Tag Archives: AS-506

16 July 1969, 13:34:30 UTC, T + 2:30

Apollo 11 gains altitude while the first stage Rocketdyne F-1 engines increase thrust. (NASA)
Apollo 11 gains altitude while the first stage Rocketdyne F-1 engines increase thrust. (NASA)

16 July 1969: Apollo 11/Saturn V AS-506 accelerates with all five Rocketdyne F-1 engines burning. As the rocket climbs through thinner atmosphere, the engines become more efficient and the total thrust for the S-IC first stage increases from 7,648,000 pounds of thrust to 9,180,000 pounds of thrust at about T+1:23.0.

In order to limit acceleration, a pre-planned signal to cut off the center engine is sent at T+2:15.2 (Center Engine Cut-Off, “CECO”). As the first stage burns fuel at a rate of 13 tons per second, the rapidly deceasing weight of the Saturn V and the increasing efficiency of the F-1 engines could cause the limits of vehicle acceleration to be exceeded.

Launch Vehicle acceleration vs. time

By T+2:30, the Saturn V has reached an altitude of 39 miles (62.8 kilometers) and is 55 miles (88.5 kilometers) downrange.

The photograph above was taken by a 70mm telescopic camera aboard a USAF/Boeing EC-135N A/RIA (Apollo Range Instrumentation Aircraft) serial number 60-374. The airplane is in the collection of the National Museum of the United States Air Force.

© 2019, Bryan R. Swopes

16 July 1969, 13:32:00.3 UTC, T plus 00.00.00.3

Apollo 11/Saturn V AS-506 at the moment of first stage ignition, T -6.9 seconds, 13:31:53.9 UTC, 16 July 1969. (NASA)

On Wednesday morning, 16 July 1969, the Apollo 11/Saturn V launch vehicle, AS-506), stood on the pad at Launch Complex 39A, Kennedy Space Center, Cape Canaveral, Florida. On board were Neil Alden Armstrong, Mission Commander; Michael Collins, Command Module Pilot; and Edwin E. Aldrin, Jr., Lunar Module Pilot. Their destination was Mare Tranquillitatis, The Moon.

Neil Alden Armstrong, Michael Collins and Edwin E. Aldrin, Jr., flight crew of Apollo 11, 16–23 July 1969. (NASA)

The cryogenic liquid oxygen in the rocket’s propellant tanks cooled the humid Florida air to the point that frost formed on the tanks’ skin.

Saturn V AS-506 reaches full thrust. (NASA)

The mission was on schedule. At T – 6.1 seconds (13:31:53.9 UTC) the first of the five F-1 engines ignited, followed in quick succession by the others. When the engines had reached full thrust, the pad’s hold-down arms were released. First Motion—10.47 m/s² (34.35 ft/s²)—1.07 gs, was detected at T + 0.3 seconds (13:32:00.3 UTC, 9:32:00.3 a.m., Eastern Daylight Time). The umbilical was released at T + 0.6 seconds. The Saturn V cleared the gantry tower and rolled onto its programmed course.

LIFT OFF! Apollo 11 (AS-506) launches from Launch Complex 39A, Kennedy Space Center, Cape Canaveral, Florida, at 13:32:00.06 UTC, 16 July 1969. (NASA)

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, 0.15 inches (110.64621 meters) tall, from the tip of the escape tower to the bottom of the F-1 engines. Fully loaded and fueled, AS-506 weighed  6,477,875 pounds (2,938,315 kilograms).

Apollo 11 climbs away from the pad. (NASA)

The Saturn V 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, 33 feet, 1.2 inches (10.089 meters) in diameter, and had an empty weight of 287,531 pounds (130,422 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 5,023,648 pounds (2,131,322 kilograms). It was propelled by five Rocketdyne F-1 engines, which were built by the Rocketdyne Division of North American Aviation, Inc., at Canoga Park, California.

Saturn V first stage Rocketdyne F-1 engines running, producing 7.5 million pounds of thrust. Ice falls from the rocket. The hold-down arms are releasing. (NASA)

The AS-506 S-IC stage’s five F-1 engines  produced 7,552,000 pounds of thrust (33,593 kilonewtons). According to the post-mission flight evaluation report, “The F-1 engines performance levels during the AS-506 flight showed the smallest deviations of any S-IC Flight.” The center engine shut down at T + 135.20 to limit the rocket’s acceleration, and the outer four were shut down at T + 161.63 seconds.

The S-II second stage was built by North American Aviation, Inc., at Seal Beach, California. It was 81 feet, 7 inches (24.87 meters) tall and had the same diameter as the first stage. The AS-506 second stage weighed 79,714 pounds (36,158 kilograms), dry, and 1,058,140 pounds (479,964 kilograms), fueled. 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, and combined, 1,161,250 pounds of thrust.

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). The AS-506 S-IVB third stage had a dry weight of 24,852 pounds (11,273 kilograms) and fully fueled, it weighed 262,613 pounds (119,119 kilograms). The third stage had one J-2 engine which also used liquid hydrogen and liquid oxygen for propellant. At the first burn, the J-2 produced 202,603 pounds of thrust (901.223 kilonewtons). 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. At this second burn, it produced 201,061 pounds  of thrust (894.364 kilonewtons).

Apollo 11 Command and Service Module CSM-107 being assembled to the SA-506 Saturn V in the Vehicle Assembly Building, April 1969. (NASA)

The Apollo Command/Service Module was built by the Space and Information Systems Division of North American Aviation, Inc., at Downey, California. The Apollo 11 Command and Service Module, CSM-107, weighed 109,646 pounds (49,735 kilograms).

The SPS engine was an AJ10-137, built by Aerojet General Corporation of Azusa, California. It burned a hypergolic fuel combination of Aerozine 50 and nitrogen tetraoxide, producing 20,500 pounds of thrust (91.19 kilonewtons). It was designed for a 750 second burn, or 50 restarts during a flight.

The Apollo Lunar Module was built by Grumman Aerospace Corporation to carry two astronauts from lunar orbit to the surface, and return. There was a descent stage and ascent stage. The LM was intended only for operation in the vacuum of space, and was expended after use.

The LM was 23 feet, 1 inches (7.036 meters) high with a maximum landing gear spread of 31 feet (9.449 meters). It weighed 33,500 pounds (15,195 kilograms). The spacecraft was designed to support the crew for 48 hours, though in later missions, this was extended to 75 hours.

The Descent Stage was powered by a single TRW LM Descent Engine. The LMDE used hypergoloc fuel and was throttleable. It produced from 1,050 pounds of thrust (4.67 kilonewtons) to 10,125 pounds (45.04 kilonewtons). The Ascent Stage was powered by a Bell Aerospace Lunar Module Ascent Engine. This also used hypergolic fuels. It produced 3,500 pounds of thrust (15.57 kilonewtons).

Eighteen Saturn V rockets were built.

The Moon. The terminator is bisecting Mare Tranquillitatis. (Rob Pettengill)

Note: All timing, acceleration, weight/mass, and thrust data is from: Saturn V Launch Vehicle Flight Evaluation Report—AS-506, George C. Marshall Space Flight Center, MPR-SAT-FE-69-9, 20 September 1969.

© 2018, Bryan R. Swopes

20 May 1969

Apollo 11/Saturn V (AS-506) on the crawler transporter at Kennedy Space center, Cape Canaveral Florida, 20 May 1969. (NASA)
Apollo 11/Saturn V (AS-506) and its Mobile Launch Platform on one of the two Crawler–Transporters at Kennedy Space Center, Cape Canaveral, Florida, 20 May 1969. (NASA)

20 May 1969: The Apollo 11 Saturn V (SA-506) “stack” was rolled out of the Vehicle Assembly Building aboard a Mobile Launch Platform, carried by a Crawler-Transporter, and moved to Launch Complex 39A. The rocket would be launched for the Moon at 13:32:00 UTC, 16 July 1969.

The two Crawler-Transporters are the world’s largest self-propelled land vehicles. They were designed and built by Marion Power Shovel Company, Marion, Ohio, and were assembled on Merritt Island. (The Crawlerway connected the island to mainland Florida, so that it now forms a peninsula.) They are 131 feet (39.9 meters) long and 113 feet  (34.4 meters) wide. The height is adjustable from 20 feet (6.1 meters) to 26 feet (7.9 meters). The load deck is 90 feet × 90 feet (27.4 × 27.4 meters). The transporters weigh 2,721 metric tons (3,000 tons).

A Crawler-Transporter carrying a Mobile Launch Platform. (NASA)

The Crawler-Transporters were powered by two 10,687.7-cubic-inch-displacement (175.1 liters) liquid-cooled, turbosupercharged, American Locomotive Company (ALCO) V-16 251C 45° sixteen-cylinder 4-cycle diesel engines. This engine produced 2,750 horsepower. The engines drive four 1,000 kilowatt electric generators. These in turn supply electricity to sixteen 375 horsepower traction motors.

Two 1,065 horsepower White-Superior eight-cylinder diesel engines provide electrical and hydraulic power to operate the crawlers’ systems. The hydraulic system operates at 5,200 p.s.i.

The maximum loaded speed is 0.9 miles per hour (1.4 kilometers per hour).

Since the time of the Apollo and Space Shuttle Programs, the Crawler-Transporters have been upgraded to handle the Space Launch System (SLS) heavy-lift rockets. The original ALCO locomotive engines have been replaced by two Cummins QSK95 16-cylinder diesel/C3000-series 1,500 kW power generation units. The new engine displaces 5,797 cubic inches and produces a maximum 4,200 horsepower at 1,200 r.p.m. The QSK95 has 46% less displacement than the old ALCO, weighs 39% less, but produces 57% more horsepower. The generators also double the electrical output.

Inside the Vehicle Assembly Building, a Cummins power generation unit is lowered into a Crawler-Transporter. (NASA)

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.

A Saturn V S-IC first stage being lifted inside the Vehicle Assembly Building. (NASA 68-HC-70)

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, each, for a total of 7,610,000 pounds of thrust at Sea Level. 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.

A Saturn V S-II second stage being positioned above the S-IC first stage. (NASA MSFC-67-58331)

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, and combined, 1,161,250 pounds of thrust.

A Saturn V S-IVB third stage with its Rocketdyne J-2 engine. ( NASA)

The Saturn V third stage was designated S-IVB. It was built by McDonnell Douglas Astronautics 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 wou 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.

Saturn V SA-506 traveles the 3.5 mile "crawlerway" from the Vehicle Assembly Building to Launch Complex 39A, 20 May 1969. (NASA)
Saturn V SA-506 travels the 3.5 mile “crawlerway” from the Vehicle Assembly Building to Launch Complex 39A, 20 May 1969. (NASA)

© 2019, Bryan R. Swopes