Instruct: Given a question, retrieve documents that answer the question.
Query: When was the J-2 rocket engine built?
The J-2 was a liquid-fuel cryogenic rocket engine used on NASA's Saturn IB and Saturn V launch vehicles. Built in the U.S. by Rocketdyne, the J-2 burned cryogenic liquid hydrogen (LH2) and liquid oxygen (LOX) propellants, with each engine producing 1,033.1kN (232,250lbf) of thrust in vacuum. The engine's preliminary design dates back to recommendations of the 1959 Silverstein Committee. Rocketdyne won approval to develop the J-2 in June 1960 and the first flight, AS-201, occurred on 26 February 1966. The J-2 underwent several minor upgrades over its operational history to improve the engine's performance, with two major upgrade programs, the de Laval nozzle-type J-2S and aerospike-type J-2T, which were cancelled after the conclusion of the Apollo program.
The J-2X is a liquid-fueled cryogenic rocket engine that was planned for use on the Ares rockets of NASA's Constellation program, and later the Space Launch System. Built in the United States by Aerojet Rocketdyne (formerly, Pratt & Whitney Rocketdyne), the J-2X burns cryogenic liquid hydrogen and liquid oxygen propellants, with each engine producing of thrust in vacuum at a specific impulse ("I") of . The engine's mass is approximately 2,470 kg (5,450 Lb), significantly heavier than its predecessors.
Other facilities that came on line during the decade included J-6 — the world's largest solid rocket motor test facility — and DECADE, a nuclear weapons effects facility. Among facilities that saw significant modernization were the J-4 Liquid Rocket Engine Test Facility, the Aeropropulsion Test Unit and the Engine Test Facility. PWT also saw a major sustainment and modernization program begin. A number of major aerospace programs came to AEDC for testing, including the F-22 Raptor, the Joint Strike Fighter, the F/A-18E/F Super Hornet, the B-2 Spirit stealth bomber, the Pratt & Whitney 4000 series engines for the Boeing 777 and F-119 engines for the F-22 and Joint Strike Fighter, the Boeing 747 and 767 and the RL-10 rocket engine.
The center showcases significant military rockets, including representatives of the Project Nike series, which formed the first ballistic missile defense, MIM-23 Hawk surface-to-air missile, Hermes, an early surface-to-surface missile, MGR-1 Honest John and Corporal nuclear missiles and Patriot, first used in the Gulf War of 1991.
The rocketry collection includes numerous engines, as well. In addition to the authentic engines mounted on rockets on display, the museum has unmounted engines on display, including two F-1s, the type of gigantic engine that produced to push Saturn Vs off the launch pad, J-2 engine that powered second and third stages of the Saturn V, and both Descent and Ascent Propulsion System (DPS/APS) engines for the Lunar Module. Engines from the V-2 engine to NERVA to the Space Shuttle Main Engine are on display as well.
He became NRL project manager for the Viking rocket, which was the first large US liquid-fueled rocket. Roughly half the size, in terms of mass and power, of the V-2, the Viking improved upon it in several important respects. Both were actively guided, and fueled with the same propellants (alcohol and liquid oxygen [LOX]), which were fed to a single rocket engine by turbine-driven pumps. The Viking airframe was designed and built under contract to NRL by the Glenn L. Martin Company. The engine, built by Reaction Motors Inc (RMI) of New Jersey, was the largest liquid-fueled rocket engine developed in the United States up to that time. It produced 89 kN (20000 lbf) of thrust. As was also the case for the V-2, hydrogen peroxide was converted to steam to drive the turbo-pump that fed fuel and LOX into the engine.
Liquid-propellant rocket development has always proceeded in three steps: 
First, prototype engines are tested in a Rocket engine test facility, where the most promising designs are refined during a period of extensive testing. After an engine has been proven, the complete rocket is assembled. In this second step, the rocket is anchored to a static test stand. With the rocket held down, engineers run the engine at full power and refine the system. The test launch is third, when the missile is fired into the sky. Wernher von Braun and his team used this process to develop the V-2 or A4 missile in Germany during WWII.
Each of those engines were Pontiac-built units as in previous years, but offered in 49 of the 50 states. Because Pontiac's own V8 engines could not meet the more stringent California emission standards set for 1977, all Grand Prixs (and other Pontiac models) sold in California were powered by Oldsmobile-built engines including Lansing's "Rocket V8" for J and LJ, and the Rocket V8 standard on the SJ and optional on the other two GPs in California. Due to a shortage of Olds 350 engines resulting from record sales of Cutlasses and reduced production of that engine due to a plant conversion to build a Diesel V8 beginning in 1978, a few 1977 Grand Prixs destined for California reportedly came off the line with a Chevrolet-built V8.
Unlike most liquid-fueled rocket engines in service at the time, the J-2 was designed to be restarted once after shutdown when flown on the Saturn V S-IVB third stage. The first burn, lasting about two minutes, placed the Apollo spacecraft into a low Earth parking orbit. After the crew verified that the spacecraft was operating nominally, the J-2 was re-ignited for translunar injection, a 6.5 minute burn which accelerated the vehicle to a course for the Moon.
The S-IB stage was built by the Chrysler corporation at the Michoud Assembly Facility, New Orleans. It was powered by eight Rocketdyne H-1 rocket engines burning RP-1 fuel with liquid oxygen (LOX). Eight Redstone tanks (four holding fuel and four holding LOX) were clustered around a Jupiter rocket LOX tank. The four outboard engines were mounted on gimbals, allowing them to be steered to control the rocket. Eight fins surrounding the base thrust structure provided aerodynamic stability and control.The S-IVB was built by the Douglas Aircraft Company at Huntington Beach, California. The S-IVB-200 model was similar to the S-IVB-500 third stage used on the Saturn V, with the exception of the interstage adapter, smaller auxiliary propulsion control modules, and lack of on-orbit engine restart capability. It was powered by a single Rocketdyne J-2 engine. The fuel and oxidizer tanks shared a common bulkhead, which saved about ten tons of weight and reduced vehicle length over ten feet.IBM built the instrument unit at the Space Systems Center in Huntsville, Alabama. Located at the top of the S-IVB stage, it consisted of a Launch Vehicle Digital Computer (LVDC), an inertial platform, accelerometers, a tracking, telemetry and command system and associated environmental controls. It controlled the entire rocket from just before liftoff until battery depletion. Like other rocket guidance systems, it maintained its state vector (position and velocity estimates) by integrating accelerometer measurements, sent firing and steering commands to the main engines and auxiliary thrusters, and fired the appropriate ordnance and solid rocket motors during staging and payload separation events.
Introduced in the middle of the 1957 model year, the 1957 and 1958 J-2 Golden Rocket had three two-barrel (twin choke) carburetors with a vacuum-operated linkage. Only the center carburetor was mechanically connected to the throttle pedal, and it was the only one equipped with a choke. When the center carburetor was opened to 60° or more engine vacuum drawn from the windshield wiper pump would simultaneously open the front and rear carburetors. These carburetors did not open progressively; they were either open or closed. The J-2 engine also had a slightly thinner head gasket, raising compression to 10.0:1. It was advertised with gross power and torque ratings of at 4600 rpm and at 2800 rpm. Oldsmobile charged $83 for the J-2 option with the three-speed manual (or in the 98), $314 dollars with the automatic.
During development of rocket engines in Germany during World War II J-2 Diesel fuel was used as the fuel component in several engines including the BMW 109-718. J-2 diesel fuel was also used as a fuel for gas turbine engines.
The NK-33 and NK-43 are rocket engines designed and built in the late 1960s and early 1970s by the Kuznetsov Design Bureau. The NK designation is derived from the initials of chief designer Nikolay Kuznetsov. The NK-33 was among the most powerful LOX/RP-1 rocket engines when it was built, with a high specific impulse and low structural mass. They were intended for the ill-fated Soviet N-1 rocket Moon shot. The NK-33A rocket engine is now used on the first stage of the Soyuz-2-1v launch vehicle.
The RS-2200 Linear Aerospike Engine was derived from the XRS-2200. The RS-2200 was to power the VentureStar single-stage-to-orbit vehicle. In the latest design, seven RS-2200s producing each would boost the VentureStar into low earth orbit. The development on the RS-2200 was formally halted in early 2001 when the X-33 program did not receive Space Launch Initiative funding. Lockheed Martin chose to not continue the VentureStar program without any funding support from NASA. An engine of this type is on outdoor display on the grounds of the NASA Marshall Space Flight Center in Huntsville Alabama.
The cancellation of the Lockheed Martin X-33 by the federal government in 2001 decreased funding availability, but aerospike engines remain an area of active research. For example, a milestone was achieved when a joint academic/industry team from California State University, Long Beach (CSULB) and Garvey Spacecraft Corporation successfully conducted a flight test of a liquid-propellant powered aerospike engine in the Mojave Desert on September 20, 2003. CSULB students had developed their Prospector 2 (P-2) rocket using a 1,000 lb (4.4 kN) LOX/ethanol aerospike engine. This work on aerospike engines continues; Prospector-10, a ten-chamber aerospike engine, was test-fired June 25, 2008.
Further progress came in March 2004 when two successful tests sponsored by the NASA Dryden Flight Research Centre using high-power rockets manufactured by Blacksky Corporation, based in Carlsbad, California. The aerospike nozzles and solid rocket motors were developed and built by the rocket motor division of Cesaroni Technology Incorporated, north of Toronto, Ontario. The two rockets were solid-fuel powered and fitted with non-truncated toroidal aerospike nozzles. Flown at the Pecos County Aerospace Development Center, Fort Stockton, Texas, the rockets achieved apogees of and speeds of about Mach 1.5.
In August or September 1955, the DOD Committee on Special Capabilities chose the NRL proposal, named Vanguard, for the IGY project. The Martin company, which had also built the Viking, became prime contractor for the launch vehicle. The Vanguard rocket was designed as a three-stage vehicle. The first stage was a General Electric X-405 liquid-fueled engine (designated XLR50-GE-2 by the Navy), derived from the engine of the RTV-N-12a Viking. The second stage was the Aerojet General AJ10-37 (XLR52-AJ-2) liquid-fueled engine, a variant of the engine in the RTV-N-10 Aerobee. Finally, the third stage was a solid-propellant rocket motor. All three-stage Vanguard flights except the last one used a motor built by the Grand Central Rocket Company. Vanguard had no fins, and the first and second stages were steered by gimbaled engines. The second stage housed the vehicle's telemetry system, the inertial guidance system and the autopilot. The third stage was spin-stabilized, with the spin imparted by a turntable on the second stage before separation.
The HG-3 was a liquid-fuel cryogenic rocket engine which was designed for use on the upper stages of Saturn rockets in the post-Apollo era. Designed in the United States by Rocketdyne, the HG-3 was to have burned cryogenic liquid hydrogen and liquid oxygen propellants, with each engine producing of thrust during flight. The engine was designed to produce a specific impulse ("I") of 451 seconds in a vacuum, or 280 seconds at sea level. Developed from Rocketdyne's J-2 engine used on the S-II and S-IVB stages, the engine was intended to replace the J-2 on the upgraded S-II-2 and S-IVB-2 stages intended for use on the Saturn MLV, Saturn IB-B and Saturn V/4-260 rockets, with a sea-level optimised version, the HG-3-SL, intended for use on the Saturn INT-17. The engine was cancelled, however, during the post-Apollo drawdown when development of the more advanced Saturn rockets ceased, and never flew, although the engine was later used as the basis for the design of the RS-25 Space Shuttle main engine.
On January 10, 1962, NASA announced plans to build the C-5. The three-stage rocket would consist of: the S-IC first stage, with five F-1 engines; the S-II second stage, with five J-2 engines; and the S-IVB third stage, with a single J-2 engine. The C-5 was designed for a payload capacity to the Moon.
The Executor engine construction started at ARCA in December 2011. The first ground test was scheduled for the middle of 2012. Twelve engines were scheduled to be built in the first phase, until the first flight on board of the Haas 2 rocket in 2013. This first ground flight of the Haas 2 rocket will be for the Google Lunar X Prize Competition. After this flight, the engine will be integrated on the IAR 111 Excelsior supersonic airplane.
The design of the J-2X engine intended for use on the Ares V booster rocket was originally to be similar to the J-2 engine of the Apollo-era Saturn V and Saturn IB rockets. In designing the J-2X, NASA engineers visited museums, searched for Apollo-era documentation and consulted with engineers who worked on the Apollo program. "The mechanics of landing on the Moon and getting off the Moon to a large extent have been solved," said Constellation program manager Jeff Hanley. "That is the legacy that Apollo gave us." However, as the J-2X program progressed, it became apparent that, because of revised safety requirements and the growing mass of the upper stage, it was necessary to scrap the original J-2 design completely and use a completely new design for the J-2X.
The upper stage, derived from the Shuttle's External Tank (ET) and based on the S-IVB stage of the Saturn V, was to be propelled by a single J-2X rocket engine fueled by liquid hydrogen (LH) and liquid oxygen (LOX). The J-2X was derived from the original J-2 engine used during the Apollo program, but with more thrust (~294,000 lbf) and fewer parts than the original engine. On July 16, 2007, NASA awarded Rocketdyne a sole-source contract for the J-2X engines to be used for ground and flight tests. Rocketdyne was the prime contractor for the original J-2 engines used in the Apollo program.
The Space Engineering EDucation Satellite 2 (SEEDS-2) is a Japanese amateur CubeSat picosatellite, built and operated by Nihon University. It was launched by the Indian Space Research Organisation, aboard a PSLV rocket, on 28 April 2008. It was built to replace the SEEDS satellite, which was lost in a launch failure on a Dnepr rocket in July 2006.
"Rocket" was built at a time of rapid development of steam engine technology. It was based on experience gained from earlier designs by George and Robert Stephenson, including the Killingworth locomotive "Blücher" (1814); "Locomotion" (1825); and the "Lancashire Witch" (1828).
"Rocket" was followed by a number of other engines of similar 0-2-2 layout with rear-mounted cylinders built for the L&MR before it opened on 15 September 1830, culminating in the "Northumbrian" (1830), by which time the cylinders were horizontal. Other engines of the rocket design which were delivered to the Liverpool and Manchester railway included "Arrow", "Comet", "Dart" and "Meteor" all being delivered to the railway during 1830.
At around the same time, Stephenson experimented with front-mounted cylinders. The unsuccessful 0-4-0 "Invicta", built in 1829 immediately after "Rocket", still had them at an angle. The successful 2-2-0 locomotive "Planet" (1830) had internal front-mounted cylinders set to the horizontal.
The engine produced a specific impulse (Isp) of 421 seconds (4.13km/s) in a vacuum (or 200 seconds (2.0km/s) at sea level) and had a mass of approximately 1,788 kilograms (3,942lb). Five J-2 engines were used on the Saturn V's S-II second stage, and one J-2 was used on the S-IVB upper stage used on both the Saturn IB and Saturn V. Proposals also existed to use various numbers of J-2 engines in the upper stages of an even larger rocket, the planned Nova. The J-2 was America's largest production LH2-fuelled rocket engine before the RS-25 Space Shuttle Main Engine. A modernized version of the engine, the J-2X, was considered for use on the Earth Departure Stage of NASA's Space Shuttle replacement, the Space Launch System.
The Convair X-12 was the second, more advanced testbed for the Atlas rocket program. It was designed with 2 engines, the booster engine used on the predecessor X-11 plus a sustainer engine. This combination of booster plus sustainer engines was designated the MA-1 engine system. MA-1 was used in Atlas B and Atlas C. MA-1 was the direct predecessor of the MA-2 engine system of Atlas D which in turn was the direct predecessor of the MA-5 engine system used in Atlas Agena and Atlas Centaur launch vehicles. The first flight of the SM-65B (Atlas B) was in July 1958. The SM-65B pioneered the use of these 1.5-stage rocket engines that became a hallmark of the Atlas rocket program. It was also the first rocket to achieve a flight distance that could be considered intercontinental when it flew .
After losing control of the Texas Bullet program, "Pop" Johnson found investors in Henderson, Texas and formed the Regent Aircraft Corporation to build a new design. One investor was Vess Taylor, whose father, S. J. Taylor, had been an investor in Aircraft Manufacturing Company which built the Texas Bullet. J. Mitrovich was chief engineer. The Regent Rocket was slighter larger than the Texas Bullet and powered by a 260 hp Lycoming GSO-435 engine.
Before it can be launched, NASA's proposed Ares I rocket would require both a new, modified five-segment version of the Space Shuttle SRB and the J-2X upper stage engine, a modification of the J-2 engine used on the Saturn V. The proposed Jupiter family can launch with currently available engines but could still take advantage of a more powerful SRB and J-2X upper stage engine should they become available.