24 November 1969: The Apollo 12 command module Yankee Clipper, carrying astronauts Charles “Pete” Conrad, Jr., Mission Commander; Richard F. Gordon, Jr., Command Module Pilot; Alan L. Bean, Lunar Module Pilot; landed in the Pacific Ocean at 20:58:24 UTC, approximately 500 miles east of American Samoa. Mission Time: 244:36:23.
19 November 1969: The Apollo 12 lunar lander, LM-6, named Intrepid by the flight crew, landed at Oceanus Procellarum, The Moon, at 06:54:35 UTC. The lunar module touched down within approximately 600 feet of the intended landing site, the lunar probe Surveyor 3, which had landed there 20 April 1967. The landing site is named Statio Conitum.
Mission Commander, Charles (“Pete”) Conrad, Jr., began the first lunar EVA at 11:32:35 UTC and set foot on the surface at 11:44:22 UTC. Approximately one-half hour later, at 12:13;50 UTC, Lunar Module Pilot Alan L. Bean, Jr., also stepped out onto The Moon.
14 November 1969: At 19:09:22 UTC, the Apollo 12 S-IVB third stage engine reignited for the Trans Lunar Injection maneuver.
One of the necessary features of the Rocketdyne J-2 engine was its ability to restart a second time. The third stage was first used to place the Apollo 12 spacecraft into Earth orbit and was then shutdown. When the mission was ready to proceed toward the Moon, the J-2 was re-started. Using liquid hydrogen and liquid oxygen for propellant, Apollo 12’s S-IVB burned for 5 minutes, 41 seconds. The engine was shut down at 19:15:03 UTC. Trans Lunar Injection was at T plus 2 hours, 53 minutes, 13.94 seconds.
14 November 1969, 16:24:43.4 UTC: The Apollo 12 Saturn 5 passes 42 miles (67 kilometers) altitude at 5,145 miles per hour (8,280 kilometers per hour). The rocket reaches it maximum inertial acceleration of 3.91 g.
At T plus 2 minutes, 42.4 seconds, Apollo 12’s S-IC first stage separates. 0.8 seconds later, the S-II stage Rocketdyne J-2 engines ignited.
14 November 1969: At 16:22:00 UTC (11:22:00 a.m., Eastern Standard Time), the Apollo 12 Saturn V (SA-507) lifted off from Launch Complex 39A, Kennedy Space Center, Cape Canaveral, Florida. This was the second manned space flight to the Moon. The flight crew were Commander Charles “Pete” Conrad, Jr., United States Navy, Mission Commander; Commander Richard F. Gordon, Jr., U.S. Navy, Command Module Pilot; Commander Alan L. Bean, U.S. Navy, Lunar Module Pilot. Their destination was Oceanus Procellarum.
A lightning strike 36.5 seconds after liftoff caused the spacecraft’s automatic systems to shut down three fuel cells, leaving Apollo 12 on battery power. A second lightning strike at T + 52 seconds caused the “8 ball” attitude indicator in the cockpit to fail. A quick thinking ground controller, the “EECOM,” called “Try SCE to Aux.” Alan Bean recalled this from a simulation a year earlier, found the correct switch and restored the failed systems.
Soon after passing Mach 1, the Saturn V rocket encountered the maximum dynamic pressure (“Max Q”) of 682.95 pounds per square foot (0.327 Bar) as it accelerated through the atmosphere. At T + 2:15.24, the center F-1 engine is shut down to reduce acceleration. The remaining four F-1s were shut down at T + 2:41.82. The first stage separation sequence began at T + 2:42.4.
The Saturn V rocket was a three-stage, liquid-fueled heavy launch vehicle. Fully assembled with the Apollo Command and Service Module, it stood 363 feet (110.642 meters) tall. The first and second stages were 33 feet (10.058 meters) in diameter. Fully loaded and fueled the rocket weighed 6,200,000 pounds (2,948,350 kilograms). It could lift a payload of 260,000 pounds (117,934 kilograms) to Low Earth Orbit.
The first stage was designated S-IC. It was designed to lift the entire rocket to an altitude of 220,000 feet (67,056 meters) and accelerate to a speed of more than 5,100 miles per hour (8,280 kilometers per hour). The S-IC stage was built by Boeing at the Michoud Assembly Facility, New Orleans, Louisiana. It was 138 feet (42.062 meters) tall and had an empty weight of 290,000 pounds (131,542 kilograms). Fully fueled with 203,400 gallons (770,000 liters) of RP-1 and 318,065 gallons (1,204,000 liters) of liquid oxygen, the stage weighed 5,100,000 pounds (2,131,322 kilograms). It was propelled by five Rocketdyne F-1 engines, producing 1,522,000 pounds of thrust (6770.19 kilonewtons), each, for a total of 7,610,000 pounds of thrust at Sea Level (33,850.97 kilonewtons). These engines were ignited seven seconds prior to lift off and the outer four burned for 168 seconds. The center engine was shut down after 142 seconds to reduce the rate of acceleration. The F-1 engines were built by the Rocketdyne Division of North American Aviation at Canoga Park, California.
The S-II second stage was built by North American Aviation at Seal Beach, California. It was 81 feet, 7 inches (24.87 meters) tall and had the same diameter as the first stage. The second stage weighed 80,000 pounds (36,000 kilograms) empty and 1,060,000 pounds loaded. The propellant for the S-II was liquid hydrogen and liquid oxygen. The stage was powered by five Rocketdyne J-2 engines, also built at Canoga Park. Each engine produced 232,250 pounds of thrust (1,022.01 kilonewtons), and combined, 1,161,250 pounds of thrust (717.28 kilonewtons).
The Saturn V third stage was designated S-IVB. It was built by Douglas Aircraft Company at Huntington Beach, California. The S-IVB was 58 feet, 7 inches (17.86 meters) tall with a diameter of 21 feet, 8 inches (6.604 meters). It had a dry weight of 23,000 pounds (10,000 kilograms) and fully fueled weighed 262,000 pounds. The third stage had one J-2 engine and also used liquid hydrogen and liquid oxygen for propellant. The S-IVB would place the Command and Service Module into Low Earth Orbit, then, when all was ready, the J-2 would be restarted for the Trans Lunar Injection.
Eighteen Saturn V rockets were built. They were the most powerful machines ever built by man.