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Saturn V

Saturn V Geneology

Saturn V Geneology
Credit: © Mark Wade

American orbital launch vehicle. America's booster for the Apollo manned lunar landing. The design was frozen before a landing mode was selected; the Saturn V could be used for either Earth-Orbit-Rendezvous or Lunar-Orbit-Rendezvous methods. The vehicle ended up with the same payload capability as the 'too large' Nova. The basic diameter was dictated by the ceiling height at the Michoud factory selected for first stage manufacture. Despite the study of innumerable variants, production was ended after only 12 were built and America spent the next fifty years in a pointless slow-motion withdrawal from manned space exploration.

AKA: SaturnV. Status: Retired 1973. First Launch: 1967-11-09. Last Launch: 1973-05-14. Number: 13 . Payload: 118,000 kg (260,000 lb). Thrust: 33,737.90 kN (7,584,582 lbf). Gross mass: 3,038,500 kg (6,698,700 lb). Height: 102.00 m (334.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

The Saturn launch vehicle was the penultimate expression of the Peenemuende Rocket Team's designs for manned exploration of the moon and Mars. The designs were continuously developed and improved, starting from the World War II A11 and A12 satellite and manned shuttle launcher, through the designs made public in the Collier's Magazine series of the early 1950's, until the shock of the first Sputnik launch brought sudden real interest from the U.S. government. On December 30 1957 Von Braun produced a 'Proposal for a National Integrated Missile and Space Vehicle Development Plan'. This had the first mention of a 1,500,000 lbf booster (Juno V, later Saturn I). By July of the following year Huntsville had in hand the contract from ARPA to proceed with design of the Juno V.

Following transfer of the Peenemuende Rocket Team from the US Army to NASA, a year after the first plan was mooted, Von Braun briefed NASA on plans for booster development at Huntsville with objective of manned lunar landing. It was initially proposed that 15 Juno V (Saturn I) boosters assemble a 200,000 kg payload in earth orbit for direct landing on moon. NASA produced two months later, on February 15, 1959, its plan for development in the next decade of Vega (later cancelled after NASA discovered the USAF was secretly developing the similar Hustler (Agena) upper stage), Centaur, Saturn, and Nova launch vehicles (Juno V renamed Saturn I at this point). Throughout the initial planning, Presidential decision, and landing mode debate for the Apollo lunar landing goal, a variety of Saturn and Nova configurations were considered. Of these, only the C-1 and C-5 were taken through to further development.

Configuration Stage 1 Stage 2 Stage 3 Stage 4 LEO Payload - kg Escape Payload - kg
Saturn A-1 8 x H-1 2 x LR89 2 x LR115
Saturn A-2 8 x H-1 4 x S-3 2 x LR115
Saturn B-1 8 x H-1 4 x LR89 5 x LR115 2 x LR115
Saturn C-1 8 x H-1 6 x LR115 2 x LR115 9,0002,200
Saturn C-2 8 x H-1 1 x J-2 6 x LR115 2 x LR11520,0006,800
Saturn C-3 2 x F-1 4 x J-2 6 x LR115 2 x LR115
Saturn C-4 4 x F-1 4 x J-2 1 x J-2
Saturn C-5 5 x F-1 5 x J-2 1 x J-2 127,00045,000
Nova Basic 6 x F-1 1 x F-1 4 x J-2 68,00016,000
Nova A 4 x F-1 4 x J-2 5 x LR115 1 x 2700 kgf68,00027,000
Nova B 6 x F-1 8 x J-2 7 x LR115 1 x LR115112,00047,000
Nova C 6 x F-1 8 x J-2 1 x Nerva 68,00038,000
Nova D 6 x F-1 8 x J-2 1 x Nerva 112,00065,000
Nova N-F1 8 x F-1 4 x F-1 1 x J-2 70,000
Nova N-M1 8 x F-1 4 x M-1 1 x J-2 180,00090,000

After the Saturn V drawings had been issued, Marshall engineers immediately turned to considering further developments of the basic launch vehicle. These would be required for Apollo Applications, Manned Orbiting Research Laboratory, Mars fly-by, and Mars landing missions in the 1970's and 1980's.

Contracts were let for a variety of trade studies. There were limits to how far the core stack could be stretched, dictated by the 410 foot maximum overhead crane height in the Vertical Assembly Building at Kennedy Space Center (this did not prevent 470 foot versions being proposed, including the nuclear NERVA third stage, for manned missions to Mars - they'd just have to raise the roof, darn it). Given these limits, a variety of strap-on solid motors were considered.

The most feasible, lowest development cost improvement would have used upgraded F-1 motors, an S- IC first stage stretch, modest upgrades to the J-2 upper stage motors, and proven 120 inch solid rocket motor strap-ons. If a follow-on Saturn V production contract had ever been issued, it probably would have been for this configuration. More advanced versions would have used Flox oxidizer (liquid fluorine mixed with the liquid oxygen oxidizer - nasty to handle, but increased performance with minimal changes to the existing motors and pumps), new technology engines (plug nozzles or high-pressure combustion engines - the ancestors of the Shuttle SSME's). Instead America abandoned its heavy lift capability and further manned exploration of space. The two unused flightworthy Saturn V's from the initial production run of 15 became tourist displays at Cape Canaveral and Huntsville. A third Saturn V, exhibited in Houston, is made up of static test article stages.

Saturn II First Stage Derivatives

There was a large payload gap between the Saturn IB's 19,000 kg low-earth orbit capacity and the two-stage Saturn V's 100,000 kg capability. Marshall considered the best way to fill the gap was to use the Saturn V's second stage, the S-II, as the first stage of an intermediate launch vehicle.

Using the S-II had several advantages. It could be mounted atop a 'milk stool' and use the existing Saturn V launch gantry arms and plumbing for fueling and preparations (this approach was actually used later for Saturn IB launches for Skylab and ASTP). Discontinuing use of the Saturn IB would eliminate one rocket stage production line together with associated configuration and quality control headaches.

A dazzling array of combinations of S-II stages, S-IVB stages, and a variety of solid rocket motor strapons were considered. In most cases the S-II would have to be fitted with 'sea-level' versions of its J-2 engines, which were designed only for operation in near-vacuum conditions. This resulted in a decrease in engine performance. Since the S-II stage did not have enough thrust to get off the ground by itself, various combinations of solid rocket motor augmentation and propellant off-loads had to be used. The resulting configurations would have provided a payload range of between 13,000 kg and 66,000 kg to low earth orbit, thereby filling the payload gap and replacing the S-IB.

LEO Payload: 118,000 kg (260,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 47,000 kg (103,000 lb) to a translunar trajectory. Development Cost $: 7,439.600 million. Launch Price $: 431.000 million in 1967 dollars in 1966 dollars.

Stage Data - Saturn V


More at: Saturn V.

Subtopics

Jarvis launch vehicle American orbital launch vehicle. Launch vehicle planned for Pacific launch based on Saturn V engines, tooling. Masses, payload estimated.

Saturn C-3 The launch vehicle concept considered for a time as the leading contender for the Earth Orbit Rendezvous approach to an American lunar landing.

Saturn C-3B American orbital launch vehicle. Final configuration of the Saturn C-3 at the time of selection of the Saturn C-5 configuration for the Apollo program in December 1961.

Saturn C-3BN American nuclear orbital launch vehicle. Version of Saturn C-3 considered with small nuclear thermal stage in place of S-IVB oxygen/hydrogen stage.

Saturn C-4 American orbital launch vehicle. The launch vehicle actually planned for the Lunar Orbit Rendezvous approach to lunar landing. The Saturn C-5 was selected instead to have reserve capacity.

Saturn C-4B American orbital launch vehicle. Final configuration of the Saturn C-4 at the time of selection of the Saturn C-5 configuration for the Apollo program in December 1961. Only Saturn configuration with common bulkhead propellant tanks in first stage, resulting in shorter vehicle than less powerful Saturn C-3.

Saturn C-5 American orbital launch vehicle. Final configuration of Saturn C-5 at the time of selection of this configuration for the Apollo program in December 1961. The actual Saturn V would be derived from this, but with an increased-diameter third stage (6.61 m vs 5.59 m in C-5) and increased propellant load in S-II second stage.

Saturn C-5N American nuclear orbital launch vehicle. Version of Saturn C-5 considered with small nuclear thermal stage in place of S-IVB oxygen/hydrogen stage.

Saturn INT-17 North American study, 1966. Saturn variant with a modified S-II first stage with seven high-performance HG-3 engines; S-IVB second stage. Poor performance and cost-effectiveness and not studied further.

Saturn INT-18 North American study, 1966. Saturn variant with Titan UA1205 or 1207 motors as boosters, Saturn II stage as core, and Saturn IVB upper stage. Various combinations of numbers of strap-ons, propellant loading of the two core stages, and sea-level versus altitude ignition were studied.

Saturn INT-19 North American study, 1966. Saturn variant with 4 to 12 Minuteman motors as boosters, Saturn II stage as core, and Saturn IVB upper stage. Saturn II stage would be fitted with lower expansion ratio engines and would ignite at sea level. Various combinations of numbers of strap-ons, propellant loading of the two core stages were studied.

Saturn INT-20 American orbital launch vehicle. Saturn variant consisting of S-IC first stage and S-IVB second stage. Consideration was given to deleting one or more of the F-1 engines in the first stage.

Saturn INT-21 American orbital launch vehicle. Saturn variant consisting of S-IC first stage and S-II second stage. This essentially flew once to launch Skylab in 1972, although the IU was located atop the Skylab space station (converted S-IVB stage) rather than atop the S-II as in the INT-21 design.

Saturn LCB-Storable-140 American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb payload to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, HY-140 Steel Hull.

Saturn MLV-V-1 American orbital launch vehicle. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 41 inches with 1.0 million pounds propellant and 5 J-2 engines; S-IVB strengthened but with standard 230,000 lbs propellant, 1 J-2 engine.

Saturn MLV-V-1/J-2T/200K American orbital launch vehicle. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Variant of MLV-V-1 with toroidal J-2T-200K engines replacing standard J-2 engines in upper stages.

Saturn MLV-V-1/J-2T/250K American orbital launch vehicle. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Variant of MLV-V-1 with toroidal J-2T-250K engines replacing standard J-2 engines in upper stages.

Saturn MLV-V-1A American orbital launch vehicle. MSFC study, 1965. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 6 F-1 engines; S-II stretched 156 inches with 1.2 million pounds propellant and 7 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine.

Saturn MLV-V-2 American orbital launch vehicle. MSFC study, 1965. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 41 inches with 1.0 million pounds propellant and 5 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine.

Saturn MLV-V-3 American orbital launch vehicle. MSFC study, 1965. Ultimate core for improved Saturn V configurations studied under contract NAS8-11359. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 156 inches with 1.2 million pounds propellant and 5 HG-3 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine.

Saturn MLV-V-4(S) American orbital launch vehicle. MSFC study, 1965. Saturn V core, strengthened but not stretched, with 4 Titan UA1205 strap-on solid rocket boosters.

Saturn MLV-V-4(S)-A American orbital launch vehicle. MSFC study, 1965. 4 Titan UA1205 solid rocket boosters; Saturn IC stretched 337 inches with 6.0 million pounds propellant and 5 F-1 engines; S-II with 970,000 pounds propellant and 5 J-2 engines; S-IVB strengthened but with standard 230,000 lbs propellant, 1 J-2 engine.

Saturn MLV-V-4(S)-B American orbital launch vehicle. Boeing study, 1967. Configuration of improved Saturn 5 with Titan UA1207 120 inch solid rocket boosters. Saturn IC stretched 336 inches with 6.0 million pounds propellant and 5 F-1 engines; Saturn II and Saturn IVB stages strengthened but not stretched. Empty mass of stages increased by 13.9% (S-IC), 8.6% (S-II) and 11.8% (S-IVB). Studied again by Boeing in 1967 as Saturn V-4(S)B.

Saturn S-IC-TLB American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb payload to LEO): S-IC Technology Liquid Booster: 260 inch liquid booster with 2 x F-1 engines, recoverable/reusable

Saturn V 2 American orbital launch vehicle. Two stage version of Saturn V, consisting of 1 x Saturn S-IC + 1 x Saturn S-II, used to launch Skylab.

Saturn V/4-260 American orbital launch vehicle. Boeing study, 1967-1968. Use of full length 260 inch solid rocket boosters with stretched Saturn IC stages presented problems, since the top of the motors came about half way up the liquid oxygen tank of the stage, making transmission of loads from the motors to the core vehicle complex and adding a great deal of weight to the S-IC. Boeing's solution was to retain the standard length Saturn IC, with the 260 inch motors ending half way up the S-IC/S-II interstage, but to provide additional propellant for the S-IC by putting propellant tanks above the 260 inch boosters. These would be drained first and jettisoned with the boosters. This added to the plumbing complexity but solved the loads problem.

Saturn V-23(L) American orbital launch vehicle. Boeing study, 1967. 4 260 inch liquid propellant boosters (each with 2 F-1's!).; Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1 engines; S-II strengthened but with standard 930,000 pounds propellant and 5 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine.

Saturn V-24(L) American orbital launch vehicle. Boeing study, 1967. 4 260 inch liquid propellant boosters (each with 2 F-1A).; Saturn IC stretched 336 inches with 6.0 million pounds propellant and 5 F-1A engines; S-II stretched 156 inches with 1.2 million pounds propellant and 5 HG-3 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine. Not studied in detail since vehicle height of 600 feet with payload exceeded study limit of 410 feet.

Saturn V-25(S)B American orbital launch vehicle. Boeing study, 1967. 4 156 inch solid propellant boosters; Saturn IC stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; S-II standard length with 5 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine.

Saturn V-25(S)U American orbital launch vehicle. Boeing study, 1968. 4 156 inch solid propellant boosters; Saturn IC stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; S-II standard length with 5 J-2 engines. This vehicle would place Nerva nuclear third stage into low earth orbit, where five such stages would be assembled together with the spacecraft for a manned Mars expedition.

Saturn V-3B American orbital launch vehicle. Boeing study, 1967. Variation on MSFC 1965 study Saturn MLV-V-3 but with toroidal engines. Saturn IC stretched 240 inches with 5.6 million pounds propellant (but only 4.99 million pounds usable without solid rocket boosters) and 5 F-1A engines; S-II stretched 186 inches with 1.29 million lbs propellant and 5 J-2T-400 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2T-400 engine.

Saturn V-4X(U) American orbital launch vehicle. Boeing study, 1968. Four core vehicles from Saturn V-25(S) study lashed together to obtain million-pound payload using existing hardware. First stage consisted of 4 Saturn IC's stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; second stage 4 Saturn II standard length stages with 5 J-2 engines

Saturn V-A American orbital launch vehicle. MSFC study, 1968. Essentially identical to Saturn INT-20; standard Saturn IC stage together with Saturn IVB second stage, with Centaur third stage for deep space missions.

Saturn V-B American orbital launch vehicle. MSFC study, 1968. Intriguing stage-and-a-half to orbit design using Saturn S-ID stage. The S-ID would be the same length and engines as the standard Saturn IC, but the four outer engines and their boost structure would be jettisoned once 70% of the propellant was consumed, as in the Atlas ICBM. This booster engine assembly would be recovered and reused. The center engine would be gimbaled and serve as a sustainer engine to put the rest of the vehicle and its 50,000 pound payload into orbit. At very minimal cost (36 months lead-time and $ 150 million) the United States could have attained a payload capability and level of reusability similar to that of the space shuttle.

Saturn V-C American orbital launch vehicle. MSFC study, 1968. S-ID stage-and-a-half first stage and Saturn IVB second stage. Centaur available as third stage for deep space missions. 30% performance improvement over Saturn V-A/Saturn INT-20 with standard Saturn IC first stage.

Saturn V-Centaur American orbital launch vehicle. MSFC study, 1968. S-ID stage-and-a-half first stage and Saturn IVB second stage. Centaur available as third stage for deep space missions. 30% performance improvement over Saturn V-A/Saturn INT-20 with standard Saturn IC first stage.

Saturn V-D American orbital launch vehicle. MSFC study, 1968. Rehashed the Boeing 1967 studies, covering a variety of stage stretches and 120, 156, or 260 inch solid rocket boosters, but with S-ID stage-and-a-half first stage.

Saturn V-ELV American orbital launch vehicle. NASA study, 1966. No-height-limitation stretched Saturn with Titan UA1207 motors for thrust augmentation.

Winged Saturn V North American's study was dated 18 March 1963. The second alternative was a two-stage reusable booster derived from the Saturn V. This would boost either an 11,400 kg cargo, or a half-disc lifting body spaceplane, which would accommodate two crew plus ten passengers and minor cargo

Family: orbital launch vehicle. People: von Braun. Country: USA. Spacecraft: Apollo Lunar Landing, Mercury, Apollo LM, Apollo CSM, Gemini, Gemini Lunar Lander, Lunar Bus, Apollo ULS, Apollo M-1, Apollo W-1, Apollo D-2, Apollo R-3, Apollo L-2C, Apollo Lenticular, LORL, Apollo LM Shelter, Apollo LM Taxi, CSM Electrical, Self-Deploying Space Station, Apollo LM Truck, Apollo MSS, Gemini - Saturn V, Saturn II Stage Wet Workshop, Voyager 1973, GE Lunar NEP Tug, MORL Mars Flyby, Apollo LMSS, Gemini Lunar Surface Rescue Spacecraft, Apollo LTA, Gemini Lunar Surface Survival Shelter, Gemini LORV, Apollo 120 in Telescope, Apollo LMAL, Apollo LASS, LESA Lunar Base, Space Station 1970, Apollo ALSEP, Apollo LRM, LESA Shelter, Space Base, S-IVB Advanced Station, Skylab Lunar Orbit Station, Apollo LRV, PFS, Skylab, AES Lunar Base, ALSS Lunar Base. Projects: Apollo. Launch Sites: Cape Canaveral, Cape Canaveral LC39A, Cape Canaveral LC39B. Stages: Saturn IC, Saturn II, Saturn IVB (S-IB). Bibliography: 16, 17, 18, 2, 216, 222, 228, 229, 230, 231, 233, 26, 27, 33, 34, 47, 6, 60, 4832, 8601.
Photo Gallery

Saturn V 1Saturn V 1
Credit: NASA


Saturn VSaturn V
Credit: © Mark Wade


Saturn II stageSaturn II stage
Credit: © Mark Wade


J-2J-2
Credit: © Mark Wade


Launch vehiclesLaunch vehicles
Launch vehicles of the world as known in 1980
Credit: © Mark Wade


N1 and Saturn VN1 and Saturn V
Credit: © Mark Wade


Saturn VSaturn V
Credit: NASA


Saturn V  LVSaturn V LV
Credit: © Mark Wade


Saturn V 2Saturn V 2
Credit: NASA


Saturn V No. bSaturn V No. b
Credit: NASA


Saturn V No. dSaturn V No. d
Credit: NASA


Saturn V TitleSaturn V Title


Saturn A-1 to C-5Saturn A-1 to C-5
Credit: © Mark Wade


Saturn C-4B 2 Stage Saturn C-4B 2 Stage
Saturn C-4B 2 Stage version Nov 1961
Credit: © Mark Wade


Saturn C-4B finalSaturn C-4B final
Saturn C-4B final configuration Nov 1961
Credit: © Mark Wade


Saturn 5 finalSaturn 5 final
Saturn 5 final configuration Nov 1961
Credit: © Mark Wade


Saturn 5 nuclearSaturn 5 nuclear
Saturn 5 nuclear configuration Nov 1961
Credit: © Mark Wade


Saturn MLV 1.37Saturn MLV 1.37
Credit: © Mark Wade


Saturn 2-120-4Saturn 2-120-4
Credit: © Mark Wade


Saturn 2-120-5Saturn 2-120-5
Credit: © Mark Wade


Saturn MLV 2-120-7Saturn MLV 2-120-7
Credit: © Mark Wade


Saturn 2 w MM SOSaturn 2 w MM SO
Credit: © Mark Wade



1953 March - . Launch Vehicle: Saturn V.
1955 March - . Launch Vehicle: Saturn V.
1956 January 10 - . Launch Vehicle: Saturn V.
1956 November 1 - . Launch Vehicle: Saturn V.
1958 June 23 - . Launch Vehicle: Saturn V.
1958 August 6 - . Launch Vehicle: Saturn V.
1958 November 1 - . Launch Vehicle: Saturn V.
1958 December 17 - . Launch Vehicle: Saturn V.
1959 January 1 - . Launch Vehicle: Saturn V.
1959 March 6 - . Launch Vehicle: Saturn V.
1959 June 25-26 - . Launch Vehicle: Saturn V.
1959 August 1 - . Launch Vehicle: Saturn V.
1959 November 27 - . Launch Vehicle: Saturn V.
1959 December 31 - . Launch Vehicle: Saturn V.
1960 January 14 - . Launch Vehicle: Saturn V.
1960 February 15 - . Launch Vehicle: Saturn V.
1960 Summer - . Launch Vehicle: Saturn V.
1960 September 10 - . Launch Vehicle: Saturn V.
1960 October 5 - . Launch Vehicle: Saturn V.
1961 February 10 - . Launch Vehicle: Saturn V.
1961 April 6 - . Launch Vehicle: Saturn V.
1961 April 12 - . Launch Vehicle: Saturn V.
1961 May - . Launch Vehicle: Saturn V.
1961 June 20 - . LV Family: Saturn V. Launch Vehicle: Saturn C-3.
1961 July 7 - . Launch Vehicle: Saturn V.
1961 July 11 - . Launch Vehicle: Saturn V.
1961 July 20 - . Launch Vehicle: Saturn V.
1961 August 2 - . Launch Vehicle: Saturn V.
1961 August 16 - . Launch Vehicle: Saturn V.
1961 August 23 - . Launch Vehicle: Saturn V.
1961 August 31 - . LV Family: Saturn V. Launch Vehicle: Saturn C-3.
1961 September 5 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral. Launch Vehicle: Saturn V.
1961 September 11 - . Launch Vehicle: Saturn V.
1961 September 17 - . Launch Vehicle: Saturn V.
1961 September 25 - . Launch Vehicle: Saturn V.
1961 September 26 - . Launch Vehicle: Saturn V.
1961 October 3 - . Launch Vehicle: Saturn V.
1961 November 6 - . Launch Vehicle: Saturn V.
1961 November 16 - . Launch Vehicle: Saturn V.
1961 November 20 - . LV Family: Saturn V. Launch Vehicle: Saturn C-5.
1961 November 29-30 - . Launch Vehicle: Saturn V.
1961 December 4 - . Launch Vehicle: Saturn V.
1961 December 15 - . Launch Vehicle: Saturn V.
1961 December 20 - . Launch Vehicle: Saturn V.
1962 January 5 - . Launch Vehicle: Saturn V.
1962 February 14 - . Launch Vehicle: Saturn V.
1962 March 18 - . Launch Vehicle: Saturn V.
1962 April 2-3 - . Launch Vehicle: Saturn V.
1962 April 24 - . Launch Vehicle: Saturn V.
1962 May 26 - . Launch Vehicle: Saturn V.
1962 May 29 - . Launch Vehicle: Saturn V.
1962 June - . Launch Vehicle: Saturn V.
1962 July 2 - . Launch Vehicle: Saturn V.
1962 July 21 - . Launch Vehicle: Saturn V.
1962 August 8 - . Launch Vehicle: Saturn V.
1962 August - . Launch Vehicle: Saturn V.
1962 September 26 - . Launch Vehicle: Saturn V.
1962 September - . Launch Vehicle: Saturn V.
1962 October 4 - . Launch Vehicle: Saturn V.
1962 October 30 - . Launch Vehicle: Saturn V.
1962 October - . Launch Vehicle: Saturn V.
1962 October 31 - . Launch Vehicle: Saturn V.
1962 December 3 - . Launch Vehicle: Saturn V.
1962 December 4 - . Launch Vehicle: Saturn V.
1963 January 22 - . Launch Vehicle: Saturn V.
1963 February 12 - . Launch Vehicle: Saturn V.
1963 February 25 - . Launch Vehicle: Saturn V.
1963 April 17 - . LV Family: Saturn V, Saturn I, Titan.
1963 April 30 - . Launch Vehicle: Saturn V.
1963 May 20-22 - . Launch Vehicle: Saturn V.
1963 June 3 - . Launch Vehicle: Saturn V.
1963 June 25 - . Launch Vehicle: Saturn V.
1963 July 10 - . Launch Vehicle: Saturn V.
1963 August 2 - . Launch Vehicle: Saturn V.
1963 August 23 - . LV Family: Saturn V.
1963 October 2 - . Launch Vehicle: Saturn V.
1963 October 15 - . Launch Vehicle: Saturn V.
1963 October 31 - . Launch Vehicle: Saturn V.
1963 November 12 - . Launch Vehicle: Saturn V.
1963 November 12 - . Launch Vehicle: Saturn V.
1963 November 27 - . Launch Vehicle: Saturn V.
1963 December 9 - . Launch Vehicle: Saturn V.
1963 December 26 - . Launch Vehicle: Saturn V.
1964 February 26 - . Launch Vehicle: Saturn V.
1964 March 30 - . Launch Vehicle: Saturn V.
1964 April - . Launch Vehicle: Saturn V.
1964 May 28 - . LV Family: Saturn I, Saturn V. Launch Vehicle: Saturn INT-27, Saturn V-25(S)B, Saturn V-25(S)U.
1964 September 10 - . LV Family: Saturn V.
1964 October 2 - . Launch Vehicle: Saturn V.
1964 October 15 - . Launch Vehicle: Saturn V.
1964 November 12-19 - . Launch Vehicle: Saturn V.
1964 November 19-26 - . Launch Vehicle: Saturn V.
1964 December 4 - . Launch Vehicle: Saturn V.
1964 December 7 - . Launch Vehicle: Saturn V.
1965 January 5 - . Launch Vehicle: Saturn V.
1965 January 14-21 - . Launch Vehicle: Saturn V.
1965 January 23 - . Launch Vehicle: Saturn V.
1965 January 28 - . Launch Vehicle: Saturn V.
1965 February 9 - . Launch Vehicle: Saturn V.
1965 February 19 - . Launch Vehicle: Saturn V.
1965 February 27 - . LV Family: Saturn V, Saturn I.
1965 March 8 - . Launch Vehicle: Saturn V.
1965 April 13 - . Launch Vehicle: Saturn V.
1965 April 14 - . Launch Vehicle: Saturn V.
1965 April 15 - . Launch Vehicle: Saturn V.
1965 April 16 - . Launch Vehicle: Saturn V.
1965 April 20 - . Launch Vehicle: Saturn V.
1965 June 21 - . Launch Vehicle: Saturn V.
1965 June 25 - . Launch Vehicle: Saturn V.
1965 July 1 - . Launch Vehicle: Saturn V.
1965 August 5 - . Launch Vehicle: Saturn V.
1965 August 15 - . Launch Vehicle: Saturn V.
1965 August 20 - . Launch Vehicle: Saturn V.
1965 September - . Launch Vehicle: Saturn V.
1965 September 2-9 - . Launch Vehicle: Saturn V.
1965 December 8 - . Launch Vehicle: Saturn V.
1965 December 15 - . Launch Vehicle: Saturn V.
1965 December 17 - . Launch Vehicle: Saturn V.
1965 December 19 - . Launch Vehicle: Saturn V.
1965 December - . Launch Vehicle: Saturn V.
1966 January 6-13 - . Launch Vehicle: Saturn V.
1966 March 23 - . Launch Vehicle: Saturn V.
1966 May 25 - . Launch Vehicle: Saturn V.
1966 June 2 - . Launch Vehicle: Saturn V.
1966 July 13 - . Launch Vehicle: Saturn V.
1966 August 3 - . Launch Vehicle: Saturn V.
1966 August 8 - . Launch Vehicle: Saturn V.
1966 October 21 - . Launch Vehicle: Saturn V.
1966 December 5 - . Launch Vehicle: Saturn V.
1966 December 6 - . Launch Vehicle: Saturn V.
1966 December 22 - . Launch Vehicle: Saturn V.
1966 December 22 - . Launch Vehicle: Saturn V.
1967 January 10 - . Launch Vehicle: Saturn V.
1967 January 20 - . Launch Vehicle: Saturn V.
1967 January 26 - . Launch Vehicle: Saturn V.
1967 February 7 - . Launch Vehicle: Saturn V.
1967 February 10 - . Launch Vehicle: Saturn V.
1967 March 7 - . Launch Vehicle: Saturn V.
1967 March 8 - . Launch Vehicle: Saturn V.
1967 March 15 - . Launch Vehicle: Saturn V.
1967 April 1 - . Launch Vehicle: Saturn V.
1967 April 14 - . Launch Vehicle: Saturn V.
1967 April 17 - . Launch Vehicle: Saturn V.
1967 April 18 - . Launch Vehicle: Saturn V.
1967 May 5 - . Launch Vehicle: Saturn V.
1967 May 19 - . Launch Vehicle: Saturn V.
1967 June 8 - . Launch Vehicle: Saturn V.
1967 June 20 - . Launch Vehicle: Saturn V.
1967 July 26 - . Launch Vehicle: Saturn V.
1967 August 1 - . Launch Vehicle: Saturn V.
1967 August 11 - . Launch Vehicle: Saturn V.
1967 October 8 - . Launch Vehicle: Saturn V.
1967 November 9 - . 12:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT1. Launch Vehicle: Saturn V.
1967 November 15 - . Launch Vehicle: Saturn V.
1967 December 1 - . Launch Vehicle: Saturn V.
1967 December 14 - . Launch Vehicle: Saturn V.
1968 January 9 - . Launch Vehicle: Saturn V.
1968 April 4 - . 12:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT2. Launch Vehicle: Saturn V.
1968 April 23 - . Launch Vehicle: Saturn V.
1968 April 27 - . Launch Vehicle: Saturn V.
1968 May 25 - . Launch Vehicle: Saturn V.
1968 July 5 - . Launch Vehicle: Saturn V.
1968 July 23 - . Launch Vehicle: Saturn V.
1968 July 30 - . Launch Vehicle: Saturn V.
1968 August 1 - . Launch Vehicle: Saturn V.
1968 August 7 - . Launch Vehicle: Saturn V.
1968 August 9 - . Launch Vehicle: Saturn V.
1968 August 10 - . Launch Vehicle: Saturn V.
1968 August 12 - . Launch Vehicle: Saturn V.
1968 August 12 - . Launch Vehicle: Saturn V.
1968 August 13 - . Launch Vehicle: Saturn V.
1968 August 14 - . Launch Vehicle: Saturn V.
1968 August 15 - . Launch Vehicle: Saturn V.
1968 August 17 - . Launch Vehicle: Saturn V.
1968 August 17 - . Launch Vehicle: Saturn V.
1968 August 19 - . Launch Vehicle: Saturn V.
1968 August 26 - . Launch Vehicle: Saturn V.
1968 August 27 - . Launch Vehicle: Saturn V.
1968 September 10-11 - . Launch Vehicle: Saturn V.
1968 September 16 - . Launch Vehicle: Saturn V.
1968 October 1-2 - . Launch Vehicle: Saturn V.
1968 October 7 - . Launch Vehicle: Saturn V.
1968 October 24 - . Launch Vehicle: Saturn V.
1968 November 8 - . Launch Vehicle: Saturn V.
1968 November 10 - . Launch Vehicle: Saturn V.
1968 November 11 - . Launch Vehicle: Saturn V.
1968 December 9 - . Launch Vehicle: Saturn V.
1968 December 21 - . 12:51 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT1. Launch Vehicle: Saturn V.
1969 January 14 - . Launch Vehicle: Saturn V.
1969 January 15-17 - . Launch Vehicle: Saturn V.
1969 March 3 - . 16:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT2. Launch Vehicle: Saturn V.
1969 March 11 - . Launch Vehicle: Saturn V.
1969 March 28 - . Launch Vehicle: Saturn V.
1969 April 28 - . Launch Vehicle: Saturn V.
1969 May 2 - . Launch Vehicle: Saturn V.
1969 May 18 - . 16:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39B. Launch Platform: LUT3. Launch Vehicle: Saturn V.
1969 June 3 - . Launch Vehicle: Saturn V.
1969 June 9-13 - . Launch Vehicle: Saturn V.
1969 July 16 - . 13:32 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT1. Launch Vehicle: Saturn V.
1969 August 1 - . Launch Vehicle: Saturn V.
1969 November 14 - . 16:22 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT2. Launch Vehicle: Saturn V.
1970 January 4 - . Launch Vehicle: Saturn V.
1970 January 7 - . Launch Vehicle: Saturn V.
1970 April 11 - . 19:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT3. Launch Vehicle: Saturn V.
1970 November 23 - . Launch Vehicle: Saturn V.
1971 January 31 - . 21:03 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT2. Launch Vehicle: Saturn V.
1971 July 16 - . Launch Vehicle: Saturn V.
1971 July 26 - . 13:34 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT3. Launch Vehicle: Saturn V.
1972 April 16 - . 17:54 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT3. Launch Vehicle: Saturn V.
1972 December 7 - . 05:33 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT3. Launch Vehicle: Saturn V.
1973 January 19 - . Launch Vehicle: Saturn V.
1973 May 14 - . 17:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. Launch Platform: LUT2. Launch Vehicle: Saturn V.

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