Page 28 - Apollo Moonships

26 On bOard apOllO mOOnships
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THE F–1 ENGINE
Operational between 1967 and 1973, the F-1 remains the most powerful single-nozzle, liquid-fueled rocket engine ever built. The engine used kerosene (RP-1) as fuel and liquid oxygen (LOX) as an oxidizer to generate 1.5 million pounds of thrust. The fuel and the oxidizer were combined in the engine
thrust chamber to produce an efflux of burning gases expelled through an expansion nozzle, which generated a high-speed propulsive jet. The Saturn V S-IC first stage had a cluster of five F-1 engines that consumed 5,700 pounds of propellant per second during its 2.5 minutes of operation. Four engines were mounted outboard of the S-IC stage base, while the other was placed at the center. The four outboard engines were identical and gimbaled a maximum of 6° on the X and Z rocket axes (pitch and yaw movements) to provide thrust vector control and guide the Saturn V in flight. The center engine was fixed and did not have a gimbal system. A total of 60 F-1 engines powered 12 Saturn V rockets during the Apollo Program. All engines fell to the Atlantic Ocean after the S-IC first stage consumed its propellant and went off in flight.
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1 Engine interface panel
2 Gimbal bearing
3 Oxidizer pump
4 Oxidizer dome
5 Fuel pump
6 Fuel dome
7 Heat exchanger
8 Combustion chamber
9 Exhaust manifold
10 Nozzle extension
F–1 ENGINE PROFILE Manufacturer:
First flight:
Last flight:
Length:
Width:
Weight
Thrust:
Combustion temperature: Oxidizer flowrate:
Fuel flowrate: Nozzle exit diameter:
Rocketdyne
9 November 1967
15 May 1973
19 feet
12 feet, 4 inches
18 500 pounds
1 522 000 pounds–force 5 970 °F
3 945 lb/sec
1 738 lb/sec
11 feet, 7 inches
THE J–2 ENGINE
The J–2 was a high performance engine used to drive the Saturn V S–II second stage —which had five of them—, and the S-IVB third stage, which was propelled by only one of them. The engine consumed liquid hydrogen (LH2) and liquid oxygen (LOX) as propellant, producing a maximum thrust of 228 000 pounds in vacuum. All J–2 engines were equipped with gimbal systems, so they could be moved in flight to steer the S–II an S–IVB stages and provide them with pitch, and yaw control. The exception was the center engine of the S-II second stage, mounted in a fixed position. The J–2 was the first rocket engine designed to be restarted multiple times in flight, but this capability was used only in the third stage that burns twice: one to put the Apollo spaceships into a parking orbit around Earth, an another to accelerate the vehicles toward the moon after the ground control verified that all systems worked normally (translunar injection). The engine power could be modified in flight too, using a valve to increase or decrease oxidizer flow (LOX) to the combustion chamber. This operation varies the vacuum thrust between 175 000 and 228 000 pounds.
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J–2 ENGINE PROFILE Manufacturer:
First flight:
Last flight:
Length:
Width:
Weight
Thrust:
Combustion temperature: Oxidizer flowrate:
Fuel flowrate: Nozzle exit diameter:
Rocketdyne
26 February 1966
15 July 1975
11 feet, 1 inches
6 feet, 8 1⁄2 inches
3 480 pounds
228 000 pounds–force 5 750 °F
449 lb/sec
81.7 lb/sec
6 feet, 5 inches
1 Fuel inlet duct
2 Start tank
3 Oxidizer inlet duct
4 Gimbal bearing
5 High pressure oxidizer duct 6 Fuel turbopump
7 Oxidizer turbopump
8 Oxidizer by–pass valve
9 Exhaust manifold
10 Combustion chamber