The United States decided in 1961 to undertake a manned lunar landing effort as the focal point of a broad new space exploration program. There was no rocket in the country at that time even approaching the needed capability, but there was a sort of "test bed" in the making, the eight engine Saturn I. It had never flown and was much too small to offer any real hope of sending a trio to the moon, except possibly through as many as a half dozen separate launchings from earth and the perfection of rendezvous and docking techniques, which had never been tried.
This situation brought about the announcement on Jan. 10, 1962, that the National Aeronautics and Space Administration would develop a new rocket, much larger than any previously attempted. It would be based on the F 1 rocket engine, the development of which had been underway since 1958, and the hydrogen fueled J 2 engine, upon which work had begun in 1960.
The Saturn V, then, is the first large vehicle in the U. S. space program to be conceived and developed for a specific purpose. The lunar landing task dictated the make up of the vehicle, but it was not developed solely for that mission. As President Kennedy pointed out when he issued his space challenge to the Congress on May 25, 1961, the overall objective is for "this nation to take a clearly leading role in space achievement which in many ways may hold the key to our future on earth." He said of the lunar landing project: "No single space project in this period will be more exciting, or more impressive to mankind, or more important for the long range exploration of space; and none will be so difficult or expensive to accomplish..."
The Saturn V program is the biggest rocket effort undertaken in this country. Its total cost, including the production of 15 vehicles will be more than $7 billion. NASA formally assigned the task of developing the Saturn V to the Marshall Space Flight Center on Jan. 25, 1962. Launch responsibility was committed to the Kennedy Space Center. (The Manned Spacecraft Center, the third center involved in manned space flight, is responsible for spacecraft development, crew training, and inflight control.
Marshall Center rocket designers conceived the Saturn V in 1961 and early 1962. They decided that a three stage vehicle would best serve the immediate needs for a lunar landing mission and would serve well as a general purpose space exploration vehicle.
One of the more important decisions made early in the program called for the fullest possible use of components and techniques proven in the Saturn I program.. As a result, the Saturn V third stage (S IVB) was patterned after the Saturn I second stage (S IV), and the Saturn V instrument unit is an outgrowth of the one used on Saturn I. In these areas, maximum use was made of designs and facilities already available to save time and costs.
Many other components were necessary, including entirely new first and second stages (S IC and S II). The F 1 and J 2 engines were already under development, although much work remained to be done. The guidance system was to be an improvement on that of the Saturn I.Saturn V, including the Apollo spacecraft, is 363 feet tall. Fully loaded, the vehicle will weigh some 6.2 million pounds.
The 303,000 pound first stage is 33 feet in diameter and 138 feet long. It is powered by five F 1 engines generating 7.5 million pounds thrust. The booster will burn 209,000 gallons of RP 1 (refined kerosene) and 334,500 gallons of liquid oxygen (LOX) in 2.5 minutes. Propellant consumption varies with cutoff times tailored for different missions.
Saturn V's second stage is powered by five J 2 engines that generate a total thrust of a million pounds. The 33 foot diameter stage weighs 99,200 pounds empty and more than a million pounds loaded. It burns some 275,000 gallons of liquid hydrogen and 84,750 gallons of liquid oxygen during a typical flight of about 6 minutes.
Third stage of the vehicle is 21 feet and 8 inches in diameter and 58 feet and 7 inches long. An interstage adapter connects the larger diameter second stage to the smaller upper stage. Empty weight of the stage is 33,600 pounds and the fueled weight is about 265,600 pounds. A single J 2 engine developing up to 230,000 pounds of thrust powers the stage. Typical burn time is 2.75 minutes for the first burn and 5.2'minutes to a translunar injection.
The vehicle instrument unit sits atop the third stage. The unit, which weighs an average 4,500 pounds, contains the electronic gear that controls engine ignition and cutoff, steering, and all other commands necessary for the Saturn V mission. Diameter of the instrument unit is 21 feet and 8 inches, and height is 3 feet.
Directly above the instrument unit in the Apollo configuration is the Apollo spacecraft. It consists of the lunar module, the service module, the command module, and the launch escape system. Total height of the package is about 80 feet.
TYPICAL LUNAR LANDING MISSION
The jumping off place for a trip to the moon is NASA's Launch Complex 39 at the Kennedy Space Center. After the propellants are loaded, the three astronauts will enter the spacecraft and check out their equipment.
While the astronauts tick off the last minutes of the countdown in the command module, a large crew in the launch control center handles the complicated launch operations. For the last two minutes, the countdown is fully automatic. At the end of countdown, the five F 1 engines in the first stage ignite, producing 7.5 million pounds of thrust. The hold-down arms release the vehicle, and three astronauts begin their ride to the moon.
Turbopumps, working together with the strength of 30 diesel locomotives, force almost 15 tons of fuel per second into the five engines. Steadily increasing acceleration pushes the astronauts back into their couches as the rocket generates 4 1/2 times the force of earth gravity.
After 2.5 minutes, the first stage has burned its 4,578,000 pounds of propellants and is discarded at about 38 miles altitude. The second stage's five J 2 engines are ignited. Speed at this moment is about 6,000 miles per hour.
The second stage's five J 2 engines burn for about 6 minutes, pushing the Apollo spacecraft to an altitude of nearly 115 miles and a velocity of about 15,300 miles per hour. After burnout the second stage drops away and retrorockets slow it for its fall into the Atlantic Ocean west of Africa.
The single J 2 engine in the third stage now ignites and burns for 2.75 minutes. This brief burn boosts the spacecraft to orbital velocity, about 17,500 miles an hour. The spacecraft, with the third stage still attached, goes into orbit about 12 minutes after liftoff. Propellants in the third stage are not depleted when the engine is shut down. This stage stays with the spacecraft in earth orbit, for its engine will be needed again.
Throughout the launch phase of the mission,. telemetry systems are transmitting continously, tracking systems are locked on, and voice communications are used to keep in touch with the astronauts. All stage separations and engine thrust terminations are reported to the Mission Control Center at Houston.
The astronauts are now in a weightless condition as they circle the earth in a "parking orbit" until the timing is right for the next step to the moon.
The first attempt at a lunar landing is planned as an "open ended" mission with detailed plans at every stage for mission termination if necessary, A comprehensive set of alternate flight plans will be laid out and fully rehearsed for use if such a decision should prove necessary. For example, a decision might be made in the earth parking orbit not to continue with the mission. At every stage of the mission, right up to touchdown on the moon, this termination decision can be made and an earth flight plan initiated.
During the one to three times the spacecraft circles the earth, the astronauts make a complete check of the third stage and the spacecraft. When the precise moment comes for injection into a translunar trajectory, the third stage J 2 engine is reignited. Burning slightly over 5 minutes, it accelerates the spacecraft from its earth orbital speed of 17,500 miles an hour to about 24,500 miles an hour in a trajectory which would carry the astronauts around the moon. Without further thrust, the spacecraft would return to earth for re entry.
If everything is operating on schedule, the astronauts will turn their spacecraft around and dock with the lunar landing module. After the docking maneuver has been completed, the lunar module will be pulled out of the forward end of the third stage, which will be abandoned. This completes the Saturn V's work on the lunar mission.
HOW SATURN V DESIGN WAS REACHED
While a major effort of this country's space commitment was to explore the moon, the broader target was to build a capability people, launch vehicles, propulsion, spacecraft, production, testing, and launching sites to explore a vast new frontier and develop a long range space faring capability that would establish continuing national preeminence.
The questions facing national space planners in 1961 and 1962 were complex. Although the use of a Saturn I for a manned lunar landing was theoretically possible, it would have been extremely difficult. About six Saturn I launches would have been required, their payloads being assembled in earth orbit to form a moon ship. No space rendezvous and docking had taken place at that time.
During the first half of 1962, two paramount decisions were announced: to develop a new general purpose launch vehicle in the middle range of several under consideration, and to conduct the manned lunar landing by use of a lunar orbit rendezvous (LOR) technique.
The Saturn V, as the chosen vehicle was named, was given the go ahead in January, 1962.
It was to be composed of three propulsive stages and a small instrument unit to contain guidance and control. It could perform earth orbital missions through the use of the first two stages, while all three would be required for lunar and planetary expeditions. The ground stage was to be powered by five F 1 engines, each developing 1.5 million pounds of thrust, and the stage would have five times the power of the Saturn I booster then under development. The upper stages would use the J 2 hydrogen/ oxygen engine, five in the second stage and one in the third. Each would develop up to 225,000 pounds of thrust. Such a rocket would be capable of placing 120 tons into earth orbit or dispatching 45 tons to the moon. (The numbers have been uprated now to about 140 and 50.)
During its assembly, checkout, and launch, the Saturn V would use a new mobile launch concept. It would be assembled in a huge Vehicle Assembly Building, and then transported in an upright position to a launch pad several miles away. Propulsion development decisions preceded those for the vehicles.
The need for a building block rocket engine in the million pound thrust class was apparent even as ARPA was ordering work to begin on the first stage cluster of engines for the Saturn I. In January, 1959, NASA contracted with North American Aviation's Rocketdyne Division for development of the F 1.
Late in 1959, the Silverstein Committee recommended the development of a new high thrust hydrogen engine to meet upper stage requirements. In June, 1960, Rocketdyne was selected to develop the J 2 engine after NASA evaluation of competitive proposals.
Three proposed Apollo modes which were considered in detail were: the direct flight mode, using a very large launch vehicle called "Nova"; the earth orbital rendezvous (EOR) mode, requiring separate Saturn launches of a tanker and a manned spacecraft; and the lunar orbital rendezvous mode, requiring a single launch of the manned spacecraft and the lunar module.
Selected was the LOR mode, in which the injected spacecraft weight would be reduced by eliminating the requirement for the propulsion needed to soft land the entire spacecraft on the lunar surface.
A small lunar excursion module, or LEM, now referred to as the lunar module, would be detached after deboost into lunar orbit. The lunar module would carry two of the three man Apollo crew to a soft landing on the moon and would subsequently be launched from the moon to rendezvous with the third crew member in the "mother ship." The entire crew would then return to earth aboard the command module. NASA concluded that LOR offered the greatest assurance of successful accomplishment of the Apollo objectives at the earliest practical date.
Members of NASA's Manned Space Flight Management Council recommended LOR unanimously in 1962 because it:
1. Provided a higher probability of mission success with essentially equal mission safety;
2. Promised mission success some months earlier than did other modes;
3. Would cost 10 to 15 per cent less than the other modes
4. Required the least amount of technical development beyond existing commitments while advancing significantly the national technology.
As a part of the Saturn V decision, it was determined that elements of the existing Saturn I vehicle and the planned Saturn V would be combined to form a new mid range vehicle, the Saturn IB. The Saturn IB would have a payload capability 50 per cent greater than the Saturn I and would make possible the testing of the Apollo spacecraft in earth orbit about one year earlier than would be possible with the Saturn V.
By the end of 1962, all elements of the new program were under way, with the
Marshall Space Flight Center directing the work for NASA. The Boeing Company; Space Division of North American Aviation, Inc.; and Douglas Aircraft Company were acting as prime contractors for the Saturn V first, second, and third stages, respectively. Engines were being developed by the Rocketdyne Division of North American. MSFC designed the instrument unit and awarded a production contract to International Business Machines Corp. (Chrysler Corp. had been selected to produce the first stage of the Saturn IB.)
A large network of production, assembly, testing, and launch facilities was also being prepared by the end of 1962. Aside from the provision of various facilities at contractor plants and the augmentation of the Marshall Space Flight Center resources, three new government operations were established: the launch complex in Florida operated by the NASA Kennedy Space Center and two new elements of MSFC Michoud Assembly Facility in New Orleans, La., for the production of boosters, and Mississippi Test Facility, Bay St. Louis, Miss., for captive firing of stages.
Four years after its establishment, the Saturn V program was progressing on schedule, pointing toward the launch of the first vehicle in 1967 and fulfillment of the manned lunar landing before the end of the decade.
Following are highlights of the Saturn V development program:
Aug. 24 NASA announced the selection of the 88,000 acre site at Merritt Island, Fla., adjacent to Kennedy Space Center, then Cape Canaveral, for the assembly, checkout, and launch of the Saturn V.
Sept. 7 NASA selected the government owned Michoud plant, New Orleans, as production site for Saturn boosters. It became a part of the Marshall Space Flight Center.
Sept. 11 NASA selected North American Aviation, Inc., to develop and build the second stage for an advanced Saturn launch vehicle (as yet undefined) for manned and unmanned missions. One month later the Marshall Center directed NAA to design the second stage using five J 2 engines. A preliminary contract was signed in February, 1962.
Oct. 6 NASA selected the Picayune Bay St. Louis, Miss., area for its Mississippi Test Facility an arm of the Marshall Center for use in static testing of rocket stages and engines.
Dec. 15 The Boeing Company was selected as prime contractor for the first stage of the advanced Saturn vehicle not yet fully defined. A preliminary contract was signed in February, 1962, with the work to be conducted at the Michoud Assembly Facility.
Dec. 21 NASA selected the Douglas Aircraft Company to negotiate a contract to develop the third stage (S IVB) of the advanced Saturn, based on the Saturn I's S IV stage. A supplemental contract for production of 11 third stages was signed in August, 1962.
Jan. 10 Announcement was made that the advanced Saturn vehicle would have a first stage powered by five F 1 engines, a second stage powered by five J 2 engines, and for lunar missions a third stage with one J 2 engine..
Jan. 25 NASA formally assigned development of the three stage Saturn C 5 (Saturn V became the name in February, 1963) to MSFC
April 11 NASA Headquarters gave the Apollo/ Saturn I/Saturn V highest national priority.
May 26 Rocketdyne Division of NAA conducted the first full thrust, long duration F 1 engine test.
July 11 It was announced that the Saturn IB would be developed and that the lunar orbit rendezvous method of accomplishing a lunar landing had been selected.
December The U. S. Army Corps of Engineers awarded a contract for the design of the Vehicle Assembly Building (VAB) at the Florida launch complex.
Feb. 27The first contract for the Mississippi Test Facility (MTF) Saturn V test facilities was awarded.
The J 2 engine was successfully fired for the first time in a simulated space altitude of 60,000 feet.
Oct. 31 The Marshall Center received the first production model of the F 1 engine.
Nov. 12 NASA contracted for the first Saturn V launch pad at the Kennedy Space Center.
March IBM was awarded an instrument unit contract for the digital computer and data adapter by the Marshall Center. IBM became the prime IU contractor in May.
Oct. 9 The Edwards AFB test facility was accepted as the F 1 test complex, amounting 1966 to a cost of $34 million. Feb. 17
Dec. 1 The first mainstage shakedown firing of & 25 the third stage battleship was accomplished, lasting 10 seconds.
Dec. 23 First full duration firing of the third stage battleship occurred.
April 16 All five engines of the S IC T, first stage test vehicle, were fired at the Marshall Center for 6.5 seconds.
April 24 The first cluster ignition test of the second stage battleship was successfully completed.
Aug. 5 The first full duration firing of the first stage was conducted successfully at the SeptemMarshall Center.
Aug. 8 Third stage flight readiness test of 452 Dec. seconds, fully automated, was accomplished at Sacramento.
Aug. 13 The IU was qualified structurally and manrated for Saturn V use by withstanding a 140 per cent load limit.
Aug. 17 The third stage battleship was tested in Saturn V configuration for full duration (start stop restart).
Dec. 16 The S IC T static firings were completed at the Marshall Center with a total of 15 firings three of full duration.
Feb. 17 & 25 The S IC 1 underwent static firing at the Marshall Center and required no more static firings.
Mar. 30 The S IU 50OF was mated to the three stages of the Saturn V facilities vehicle at the Kennedy Space Center's VAB.
May 20 First full duration firing of the second stage flight stage was conducted at MTF.
May 25 The Apollo/Saturn V facilities vehicle, AS500 F, was transported to Pad A at Launch Complex 39, KSC, on the crawler.
May 26 Full duration acceptance firing of the SIVB 501, the first flight version of the third stage for Saturn V, was accomplished. The F 1 and J 2 engines were qualified for manned flights. Initial static firing of the first flight version of the second stage occurred at MTF.
Nov. 15 The first flight version of the first stage was static fired at MSFC. First Stage Separation During an Apollo/Saturn V ShotB 140 66 1
March 3 S IC static test stand at MTF declared operational following firing of S IC T.
March 16 Start and restart tests of J 2 engine in vacuum chamber at Arnold Engineering and Development Center, Tullahoma, Tenn. completed successfully.
April 12 Ten week phase of dynamic testing of complete Saturn V launch vehicle and Apollo May 1 spacecraft completed at MSFC.
Aug. 26 First Saturn V flight vehicle, AS 501, rolled out of VAB at KSC and transported to LC 39.
Nov. 9 Launch of first Saturn V, the AS 501, from LC 39 at KSC. 1968
April 4 Launch of second Saturn V, the AS 502, from LC 39 at KSC.
May 1 NASA announced decision to man the third Saturn V, the AS 503, after studying results of AS 501 and AS 502 flights.
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