Apollo 16 (AS-511) lifts off from Launch Complex 39A, Kennedy Space Center, Cape Canaveral, Florida, at 17:54:00 UTC, 16 April 1972. (NASA)
16 April 1972: At 17:54:00 UTC (12:54 p.m., Eastern Standard Time), Apollo 16 was launched from Launch Complex 39A at the Kennedy Space Center, Cape Canaveral, Florida. Aboard were Captain John Watts Young, United States Navy, the Mission Commander, on his fourth space flight; Lieutenant Commander Thomas Kenneth Mattingly II, U.S. Navy, Command Module Pilot, who had been scheduled for the Apollo 13 mission; and Lieutenant Colonel Charles Moss Duke, Jr., U.S. Air Force, Lunar Module Pilot. Apollo 16 was the tenth manned Apollo mission, and the fifth to land on The Moon. The landing site was in the Descartes Highlands.
Flight Crew of Apollo 16, left to right, Thomas K. Mattingly II, John W. Young, and Charles M. Duke, Jr. (NASA)
John Young had been a Navy test pilot before being assigned to NASA as an astronaut. He was the pilot for Gemini 3; backup pilot, Gemini 6A; commander, Gemini 10; command module pilot for Apollo 10; backup commander, Apollo 13; and commander, Apollo 16. He retired from the U.S. Navy in 1976 after 25 years of service. He would go on to command the first space shuttle flight, Columbia (STS-1) and then STS-9. He was scheduled to command Atlantis (STS-61-J). John Young retired from NASA in 2004, as one of the world’s most experienced astronauts.
John Watts Young (NASA)
The Saturn V lifted off at T + 000:00:00.59 and quickly accelerated, reaching Mach 1 one minute, 7.5 seconds after launch (T + 01:07.5). The S-IC first stage engines cut off and the stage separated at T + 02:43.5. The S-II stage continued to drive the space craft, and Apollo 16 entered Earth orbit at 18:05:56.21 UTC.
Apollo 16/Saturn V AS-511 at Pad 39A. (NASA AP16-KSC-71PC-771)
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 (2,812,273 kilograms).¹ 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 vertical Assembly Building. (NASA 68-HC-70)
The first stage was designated Saturn 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 Saturn 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 Saturn 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.
Apollo 16 AS-511 clears the tower at Launch Complex 39A, Kennedy Space Center, Cape Canaveral, Florida, 17:54:00 UTC, 16 April 1972. (NASA)Apollo 16 accelerates toward Earth orbit, 16 April 1972.(LIFE Magazine)
¹ At First Motion (T + 000.00.00.3) the Vehicle Weight of Apollo 16/Saturn V AS-511 was calculated at 6,439,605 pounds (2,920,956 kilograms).
10:21 a.m., PST, 14 April 1981: The first space shuttle, Columbia, touches down on Runway 23, Edwards Air Force Base, California, completing the first space flight of the United States’ shuttle program.
With its two-man crew, commander, veteran astronaut John W. Young, and pilot Robert L. Crippen, Columbia traveled 1,074,567 miles (1,729,348 kilometers) on its 37-orbit journey, in 54 hours, 20 minutes, 53 seconds.
Damage to Apollo 13’s Service Module, photographed just after separation 17 April 1970. (NASA Apollo 13 Image Library AS13-59-8500)
13 April 1970: At 10:07:53 p.m. Eastern Standard Time (mission elapsed time 55:54:53), while Apollo 13 and its crew, James A. Lovell, Jr., John L. Swigert and Fred W. Haise, were approximately 200,000 miles (322,000 kilometers) from Earth enroute to a landing at the Fra Mauro Highlands on The Moon, an internal explosion destroyed the Number 2 oxygen tank¹ in the spacecraft’s Service Module. The Number 1 tank was also damaged. Two of three fuel cells that supplied electrical power to the spacecraft failed.
Jack Swigert radioed Mission Control: “I believe we’ve had a problem here.” ²
Mission Control: “This is Houston. Say again, please.”
Jim Lovell: “Houston, we’ve had a problem. Main B Bus undervolt.”
With oxygen supplies depleted and power failing, the lunar landing mission had to be aborted, and the three-man crew evacuated the Command Module and took shelter in the Lunar Module.
This was a life-threatening event.
The story of Apollo 13 and its crew and their journey home is well known. The 1995 Ron Howard/Universal Pictures film, “Apollo 13,” takes some artistic license, but is generally accurate and realistic.
Flight Director Gene Kranz (right of center, with his back to the camera) in Mission Control, Houston, Texas, a few minutes before the accident. (NASA Apollo 13 Image Library Image AP13-S70-35139)
Five years before Apollo 13 was launched, an engineering decision had been made to increase the spacecraft electrical system from 28 volts to 65 volts. This required that every electrical component on the vehicle had to be changed to accommodate the increased power. The after-accident investigation found that the team that designed the cooling fans for the oxygen tanks was never informed of the change.
During the actual flight, the wiring inside the tank heated to approximately 1,000 °F. (538 °C.), and in the pressurized pure oxygen, the insulation caught fire. The tank, originally installed on Apollo 10, had been dropped when it was removed for modification. It was repaired and later used on Apollo 13, however, it had been weakened by the damage. The extreme pressure caused by the heat of the burning electrical wiring in the containment caused the tank to rupture.
The damaged Service Module after being jettisoned from the Command Module, photographed from the Lunar Module. The Moon is visible between the two. (NASA)
¹ Serial number 10024X-TA0009
² The official mission transcript attributes this statement to Jim Lovell, however, in Lovell’s recollection, it was made by Swigert.
Apollo 6/Saturn V AS-502 launch from LC-39A, 12:00:01.38 UTC, 4 April 1968. (National Aeronautics and Space Administration NASA 68-HC-201)
4 April 1968: At 07:00:01.38 EST (12:00:01.38 UTC), Apollo 6 (AS-502), the second and last unmanned Apollo mission, lifted off from Launch Complex 39A, Kennedy Space Center, Cape Canaveral, Florida. First motion was detected at Range Time 00:00:00.38. The purpose of the flight was to determine that an all-up Saturn V could attain Trans Lunar Injection. Because of engine difficulties, it did not do so, but data from the test gave mission planners confidence to go ahead with manned flights.
Apollo 6/Saturn V AS-502 lifts off from Launch Complex 39A, Kennedy Space Center, Cape Canaveral, Florida, 12:00:01.38 UTC, 4 April 1968. (National Aeronautics and Space Administration)
At T+2:05 the Saturn V experienced a severe “pogo” oscillation, but no structural damage occurred. Next, several structural panels from the lunar module adaptor section were lost due to a manufacturing defect. Finally, during the second stage burn, two of the five Rocketdyne J-2 engines shut down prematurely. Because of this, the planned circular orbit at 175 kilometers altitude was not achieved, instead, the spacecraft entered a 106.9 × 138.6 miles (172.1 × 223.1 kilometers) orbit, circling Earth in 89.8 minutes.
After two orbits, it was planned to send Apollo 6 to the Trans Lunar Injection point, but the third stage engine would not fire. The Service Module engine was used to boost the spacecraft to a peak altitude of 13,810.2 miles (22,225.4 kilometers) and a planned lunar re-entry simulation was carried out. Apollo 6 reached 22,385 miles per hour (36,025 kilometers per hour) as it reentered the atmosphere. 9 hours, 57 minutes, 20 seconds after launch, Apollo 6 splashed down in the Pacific Ocean north of Hawaii and was recovered by USS Okinawa (LPH-3).
Apollo 6/Saturn V AS-502. (National Aeronautics and Space Administration NASA S68-27366)
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).¹ 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.
Apollo 6/Saturn V AS-502 S-/S-II interstage falling away. (NASA 68-HC-193)
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. For more than 50 years, they were the most powerful machines ever built by man.
¹ The five Rocketdyne F-1 engines of the AS-502 S-IC first stage produced a combined thrust of 7,567,000 pounds (33,660 kilonewtons), 15,000 pounds (67 kilonewtons) less than predicted.
Astronaut Virgil I. Grissom with scale model of Gemini/Titan II launch vehicle. (NASA)Virgil Ivan Grissom (1944 Gold and Blue)
3 April 1926: Virgil Ivan Grissom was born at Mitchell, Indiana, the second of five children of Dennis David Grissom, an electrician, and Cecile King Grissom. “Gus” Grissom attended Mitchell High School, graduating in 1944. He was a member of the Hi-Y Club, the Camera Club, and the Signal Club.
Upon graduation from high school. Virgil I. Grissom enlisted as an aviation cadet in the Air Corps, United States Army, at Fort Benjamin Harrison, Lawrence, Indiana, 9 August 1944. He was assigned to basic flight training at Sheppard Field, Texas, but the War came to an end before he could graduate as a pilot. Then reassigned as a clerk, he requested to be discharged from the Air Corps, which he was in November 1945.
Grissom married Miss Betty Lavonne Moore at Mitchell, Indiana, 6 July 1945. They wood have two sons, Scott and Mark. (In Korea, Grissom named his F-86 Scotty after his first son.)
After the war, Grissom enrolled at Purdue University, Lafayette, Indiana, and in 1950, graduated with the degree of Bachelor of Science in Mechanical Engineering.
He then re-joined the U.S. Air Force in 1950 and was trained at Randolph Air Force Base, Texas, and Williams Air Base, Arizona, where he specialized as a fighter pilot. He was commissioned as a second lieutenant, U.S. Air Force, in March 1952.
Lieutenant Grissom was assigned to he 334th Fighter Interceptor Squadron, 4th Fighter Interceptor Wing, based at Kenpo Air Base (K-14), in the Republic of South Korea. He flew 100 combat missions in the North American Aviation F-86 Sabre. Grissom was promoted to first lieutenant, 11 March 1952. he requested to fly another 25 combat missions, but that was declined and he returned to the United States. Lieutenant Grissom was then assigned as a flight instructor at Bryan Air Force Base, Texas.
Grissom attended a one year program at the Air Force Institute of Technology at Wright-Patterson Air Force Base, Dayton, Ohio, and earned a second bachelor’s degree in aircraft engineering. He was then sent to the Air Force Test Pilot School at Edwards Air Force Base, California (Class 56D). After completion, he was assigned as a fighter test pilot back at Wright-Patterson.
One of 508 pilots who were considered by NASA for Project Mercury, Gus Grissom was in the group of 110 that were asked to attend secret meetings for further evaluation. From that group, 32 went on with the selection process and finally 18 were recommended for the program. Grissom was one of the seven selected.
Mercury-Redstone 4 (Liberty Bell 7) launch at Pad 5, Cape Canaveral Air Force Station, 12 20 36 UTC, 21 July 1961. (NASA)
Major Grissom was the second American to “ride the rocket” aboard Mercury-Redstone 4. He named his space capsule Liberty Bell 7. The spacecraft reached a maximum altitude of 102.8 nautical miles (118.3 statute miles, 190.4 kilometers) and traveled 262.5 nautical miles (302.1 statute miles, 486.2 kilometers) down range. During the 15 minute, 37 second, flight, Grissom was weightless for 5:00 minutes.
Next he orbited Earth as commander of Gemini III along with fellow astronaut John Young. He was back-up commander for Gemini VI-A, then went on to the Apollo Program.
The flight crew of Gemini III, John W. Young and Virgil I. Grissom. (NASA)
Gus Grissom was selected as the commander for Apollo I in January 1968. This was to be the first manned flight of the Apollo spacecraft. Ed White and Roger Chaffee were the other members of the flight crew.
As commander of AS-204 (Apollo I), LCOL Virgil I. Grissom, USAF was killed along with Ed White and Roger Chafee during a test on the launchpad, 27 January 1967.
The crew of Apollo 1. Left to right, Lieutenant Colonel Virgil I. Grissom, United States Air Force, Lieutenant Colonel Edward H. White II, United States Air Force, and Lieutenant Commander Roger B. Chaffee, United States Navy. (NASA)
Gus Grissom was an Air Force Command Astronaut with over 4,600 hours flight time. He was the first American astronaut to fly into space twice, and logged 5 hours, 7 minutes of space flight. For his military service, Grissom was awarded the Distinguished Flying Cross; the Air Medal with one bronze oak leaf cluster (two awards); the American Campaign medal; the World War II Victory Medal; teh Korean Service Medal; the United Nations Korea medal, and the Korean War Service Medal of the Republic of South Korea. For his NASA service, he was awarded the Congressional Space Medal of Honor (posthumous); the NASA Distinguished Service Medal (two awards); and the NASA Exceptional Service Medal.
Had he lived, it is very possible that Grissom would have commanded the first Apollo mission to land on The Moon.
The remains of Lieutenant Colonel Virgil Ivan Grissom, United States Air Force, NASA Astronaut, are buried at the Arlington National Cemetery, Arlington, Virginia.
