19 November 1996, 19:55:47 UTC, T minus Zero: Space Shuttle Columbia (OV-102) lifted off from Launch Complex 39B at the Kennedy Space Center, Cape Canaveral, Florida, on mission STS-80. The veteran flight crew was led by mission commander, Captain Kenneth D. Cockrell, U.S. Navy, on his third space flight, with shuttle pilot Captain Kent V. Rominger, U.S. Navy, on his second. Mission Specialist Story Musgrave, M.D., was on his sixth flight; Thomas D. Jones, Ph.D., (formerly Captain, USAF, a B-52 aircraft commander) was on his third; Tamara E. Jernigan, Ph.D. was on her fourth.
On STS-80, Story Musgrave became the only person to have flown on all five space shuttles. At 61, he was the oldest person to have flown into space at the time.
STS-80 was the longest mission of any space shuttle flight, with a duration of 17 days, 15 hours, 53 minutes, 18 seconds. Columbia landed at the Shuttle Landing Facility (SLF) at Kennedy Space Center, 11:49:05 UTC, 7 December 1996.
16 November 1973: Skylab 4 lifted off from Launch Complex 39B, Kennedy Space Center, at 14:01:23 UTC. Aboard the Apollo Command and Service Module were NASA astronauts Lieutenant Colonel Gerald Paul Carr, U.S. Marine Corps, Mission Commander; Lieutenant Colonel William Reid Pogue, U.S. Air Force; and Edward George Gibson, Ph.D. This would be the only space mission for each of them. They would spend 84 days working aboard Skylab.
The launch vehicle was a Saturn IB, SA-208. This rocket had previously stood by as a rescue vehicle during the Skylab 3 mission. The Saturn IB consisted of an S-IB first stage and an S-IVB second stage.
The S-IB was built by Chrysler Corporation Space Division at the Michoud Assembly Facility near New Orleans, Louisiana. It was powered by eight Rocketdyne H-1 engines, burning RP-1 and liquid oxygen. Eight Redstone rocket fuel tanks, with 4 containing the RP-1 fuel, and 4 filled with liquid oxygen, surrounded a Jupiter rocket fuel tank containing liquid oxygen. Total thrust of the S-IB stage was 1,666,460 pounds (7,417.783 kilonewtons) and it carried sufficient propellant for a maximum 4 minutes, 22.57 seconds of burn. First stage separation was planned for n altitude of 193,605 feet, with the vehicle accelerating through 7,591.20 feet per second (2,313.80 meters per second).
The McDonnell Douglas Astronautics Co. S-IVB stage was built at Huntington Beach, California. It was powered by one Rocketdyne J-2 engine, fueled by liquid hydrogen and liquid oxygen. The J-2 produced 229,714 pounds of thrust (1,021.819 kilonewtons), at high thrust, and 198,047 pounds (880.957 kilonewtons) at low thrust). The second stage carried enough fuel for 7 minutes, 49.50 seconds burn at high thrust. Orbital insertion would be occur 9 minutes, 51.9 seconds after launch, at an altitude of 98.5 miles (158.5 kilometers) with a velocity of 25,705.77 feet per second (7,835.12 meters per second).
The Skylab-configuration Saturn IB rocket was 223 feet, 5.9 inches (68.119 meters) tall. It had a maximum diameter of 22.8 feet (6.949 meters), and the span across the first stage guide fins was 40.7 feet (12.405 meters). Its empty weight was 159,000 pounds (72,122 kilograms) and at liftoff, it weighed 1,296,000 pounds (587,856 kilograms). It was capable of launching a 46,000 pound (20,865 kilogram) payload to Earth orbit.
14 November 1969: At 16:22:00.68 UTC (11:22:00 a.m., Eastern Standard Time), the Apollo 12 Saturn V (AS-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.
Two lightning strikes 36.5 seconds after liftoff caused the spacecraft’s automatic systems to shut down three fuel cells, leaving Apollo 12 operating on battery power. A third electrical disturbance 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.
The lightning discharge was caused by the Apollo 12/Saturn V vehicle accelerating through rain at approximately 6,300 feet (1,950 meters). There were no thunderstorms in the area. Post-flight analysis indicates that it is probable that the lightning discharge started at the top of the Apollo 12/Saturn V vehicle. Energy of the discharge was estimated at 10⁴–10⁸ joules.
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.
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. The first and second stages were 33 feet, .2 inches (10.089 meters) in diameter. Fully loaded and fueled the rocket weighed approximately 6,200,000 pounds (2,948,350 kilograms).¹ 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 (33,851 kilonewtons).² These engines were ignited 6.50 seconds prior to Range Zero and the outer four burned for 161.74 seconds. The center engine was shut down after 135.24 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 (5,165.5 kilonewtons).³
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.
¹ The AS-507 total vehicle mass at First Stage Ignition (T – 6.50 seconds) was 6,137,868 pounds (2,784,090 kilograms).
² Post-flight analysis gave the total thrust of AS-507’s S-IC stage as 7,594,000 pounds of thrust (33,780 kilonewtons).
³ Post-flight analysis gave the total thrust of AS-507’s S-II stage as 1,161,534 pounds of thrust (5,166.8 kilonewtons).
⁴ Post-flight analysis gave the total thrust of AS-507’s S-IVB stage as 206,956 pounds of thrust (920.6 kilonewtons) during the first burn; 207,688 pounds (923.8 kilonewtons) during the second burn.
27 October 1961: At 15:06:04 UTC, (10:06 a.m., EST), 3.97 seconds after ignition, the first Saturn C-1 heavy launch vehicle (Saturn I, SA-1) lifted off from Launch Complex 34 at Cape Canaveral, Florida. This was a test of the first stage, only. The rocket’s upper stages were dummies.
At about 109 seconds after liftoff, four inner engines of the first stage shut down, followed 6 seconds later by the outer four. The rocket continued on a ballistic trajectory.
The Saturn C-1 was bigger than any rocket built up to that time. Early versions of the three-stage rocket were 162 feet, 8.90 inches (49.6037meters) tall, with a maximum diameter of 21 feet, 5.0 inches (6.528 meters). The all-up weight was 1,124,000 pounds (509,838 kilograms).
The first stage of SA-1 was built by the Marshall Space Flight Center (MSFC) at Huntsville, Alabama. The S-I stage was built up with a Jupiter rocket fuel tank in the center for liquid oxygen, surrounded by eight Redstone rocket tanks. Four were filled with RP-1 propellant, alternating with four filled with LOx. The first stage was powered by eight Rocketdyne Division H-1 engines rated at 165,000 pounds of thrust (733.96 kilonewtons), each. Total thrust for the first stage was 1,320,000 pounds (5,871.65 kilonewtons). The outer four engines were gimbaled to steer the rocket. (The S-I Block I stage had no fins.)
The first stage had been test fired 20 times before being transported to Cape Canaveral by barge.
For the first flight, SA-1, the S-!V second stage and S-V third stage were dummies. The S-IV was filled with 90,000 pounds (40,823 kilograms) of water for ballast. The S-V third stage, carried 100,000 pounds (45,359 kilograms) of water. Mounted above the third stage was a Jupiter nose cone.
The Saturn C-1 weighed 925,000 pounds (419,573 kilograms). It contained 41,000 gallons (155,200 liters) of RP-1, a refined kerosene fuel, with 66,000 gallons (249,837 liters) of liquid oxygen oxidizer— 600,000 pounds (272,155 kilograms) of propellants.
SA-1 reached a maximum speed of 3,607 miles per hour (5,805 kilometers per hour), and a peak altitude of 84.813 miles (136.493 kilometers). It impacted in the Atlantic Ocean 214.727 miles (345.570 kilometers) down range. The duration of the flight was 15 minutes, 0 seconds. The flight was considered to be nearly flawless.
3 October 1962: At 08:15:12 a.m., Eastern Daylight Time, Commander Walter M. Schirra, Jr., United States Navy, lifted off from Cape Canaveral, Florida, aboard Mercury-Atlas 8 (MA-8). This was the fifth U.S. manned space flight and the third orbital flight.
The spacecraft, which Wally Schirra had named Sigma 7, entered a low earth orbit with the altitude varying from 84 nautical miles (156 kilometers) to 154 nautical miles (285 kilometers). Each orbit took 88 minutes, 54.6 seconds.
Schirra experimented with the manual flight control systems, took photographs and performed spatial-orientation exercises. There were some difficulties with the cooling of his pressure suit.
Sigma 7 completed 6 orbits and at T+8:52, fired the retro rockets to de-orbit. Reentry was successful and Sigma 7 landed within 0.5 miles (0.8 kilometers) of the primary recovery ship, the aircraft carrier USS Kearsarge (CVS-33).
The Mercury spacecraft, named Sigma 7, was built by McDonnell Aircraft Corporation, St. Louis, Missouri. It was the 16th Mercury capsule built. Designed to carry one pilot, it could be controlled in pitch, roll and yaw by thrusters. It was 9 feet, 7.72 inches (2.939 meters) long, and, bell-shaped, had a maximum diameter of 6 feet, 2.5 inches (1.885 meters). The spacecraft weighed 2,700 pounds (1,224.7 kilograms) at launch.
The rocket, a “1-½ stage”, liquid-fueled Atlas LV-3B, number 113-D, was built by Convair at San Diego, California. It was developed from a U.S. Air Force Atlas D intercontinental ballistic missile, modified for use as a “man-rated” orbital launch vehicle. The LV-3B was 94.3 feet (28.7 meters) tall with a maximum diameter of 10.0 feet (3.05 meters). When ready for launch it weighed 260,000 pounds (120,000 kilograms) and could place a 1,360 kilogram payload into Low Earth orbit. The Atlas’ three engines were built by the Rocketdyne Division of North American Aviation, Canoga Park, California. The XLR89 booster had two 150,000 pound thrust chambers, and the LR105 sustainer engine produced 57,000 pounds of thrust. The rocket was fueled by a highly-refined kerosene, RP-1, with liquid oxygen as the oxidizer.
Schirra was the first astronaut to wear an Omega Speedmaster chronograph during spaceflight. (Omega Reference No. CK2998). The Speedmaster would become flight-qualified by NASA, and the Speedmaster Professional is known as the “moon watch.”
Sigma 7 is on display at the U.S. Astronaut Hall of Fame, Titusville, Florida, near the Kennedy Space Center.
Wally Schirra commanded Gemini 6A during the orbital rendezvous mission with Gemini 7. Later, he commanded Apollo 7, an 11-day orbital mission.
Captain Walter M. Schirra, Jr., USN, died 3 May 2007 at the age of 84 years.