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00:02:21 1 Components
00:02:30 1.1 Thrust chamber and gimbal system
00:06:04 1.2 Propellant Feed System
00:06:39 1.2.1 Fuel turbopump
00:07:59 1.2.2 Oxidizer turbopump
00:09:55 1.2.3 Fuel and oxidizer flowmeters
00:10:39 1.2.4 Valves
00:14:29 1.3 Gas generator and exhaust system
00:14:52 1.3.1 Gas generator
00:15:40 1.3.2 Valves
00:16:49 1.3.3 Turbine exhaust system
00:17:30 1.3.4 Heat exchanger
00:18:12 1.4 Start tank assembly system
00:19:16 1.5 Control system
00:20:31 1.5.1 Flight instrumentation system
00:21:47 2 Engine operation
00:21:56 2.1 Start sequence
00:24:25 2.2 Flight mainstage operation
00:24:59 2.3 Cutoff sequence
00:25:37 2.4 Engine restart
00:26:53 3 History
00:27:02 3.1 Development
00:31:48 3.2 Upgrades
00:31:57 3.2.1 J-2S
00:33:28 3.2.2 J-2T
00:34:19 3.2.3 J-2X
00:36:41 4 Specifications
00:36:51 5 See also



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Voice name: en-GB-Wavenet-B


"I cannot teach anybody anything, I can only make them think."
- Socrates


SUMMARY
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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 1,033.1 kN (232,250 lbf) 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 engine produced a specific impulse (Isp) of 421 seconds (4.13 km/s) in a vacuum (or 200 seconds (2.0 km/s) at sea level) and had a mass of approximately 1,788 kilograms (3,942 lb). 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.
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.

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