacecraft to escape velocity, and on a course for the moon.
An experimental program to improve the performance of the J-2 was started in 1964 as the J-2X (not to be confused with a later variant by the same name). The main change to the original J-2 design was to change from the gas generator cycle to a
tap-off cyclewhich supplied the hot gas from a tap on the combustion chamber instead of a separate burner. In addition to removing parts from the engine, it also reduced the difficulty of starting up the engine and properly timing various combustors.
Additional changes included a throttling system for wider mission flexibility, which also required a variable mixture system to properly mix the fuel and oxygen for a variety of different operating pressures. It also included a new "Idle Mode" which produced little thrust and could be used for on-orbit maneuvering or to settle the fuel tanks on-orbit prior to a burn.
During the experimental program, Rocketdyne also produced a small run of six pre-production models for testing, the J-2S. These were test fired many times between 1965 and 1972, for a total of 30,858 seconds burn time. In 1972 it became clear that follow-on orders for further Saturn boosters would not be forthcoming, and the program was shut down. NASA did consider using the J-2S on a number of different missions, and for some time a set of five were to power the
Space Shuttle, a configuration that can be seen on early diagrams.
While work on the J-2S continued, NASA also funded a design effort to use the J-2S turbomachinery and plumbing with a new aerospike nozzle. This would improve performance even further, notably for the lower
S-IIstage that operated primarily in the atmosphere. Two versions were built, the J-2T-200k that provided 200,000 lbf (890 kN) thrust, allowing it to be "dropped in" to the existing S-II and S-IVB stages, and the J-2T-250k of 250,000 lbf.
Like the J-2S, work on the J-2T had progressed to a lengthy series of ground-based test runs, but further development was ended in the post-Apollo draw-down.
A new variant of this engine, called the J-2X, is being designed to support the upcoming
Project Constellationand its Apollo-based Orion Spacecraft, which will replace the Space Shuttleupon its retirement in 2010. Originally the plan called for two J-2X engines to be used as the powerplant only for the Earth Departure Stage(EDS). One J-2X engine will generate 294,000 lbf for the EDS. [Cite web |url=http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextoid=2e35288d1c83c010VgnVCM1000000881000aRCRD&prid=e480c230314d3110VgnVCM100000c45a529f____ |title=Press release preview |accessdate=2008-01-28 ]
With the expense of converting the SSME from a ground-started engine to an air-startable engine, along with the expense of constructing and pre-firing new SSMEs for each mission, NASA decided to also adopt the J-2X engine for the second stage of the
Ares I. This decision, made on February 18, 2006, would allow NASA to be able to launch the Ares I rocket within 3 years after the retirement of the Shuttle in 2010and allow the launching of the Orion spacecraft by 2014. In addition, the use of the J-2X on both rockets will allow NASA to simplify Orion support construction. NASA began construction of a new test stand for altitude testing of J-2Xengines at Stennis Space Center (SSC) on 23 August 2007. [cite web | title = NASA's Stennis Space Center Marks New Chapter in Space Exploration | url = http://www.nasa.gov/home/hqnews/2007/aug/HQ_07180_Stennis_groundbreaking.html | publisher = NASA] Between December 2007 and May 2008, nine tests of heritage J-2 engine components were conducted at SSC in preparation for the design of the J-2X engine. [cite web | title = NASA Successfully Completes First Series of Ares Engine Tests | url = http://www.nasa.gov/home/hqnews/2008/may/HQ_08116_power_pack_tests.html | publisher = NASA | date = 2008-05-08]
The new J-2X will be designed to be more efficient and simpler to build than its Apollo J-2 ancestor, and cost less than the SSME. It will use a gas generator power cycle. [http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextoid=84ee34890cb06110VgnVCM1000004601000aRCRD]
On July 16, 2007
NASAofficially awarded Pratt and Whitney Rocketdyne, Inc. a $1.2 billion dollar contract "for design, development, testing and evaluation of the J-2X engine that will power the upper stages of the Ares I and Ares V launch vehicles." [cite web | title = NASA Awards Upper Stage Engine Contract for Ares Rockets | publisher = NASA | date = 2007-07-16| url = http://www.nasa.gov/home/hqnews/2007/jul/HQ_C07030_J2X_Contract_prt.htm | accessdate=2007-07-17] On Sept. 8, 2008 Rocketdyne announced successful testing of a gas generatorlike those which will be used for J-2X engines. [cite web |url=http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextoid=586f52703643c110VgnVCM100000c45a529fRCRD |title=Pratt & Whitney Rocketdyne Completes Successful Test of J-2X Gas Generator |date=2008-09-08 |publisher=Rocketdyne]
Thrust (altitude): 200,000 lbf (890 kN)
Burn time: 500 s
Specific impulse: 418 s (4099 m/s)
Engine weight - dry: 3,480 lb (1,579 kg)
Engine weight - burnout: 3,609 lb (1,637 kg)
Exit to Throat Area ratio: 27.5 to 1
Propellants: LOX & LH2
Mixture ratio: 5.50
Saturn IB& Saturn V/ S-IVBupper stage - 1-engine
Saturn V/ S-II2nd stage - 5-engines
Vacuum thrust: 265,000 lbf (1179 kN)
Vacuum specific impulse: 436 s (4276 m/s)
Basic engine weight - dry: 3,235 lb (1,467 kg)
Engine weight with accessories - dry: 3,800 lb (1,724 kg)
Propellants: LOX & LH2
Mixture ratio: 5.50
Contractor: Rockwell International/Rocketdyne
Vacuum thrust: 294,000 lbf
Vacuum specific impulse: 448 s
Basic engine weight - dry: 5,450 lb
Propellants: LOX & LH2
Contractor: Pratt & Whitney Rocketdyne
Vehicle Application: Ares I upper stage - 1 engine & Ares V upper stage - 1 engine
* [http://www.astronautix.com/engines/j2.htm Encyclopedia Astronautica link about the J-2]
* [http://www.astronautix.com/engines/j2s.htm Encyclopedia Astronautica link about the J-2S]
Wikimedia Foundation. 2010.
Look at other dictionaries:
rocket engine — n. a reaction engine carrying its liquid fuel and liquid oxidizing agent in separate tanks: the fuel and oxidizer are brought together and ignited in a combustion chamber to create hot, explosive gas that escapes through a nozzle, providing a… … English World dictionary
Rocket engine — RS 68 being tested at NASA s Stennis Space Center. The nearly transparent exhaust is due to this engine s exhaust being mostly superheated steam (water vapor from its propellants, hydrogen and oxygen) … Wikipedia
Rocket engine nozzle — A rocket engine nozzle is a propelling nozzle usually of the de Laval type used in a rocket engine to expand and accelerate the combustion gases, from burning propellants, so that the exhaust gases exit the nozzle at hypersonic… … Wikipedia
Rocket engine test facility — A rocket engine test facility is a location where rocket engines may be tested on the ground, under controlled conditions. A ground test program is generally required before the engine is certified for flight. Ground testing is very inexpensive… … Wikipedia
rocket engine — noun a jet engine containing its own propellant and driven by reaction propulsion • Syn: ↑rocket • Hypernyms: ↑jet engine • Hyponyms: ↑booster, ↑booster rocket, ↑booster unit, ↑ … Useful english dictionary
Rocket Engine Test Facility — Infobox nrhp name =Rocket Engine Test Facility nrhp type = nhl caption = 1982 photograph location= Lewis Research Center, Cleveland, Ohio locmapin = Ohio area = built =1957 architect= National Advisory Committee for Aeronautics (NACA)… … Wikipedia
rocket engine — reaktyvusis variklis statusas T sritis fizika atitikmenys: angl. jet engine; jet propulsion engine; rocket engine vok. Düsenmotor, m; Strahltriebwerk, n rus. реактивный двигатель, m pranc. moteur à réaction, m; réacteur, m … Fizikos terminų žodynas
rocket engine — raketinis variklis statusas T sritis fizika atitikmenys: angl. rocket engine; rocket motor vok. Raketenantrieb, m; Raketenantriebswer, n; Raketenmotor, m rus. ракетный двигатель, m pranc. moteur fusée, m … Fizikos terminų žodynas
rocket engine — raketinis variklis statusas T sritis Energetika apibrėžtis Reaktyvinis variklis, kurio darbui nereikia aplinkos terpės (oro). atitikmenys: angl. rocket engine; rocket motor vok. Raketenmotor, m rus. ракетный двигатель, m pranc. moteur à fusée, m; … Aiškinamasis šiluminės ir branduolinės technikos terminų žodynas
rocket engine — raketinis variklis statusas T sritis Gynyba apibrėžtis Reaktyvinis variklis, nenaudojantis savo darbui aplinkos medžiagų; pagrindinis variklio tipas kovinėse raketose, astronautikoje (kosmonautikoje). Daugiausia naudojami cheminiai raketiniai… … Artilerijos terminų žodynas
rocket engine — raketinis variklis statusas T sritis apsauga nuo naikinimo priemonių apibrėžtis Reaktyvinis variklis, nenaudojantis savo darbui aplinkos medžiagos. Daugiausia naudojami cheminiai raketiniai varikliai, kuriuose deginamas cheminis kietasis,… … Apsaugos nuo naikinimo priemonių enciklopedinis žodynas