| Saturn V |
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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. 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 initally 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.
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 inital 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. Manufacturer: Von Braun. Launches: 13. Success Rate: 100.00%. First Launch Date: 1967-11-09. Last Launch Date: 1973-05-14. Launch data is: complete. LEO Payload: 118,000 kg (260,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 47,000 kg (103,000 lb). to a: Translunar trajectory. Associated Spacecraft: Apollo CSM, Apollo LM, Apollo LTA, PFS, Skylab, Apollo 120 in Telescope, Apollo R-3, MORL Mars Flyby, Saturn II Stage Wet Workshop, Apollo M-1, Gemini Lunar Surface Survival Shelter, Apollo LASS. Other Associated Spacecraft: Gemini Lunar Surface Rescue Spacecraft, Apollo W-1, S-IVB Advanced Station, LORL, Gemini LORV, LESA Shelter, Apollo ALSEP, Skylab Lunar Orbit Station, Apollo MSS, Apollo LM Truck, Apollo LRM, Space Base, Apollo LM Shelter, Apollo LM Taxi, Apollo ULS. Further Associated Spacecraft: Apollo LMSS, Apollo LRV, Saturn V Rotating Stations, Apollo LMAL, Apollo Lunar Base, Voyager 1973, . Liftoff Thrust: 33,737.900 kN (7,584,582 lbf). Total Mass: 3,038,500 kg (6,698,700 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 102.00 m (334.00 ft). Development Cost $: 7,439.600 million. in: 1966 average dollars. Launch Price $: 431.000 million. in: 1967 price dollars.
Saturn C-4.
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.
LEO Payload: 99,000 kg (218,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 32,000 kg (70,000 lb). to a: Translunar trajectory. Liftoff Thrust: 26,990.400 kN (6,067,683 lbf). Total Mass: 2,347,180 kg (5,174,640 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 76.00 m (249.00 ft). Flyaway Unit Cost $: 58.290 million. in: 1985 unit dollars.
Saturn C-4B.
Final configurtion 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.
LEO Payload: 95,000 kg (209,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 31,000 kg (68,000 lb). to a: Translunar trajectory. Liftoff Thrust: 26,679.900 kN (5,997,880 lbf). Total Mass: 2,051,290 kg (4,522,320 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 89.00 m (291.00 ft).
Saturn C-5.
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.
LEO Payload: 120,000 kg (260,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 41,000 kg (90,000 lb). to a: Translunar trajectory. Liftoff Thrust: 33,350.000 kN (7,497,370 lbf). Total Mass: 2,847,590 kg (6,277,860 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 100.00 m (320.00 ft).
Saturn C-5N.
Version of Saturn C-5 considered with small nuclear thermal stage in place of S-IVB oxygen/hydrogen stage.
LEO Payload: 155,000 kg (341,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 64,000 kg (141,000 lb). to a: Translunar trajectory. Liftoff Thrust: 33,350.000 kN (7,497,370 lbf). Total Mass: 2,841,040 kg (6,263,420 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 100.00 m (320.00 ft).
Saturn V 2.
Two stage version of Saturn V, consisting of 1 x Saturn S-IC + 1 x Saturn S-II, used to launch Skylab.
LEO Payload: 75,000 kg (165,000 lb). Apogee: 500 km (310 mi). Liftoff Thrust: 34,030.000 kN (7,650,240 lbf). Total Mass: 2,822,000 kg (6,221,000 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 104.80 m (343.80 ft).
Saturn MLV-V-1.
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.
LEO Payload: 137,250 kg (302,580 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 49,600 kg (109,300 lb). to a: Translunar trajectory. Liftoff Thrust: 40,019.900 kN (8,996,831 lbf). Total Mass: 3,501,350 kg (7,719,150 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 111.00 m (364.00 ft).
Saturn MLV-V-1/J-2T/200K. Status: Study 1965. 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.
at: 28.00 degrees. Liftoff Thrust: 40,019.900 kN (8,996,831 lbf). Total Mass: 3,216,150 kg (7,090,390 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 89.00 m (291.00 ft).
Saturn MLV-V-1/J-2T/250K. Status: Study 1965. 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.
at: 28.00 degrees. Liftoff Thrust: 40,019.900 kN (8,996,831 lbf). Total Mass: 3,216,150 kg (7,090,390 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 89.00 m (291.00 ft).
Saturn MLV-V-1A. Status: Study 1965. 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.
LEO Payload: 145,000 kg (319,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 54,400 kg (119,900 lb). to a: Translunar trajectory. Liftoff Thrust: 40,485.100 kN (9,101,413 lbf). Total Mass: 3,648,700 kg (8,044,000 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 121.00 m (396.00 ft).
Saturn MLV-V-2.
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.
LEO Payload: 137,250 kg (302,580 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 53,550 kg (118,050 lb). to a: Translunar trajectory. Liftoff Thrust: 40,019.900 kN (8,996,831 lbf). Total Mass: 3,557,450 kg (7,842,830 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 117.00 m (383.00 ft).
Saturn MLV-V-3.
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.
LEO Payload: 160,400 kg (353,600 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 65,800 kg (145,000 lb). to a: Translunar trajectory. Liftoff Thrust: 40,019.900 kN (8,996,831 lbf). Total Mass: 3,664,570 kg (8,078,990 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 121.00 m (396.00 ft).
Saturn MLV-V-4(S).
MSFC study, 1965. Saturn V core, strengthened but not stretched, with 4 Titan UA1205 strap-on solid rocket boosters.
LEO Payload: 118,000 kg (260,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 52,900 kg (116,600 lb). to a: Translunar trajectory. Liftoff Thrust: 54,911.500 kN (12,344,596 lbf). Total Mass: 3,947,350 kg (8,702,410 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 102.00 m (334.00 ft). Flyaway Unit Cost $: 463.420 million. in: 1985 unit dollars.
Saturn MLV-V-4(S)-A.
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.
LEO Payload: 160,880 kg (354,670 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 57,500 kg (126,700 lb). to a: Translunar trajectory. Liftoff Thrust: 54,920.000 kN (12,346,500 lbf). Total Mass: 4,615,440 kg (10,175,300 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 113.00 m (370.00 ft). Flyaway Unit Cost $: 71.920 million. in: 1985 unit dollars.
Saturn MLV-V-4(S)-B.
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.
LEO Payload: 171,990 kg (379,170 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 63,160 kg (139,240 lb). to a: Translunar trajectory. Liftoff Thrust: 69,317.100 kN (15,583,104 lbf). Total Mass: 4,699,860 kg (10,361,410 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 89.00 m (291.00 ft). Flyaway Unit Cost $: 97.440 million. in: 1985 unit dollars.
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.
LEO Payload: 42,000 kg (92,000 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 5,936.010 kN (1,334,468 lbf). Total Mass: 504,400 kg (1,112,000 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 51.00 m (167.00 ft).
Saturn INT-18. Status: Study 1966. 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.
LEO Payload: 66,590 kg (146,800 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 25,642.100 kN (5,764,573 lbf). Total Mass: 1,966,810 kg (4,336,070 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 51.00 m (167.00 ft). Flyaway Unit Cost $: 387.440 million. in: 1985 unit dollars.
Saturn INT-19. Status: Study 1966. 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.
LEO Payload: 34,320 kg (75,660 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 9,061.410 kN (2,037,086 lbf). Total Mass: 770,000 kg (1,690,000 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 51.00 m (167.00 ft).
Saturn INT-20. Status: Study 1967. 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.
LEO Payload: 60,000 kg (132,000 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 33,737.900 kN (7,584,582 lbf). Total Mass: 2,478,120 kg (5,463,310 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 72.00 m (236.00 ft). Flyaway Unit Cost $: 391.500 million. in: 1985 unit dollars.
Saturn INT-21.
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.
LEO Payload: 115,900 kg (255,500 lb). to: 185 km Orbit. at: 28.00 degrees. Associated Spacecraft: Space Station. Liftoff Thrust: 33,737.900 kN (7,584,582 lbf). Total Mass: 2,916,080 kg (6,428,850 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 80.00 m (262.00 ft). Flyaway Unit Cost $: 681.500 million. in: 1985 unit dollars.
Saturn INT-27.
UA study, 1965. Saturn variant using various combinations of 156 inch rocket motors as first and second stages, with S-IVB upper stage.
LEO Payload: 40,000 kg (88,000 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 65,813.000 kN (14,795,350 lbf). Total Mass: 3,068,800 kg (6,765,500 lb). Core Diameter: 6.61 m (21.68 ft). Total Length: 67.00 m (219.00 ft). Flyaway Unit Cost $: 200.000 million. in: 1985 unit dollars.
Saturn V-ELV. Status: Study 1966. NASA study, 1966. No-height-limitation stretched Saturn with Titan UA1207 motors for thrust augmentation.
LEO Payload: 200,000 kg (440,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 67,000 kg (147,000 lb). to a: Translunar trajectory. Liftoff Thrust: 59,392.700 kN (13,352,010 lbf). Total Mass: 5,172,820 kg (11,404,110 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 124.00 m (406.00 ft). Flyaway Unit Cost $: 97.440 million. in: 1985 unit dollars.
Saturn V-3B. Status: Study 1967. 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.
LEO Payload: 166,600 kg (367,200 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 72,800 kg (160,400 lb). to a: Translunar trajectory. Liftoff Thrust: 40,033.800 kN (8,999,956 lbf). Total Mass: 3,741,120 kg (8,247,750 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 121.00 m (396.00 ft).
Saturn V-4X(U). Status: Study 1968. 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
LEO Payload: 527,600 kg (1,163,100 lb). to: 486 km Orbit. at: 28.00 degrees. Liftoff Thrust: 160,135.000 kN (35,999,780 lbf). Total Mass: 15,504,720 kg (34,182,050 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 95.00 m (311.00 ft).
Saturn V/4-260. Status: Study 1967. 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.
LEO Payload: 362,700 kg (799,600 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 161,859.300 kN (36,387,418 lbf). Total Mass: 10,351,050 kg (22,820,150 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 86.00 m (282.00 ft). Flyaway Unit Cost $: 446.600 million. in: 1985 unit dollars.
Saturn V-23(L).
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.
LEO Payload: 262,670 kg (579,080 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 99,850 kg (220,130 lb). to a: Translunar trajectory. Liftoff Thrust: 87,737.400 kN (19,724,152 lbf). Total Mass: 7,178,900 kg (15,826,700 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 115.00 m (377.00 ft).
Saturn V-24(L). Status: Study 1967. 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.
LEO Payload: 435,300 kg (959,600 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 185,900 kg (409,800 lb). to a: Translunar trajectory. Liftoff Thrust: 94,019.400 kN (21,136,402 lbf). Total Mass: 7,386,760 kg (16,285,010 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 180.00 m (590.00 ft).
Saturn V-25(S)B.
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.
LEO Payload: 223,500 kg (492,700 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 85,600 kg (188,700 lb). to a: Translunar trajectory. Liftoff Thrust: 72,338.400 kN (16,262,319 lbf). Total Mass: 6,342,540 kg (13,982,900 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 123.00 m (403.00 ft). Flyaway Unit Cost $: 174.000 million. in: 1985 unit dollars.
Saturn V-25(S)U. Status: Study 1968. 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.
LEO Payload: 248,663 kg (548,208 lb). to: 486 km Orbit. at: 28.00 degrees. Payload: 160,000 kg (350,000 lb). to a: Translunar trajectory. Liftoff Thrust: 72,338.400 kN (16,262,319 lbf). Total Mass: 6,439,300 kg (14,196,200 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 153.00 m (501.00 ft). Flyaway Unit Cost $: 174.000 million. in: 1985 unit dollars.
Saturn V-A. Status: Study 1968. 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.
LEO Payload: 60,000 kg (132,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 18,200 kg (40,100 lb). to a: Translunar trajectory. Liftoff Thrust: 33,737.900 kN (7,584,582 lbf). Total Mass: 2,478,120 kg (5,463,310 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 72.00 m (236.00 ft). Flyaway Unit Cost $: 391.500 million. in: 1985 unit dollars.
Saturn V-B. Status: Study 1968. 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 leadtime and $ 150 million) the United States could have attained a payload capability and level of reusability similar to that of the space shuttle.
LEO Payload: 22,600 kg (49,800 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 33,737.700 kN (7,584,537 lbf). Total Mass: 2,313,320 kg (5,099,990 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 50.00 m (164.00 ft).
Saturn V-C. Status: Study 1968. 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.
LEO Payload: 81,600 kg (179,800 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 20,400 kg (44,900 lb). to a: Translunar trajectory. Liftoff Thrust: 33,737.700 kN (7,584,537 lbf). Total Mass: 2,504,020 kg (5,520,410 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 72.00 m (236.00 ft).
Saturn V-D.
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.
LEO Payload: 326,500 kg (719,800 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 112,000 kg (246,000 lb). to a: Translunar trajectory. Liftoff Thrust: 161,846.500 kN (36,384,541 lbf). Total Mass: 9,882,100 kg (21,786,300 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 102.00 m (334.00 ft). Flyaway Unit Cost $: 736.600 million. in: 1985 unit dollars.
Saturn V-Centaur. Status: Study 1968. 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.
LEO Payload: 118,000 kg (260,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 39,000 kg (85,000 lb). to a: Mars flyby trajectory. Liftoff Thrust: 33,737.900 kN (7,584,582 lbf). Total Mass: 3,054,750 kg (6,734,570 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 113.00 m (370.00 ft). Flyaway Unit Cost $: 701.800 million. in: 1985 unit dollars.
Saturn V Chronology 1953 March - Research on 1 million lb thrust engine begun. Research on 1-million-pound thrust plus engine begun at Rocketdyne, the feasibility of which was established in March 1955. 1954 October 18 - Nuclear rocket engine proposed. At the suggestion of Theodore von Kármán and following a request of Gen. H. B. Thatcher, an Ad Hoc Committee of the Scientific Advisory Board met in the Pentagon to consider the application of nuclear energy to missile propulsion. In its report, the Committee "noted that there was an almost complete hiatus in the study of the nuclear rocket from 1947 following a report by North American Aviation, until a 1953 report by the Oak Ridge National Laboratory. Because the technical problems appear so severe, and because another 6 years of no progress in this area would seem to be unfortunate," the Committee felt that a continuing study both analytical and experimental, at a modest level of effort, should be carried on. 1955 March - Feasibility of million-pound-thrust liquid-fueled rocket engine established The feasibility of a million-pound-thrust liquid-fueled rocket engine established by the Rocketdyne Division of North American Aviation, Inc. 1955 June 1 - NERVA project begins. NACA Lewis Laboratory presented ARDC with results of air-breathing nuclear propulsion systems for manned applications, leading to AEC-AF Pluto project, and also initiated comparison of nuclear rocket with chemical systems for ICBM, a concept of use to Rover program. 1955 November 2 - NERVA go-ahead. The Atomic Energy Commission approved, on the basis of a statement of interest by the Department of Defense, the proposed plans of the Los Alamos Scientific and the Radiation Laboratories of the University of California, for the study and development of nuclear power for rocket propulsion. 1956 January 10 - First test of 400,000+ lb thrust engine. First U.S.-built complete liquid-rocket engine having a thrust in excess of 400,000 pounds was fired for the first time at Santa Susana, Calif. 1956 November 1 - Million pound thrust test stand activiated. Rocket test stand capable of testing engines to 1 million pounds thrust activated at Edwards AFB, which became operational in March 1957. 1957 March 18 - NERVA research cut back. As a result of guidance from the Secretary of Defense as to desired level of effort, the Atomic Energy Commission reduced its program on nuclear rocket propulsion to a single laboratory effort, phasing out work at the University of California Radiation Laboratory and concentrating AEC development efforts at Los Alamos Scientific Laboratory. 1957 June 1 - NERVA advanced concepts studied. Research on tungsten nuclear rocket propulsion systems initiated by NACA Lewis Laboratory, and other feasible systems for practical nuclear rocket systems, such as 1958 concept of coaxial jet gaseous reactor, followed. 1958 June 23 - Preliminary design begun on F-1 - 1.5 million pounds thrust rocket engine The U.S. Air Force contracted with NAA, Rocketdyne Division, for preliminary design of a single-chamber, kerosene and liquid-oxygen rocket engine capable of 1 to 1.5 million pounds of thrust. During the last week in July, Rocketdyne was awarded the contract to develop this engine, designated the F-1. 1958 August 6 - Rocketdyne gets F-1 engine contract. Rocketdyne Division of North American announced an Air Force contract for a 1-million-pound thrust engine. 1958 November 1 - F-1 engine gets highest priority. NASA requested DX priority for 1.5-million-pound-thrust F-1 engine project and Project Mercury. 1958 December 17 - Rocketdyne gets contract to develop F-1 engine. NASA awarded contract to Rocketdyne of North American to build single-chamber 1.5-million-pound-thrust rocket engine. 1959 January 1 - 1 million pound engine demonstrated. Rocketdyne demonstrated 1-million-pound-thrust liquid-propellant rocket combustion chamber at full power. 1959 January 19 - Contract with Rocketdyne for development of the F-1 engine NASA signed a definitive contract with Rocketdyne Division, NAA, for $102 million covering the design and development of a single-chamber, liquid-propellant rocket engine in the 1- to l.5-million-pound-thrust class (the F-1, to be used in the Nova superbooster concept). NASA had announced the selection of Rocketdyne on December 12. 1959 March 6 - Thrust chamber of the Saturn F-1 engine successfully static-fired The thrust chamber of the F-1 engine was successfully static-fired at the Santa Susana Air Force-Rocketdyne Propulsion Laboratory in California. More than one million pounds of thrust were produced, the greatest amount attained to that time in the United States. 1959 May 25-26 - National booster program, Dyna-Soar, and Mercury discussed Spacecraft: Mercury. The national booster program, Dyna-Soar, and Project Mercury were discussed by the Research Steering Committee. Members also presented reviews of Center programs related to manned space flight. Maxime A. Faget of STG endorsed lunar exploration as the present goal of the Committee although recognizing the end objective as manned interplanetary travel. George M. Low of NASA Headquarters recommended that the Committee:
1959 June 25-26 - Study and research areas for manned flight to and from the moon Spacecraft: Mercury. Members of the Research Steering Committee determined the study and research areas which would require emphasis for manned flight to and from the moon and for intermediate flight steps: Additional Details: Study and research areas for manned flight to and from the moon. 1959 July 1 - Kiwi-A first experimental nuclear rocket tested. The first experimental reactor (Kiwi-A) in the nuclear space rocket program operated successfully at full temperature and duration at Jackass Flats, Nev. 1959 August 1 - Static firing of the first Saturn planned for early 1960 The Advanced Research Projects Agency (ARPA) directed the Army Ordnance Missile Command to proceed with the static firing of the first Saturn vehicle, the test booster SA-T, in early calendar year 1960 in accordance with the $70 million program and not to accelerate for a January 1960 firing. ARPA asked to be informed of the scheduled firing date. 1959 November 27 - Study group to recommend upper-stage configurations While awaiting the formal transfer of the Saturn program, NASA formed a study group to recommend upper-stage configurations. Membership was to include the DOD Director of Defense Research and Engineering and personnel from NASA, Advanced Research Projects Agency, Army Ballistic Missile Agency, and the Air Force. This group was later known both as the Saturn Vehicle Team and the Silverstein Committee (for Abe Silverstein, Chairman). 1959 December 19 - NERVA development roles AEC/NASA. The Chairman, AEC, in a letter to the Administrator of NASA, proposed a flight test objective be established for the nuclear rocket program and proposed a technical program and division of agency responsibilities to achieve those objectives. 1959 December 31 - NASA approval of Saturn development program NASA accepted the recommendations of the Saturn Vehicle Evaluation Committee Silverstein Committee on the Saturn C-1 configuration and on a long-range Saturn program. A research and development plan of ten vehicles was approved. The C-1 configuration would include the S-1 stage (eight H-1 engines clustered, producing 1.5 million pounds of thrust), the S-IV stage (four engines producing 80,000 pounds of thrust), and the S-V stage two engines producing 40,000 pounds of thrust. 1960 January 14 - Super booster program to be accelerated President Dwight D. Eisenhower directed NASA Administrator T. Keith Glennan "to make a study, to be completed at the earliest date practicable, of the possible need for additional funds for the balance of FY 1960 and for FY 1961 to accelerate the super booster program for which your agency recently was given technical and management responsibility." 1960 February 15 - Lunar Program Based on Saturn Systems Spacecraft: Apollo Lunar Landing. Study issued by Huntsville of lunar landing alternatives using Saturn systems. Huntsville transferred from Army to NASA. Vought study on modular approach to lunar landing. Internally NASA decides on lunar landing as next objective after Mercury. 1960 May 31 - Selection of Rocketdyne for the J-2 rocket engine NASA selected Rocketdyne Division of NAA to develop the J-2, a 200,000-pound-thrust rocket engine, burning liquid hydrogen and liquid oxygen. (A decision was later made to use the J-2 in the upper stages of the Saturn C-5.) 1960 Summer - Boilerplate Apollo spacecraft to be used on Saturn C-1 H. Kurt Strass of STG and John H. Disher of NASA Headquarters proposed that boilerplate Apollo spacecraft be used in some of the forthcoming Saturn C-1 hunches. (Boilerplates are research and development vehicles which simulate production spacecraft in size, shape, structure, mass, and center of gravity.) These flight tests would provide needed experience with Apollo systems and utilize the Saturn boosters effectively. Four or five such tests were projected. On October 5, agreement was reached between members of Marshall Space Flight Center and STG on tentative Saturn vehicle assignments and flight plans. 1960 July 5 - House recommends a high priority manned expedition to the moon The House Committee on Science and Astronautics declared: "A high priority program should be undertaken to place a manned expedition on the moon in this decade. A firm plan with this goal in view should be drawn up and submitted to the Congress by NASA. Such a plan, however, should be completely integrated with other goals, to minimize total costs. The modular concept deserves close study. Particular attention should be paid immediately to long lead-time phases of such a program." The Committee also recommended that development of the F-1 engine be expedited in expectation of the Nova launch vehicle, that there be more research on nuclear engines and less conventional engines before freezing the Nova concept, and that the Orion project be turned over to NASA. It was the view of the Committee that "NASA's 10-year program is a good program, as far as it goes, but it does not go far enough. Furthermore the space program is not being pushed with sufficient energy." 1960 July 8 - Kiwi-A Prime tested at full power. Second experimental reactor (Kiwi-A Prime) in the Project Rover nuclear rocket program was successfully tested at full power and duration at Jackass Flats, Nev. 1960 July 14-15 - Space Exploration Program Council The third meeting of the Space Exploration Program Council was held at NASA Headquarters. The question of a speedup of Saturn C-2 production and the possibility of using nuclear upper stages with the Saturn booster were discussed. The Office of Launch Vehicle Programs would plan a study on the merits of using nuclear propulsion for some of NASA's more sophisticated missions. If the study substantiated such a need, the amount of in-house basic research could then be determined. 1960 September 10 - Contract for development of the Saturn J-2 engine A NASA contract for approximately $44 million was signed by Rocketdyne Division of NAA for the development of the J-2 engine. 1960 September 29 - RAND Corporation to evaluate nuclear propulsion missions In a memorandum to NASA Associate Administrator Robert C. Seamans, Jr., Robert L. King, Executive Secretary, described the action taken on certain items discussed at the July 14-15 meeting of the Space Exploration Program Council. Among these actions was the awarding of a contract to The RAND Corporation to evaluate missions for which nuclear propulsion would be desirable. Included in the study would be the determination of availability dates, cost of development, operational costs, the safety aspects of the missions, and an evaluation of research requirements. 1960 October 5 - Discussion of Saturn and Apollo guidance integration Members of STG visited the Marshall Space Flight Center to discuss possible Saturn and Apollo guidance integration and potential utilization of Apollo onboard propulsion to provide a reserve capability. Agreement was reached on tentative Saturn vehicle assignments on abort study and lunar entry simulation; on the use of the Saturn guidance system; and on future preparations of tentative flight plans for Saturns SA-6, 8, 9, and 10. 1960 October 7 - NERVA test facilities bidder's conference. AEC briefing held at the Nevada Test Site at Jackass Flats, Nev., for representatives of 26 companies for proposals to study the requirements for a National Nuclear Rocket Engine Development Facility. Existing test facilities are fully committed to the development of nuclear reactors. 1960 October 19 - Project Rover request for bids. Kiwi-A No. 3 static test of nuclear rocket propulsion was successfully conducted at AEC Nevada test site, resulting in NASA-AEC call for bids for industrial development phase of Project Rover on November 1, 1960. 1961 February 2 - NERVA Request for Proposal. NASA-AEC Space Nuclear Propulsion Office invited industry to submit proposals for participation in development of Nerva (nuclear engine for rocket vehicle application), a part of Project Rover initiated in 1955 by USAF-AEC. 1961 February 10 - First static test of prototype F-1 thrust chamber Rocketdyne Division's first static test of a prototype thrust chamber for the F-1 engine achieved a thrust of 1.550 million pounds in a few seconds at Edwards Air Force Base, Calif. 1961 April 6 - 1,640 million pounds of thrust achieved in static- firing of the F-1 engine The Marshall Space Flight Center announced that 1.640 million pounds of thrust was achieved in a static- firing of the F-1 engine thrust chamber at Edwards Air Force Base, Calif. This was a record thrust for a single chamber. 1961 April 12 - Seamans established the permanent Saturn Program Requirements Committee NASA Associate Administrator Robert C. Seamans, Jr., established the permanent Saturn Program Requirements Committee. Members were William A. Fleming, Chairman; John L. Sloop, Deputy Chairman; Richard B. Canright; John H. Disher; Eldon W. Hall; A. M. Mayo; and Addison M. Rothrock, all of NASA Headquarters. The Committee would review on a continuing basis the mission planning for the utilization of the Saturn and correlate such planning with the Saturn development and procurement plans. 1961 May - Reevaluation of the Saturn C-2 to support circumlunar missions The Marshall Space Flight Center began reevaluation of the Saturn C-2 configuration capability to support circumlunar missions. Results showed that a Saturn vehicle of even greater performance would be desirable. 1961 July 7 - NASA and DoD to study development of large launch vehicles The NASA Administrator and the Secretary of Defense concluded an agreement to study development of large launch vehicles for the national space program. For this purpose, the DOD-NASA Large Launch Vehicle Planning Group was created, reporting to the Associate Administrator of NASA and to the Assistant Secretary of Defense (Deputy Director of Defense Research and Engineering). 1961 July 11 - F-1 engine begins static testing. NASA announced that a complete F-1 engine had begun a series of static test firings at Edwards Rocket Test Center, Calif. 1961 July 20 - Large Launch Vehicle Planning Group The Large Launch Vehicle Planning Group, established on July 7, 1961, began its formal existence with seven DOD and seven NASA members and alternates. Additional Details: Large Launch Vehicle Planning Group. 1961 July 31 - NASA-DOD report on launch sites for Apollo Phase I of a joint NASA-DOD report on facilities and resources required at launch sites to support the manned lunar landing program was submitted to Associate Administrator Robert C. Seamans, Jr., by Kurt H. Debus, Director, Launch Operations Directorate, and Maj. Gen. Leighton I. Davis, Commander of the Air Force Missile Test Center. The report, requested by Seamans on June 23, was based on the use of Nova- class launch vehicles for the manned lunar landing in a direct ascent mode, with the Saturn C-3 in supporting missions. Eight launch sites were considered: Cape Canaveral (on-shore); Cape Canaveral (off- shore); Mayaguana Island (Atlantic Missile Range downrange); Cumberland Island, Ga.; Brownsville, Tex.; White Sands Missile Range, N. Mex.; Christmas Island, Pacific Ocean; and South Point, Hawaii. On the basis of minimum cost and use of existing national resources, and taking into consideration the stringent time schedule, White Sands Missile Range and Cape Canaveral (on-shore) were favored. White Sands presented serious limitations on launch azimuths because of first-stage impact hazards on populated areas. 1961 August 2 - Apollo launch site study begun. NASA headquarters announced that it was making a world-wide study of possible launching sites for Moon vehicles; the size, power, noise, and possible hazards of Saturn-Nova type rockets requiring greater isolation for public safety than presently available. 1961 August 16 - First F-1 firing. F-1 rocket engine tested in first of firing series of the complete flight system. 1961 August 23 - Golovin Committee evaluates three rendezvous methods for manned lunar landing Spacecraft: Apollo LM. The Large Launch Vehicle Planning Group (Golovin Committee) notified the Marshal! Space Flight Center (MSFC), Langley Research Center, and the Jet Propulsion Laboratory (JPL) that the Group was planning to undertake a comparative evaluation of three types of rendezvous operations and direct flight for manned lunar landing. Rendezvous methods were earth orbit, lunar orbit, and lunar surface. MSFC was requested to study earth orbit rendezvous, Langley to study lunar orbit rendezvous, and JPL to study lunar surface rendezvous. The NASA Office of Launch Vehicle Programs would provide similar information on direct ascent. Additional Details: Golovin Committee evaluates three rendezvous methods for manned lunar landing. 1961 August 24 - Cape Canaveral -. Merritt Island selected for Saturn V launch site. Spacecraft: Apollo Lunar Landing. After considering Cape Canaveral, Cape Canaveral-Merritt Island, Mayaguana-Bahamas, Cumberland-Georgia, Brownville-Texas, Christmas Island, Hawaii, and White Sands, Merritt Island selected as launch site for manned lunar flights and other missions requiring Saturn and Nova class vehicles. Based upon national space goals announced by the President in May, NASA plans called for acquisition of 80,000 acres north and west of AFMTC, to be administered by the USAF as agent for NASA and as a part of the Atlantic Missile Range. Additional Details: Merritt Island selected for Saturn V launch site.. 1961 August 28 - NERVA facilities contract. NASA selected Vitro Engineering Co. for negotiation of a design contract for an engine maintenance and disassembly building, one of the facilities to be a part of the National Nuclear Rocket Development Center. 1961 August - Heaton Committee recommends earth orbit rendezvous for Apollo mission Spacecraft: Apollo Lunar Landing. The Ad Hoc Task Group for Study of Manned Lunar Landing by Rendezvous Techniques, Donald H. Heaton, Chairman, reported its conclusions: rendezvous offered the earliest possibility for a successful lunar landing, the proposed Saturn C-4 configuration should offer a higher probability of an earlier successful manned lunar landing than the C-3, the rendezvous technique recommended involved rendezvous and docking in earth orbit of a propulsion unit and a manned spacecraft, the cost of the total program through first lunar landing by rendezvous was significantly less than by direct ascent. 1961 September 5 - Cape Canaveral -. Purchase of land for Saturn V launch facilities. Authorization for NASA to acquire necessary land for additional launch facilities at Cape Canaveral was approved by the Senate. 1961 September 7 - Selection of Saturn first stage assembly plant NASA announced that the government-owned Michoud Ordnance Plant near New Orleans, La., would be the site for fabrication and assembly of the Saturn C-3 first stage as well as larger vehicles. Finalists were two government-owned plants in St. Louis and New Orleans. The height of the factory roof at Michoud meant that an 8 x F-1 engined vehicle could not be built; 4 or 5 engines would have to be the maximum. 1961 September 11 - North American selected to build S-II stage. Spacecraft: Apollo Lunar Landing. NASA selected NAA to develop the second stage (S-II) for the advanced Saturn launch vehicle. The cost, including development of at least ten vehicles, would total about $140 million. The S-II configuration provided for four J-2 liquid-oxygen - liquid-hydrogen engines, each delivering 200,000 pounds of thrust. 1961 September 17 - 36 companies invited to bid on the first stage of advanced Saturn NASA invited 36 companies to bid on a contract to produce the first stage of the advanced Saturn launch vehicle. Representatives of interested companies would attend a pre-proposal conference in New Orleans, La., on September 26. Bids were to be submitted by October 16 and NASA would then select the contractor, probably in November. 1961 September 25 - S-IC fabrication plant manager named. Dr. George N. Constan of Marshall Space Flight Center named as acting manager of the new NASA Saturn fabrication plant near New Orleans by Director von Braun of Marshall Space Flight Center. 1961 September 26 - Bidders conference for S-IC stage. Spacecraft: Apollo Lunar Landing. NASA bidders conference on a contract to produce the booster (S-I) stage of the Saturn vehicle was held at the Municipal Auditorium, New Orleans. 1961 October 3 - S- IVB stage to have a single J-2 engine The MSFC-STG Space Vehicle Board at NASA Headquarters discussed the S- IVB stage, which would be modified by the Douglas Aircraft Company to replace the six LR-115 engines with a single J-2 engine. Funds of $500,000 were allocated for this study to be completed in March 1962. Additional Details: S- IVB stage to have a single J-2 engine. 1961 October 25 - Saturn static test stand site selected. NASA selected Pearl River site in southwestern Mississippi, 35 miles from Michoud plant in New Orleans, for static test facility for Saturn and Nova-class vehicles, completed facility to operate under direction of Marshall Space Flight Center. 1961 November 6 - Saturn S-II to use five J-2 engines Marshall Space Flight Center directed NAA to redesign the advanced Saturn second stage (S-II) to incorporate five rather than four J-2 engines, to provide a million pounds of thrust. 1961 November 6 - Working group on large launch vehicles In a memorandum to D. Brainerd Holmes, Director, Office of Manned Space Flight (OMSF), Milton W. Rosen, Director of Launch Vehicles and Propulsion, OMSF, described the organization of a working group to recommend to the Director a large launch vehicle program which would meet the requirements of manned space flight and which would have broad and continuing national utility for other NASA and DOD programs. The group would include members from the NASA Office of Launch Vehicles and Propulsion (Rosen, Chairman, Richard B. Canright, Eldon W. Hall, Elliott Mitchell, Norman Rafel, Melvyn Savage, and Adelbert O. Tischler); from the Marshall Space Flight Center (William A. Mrazek, Hans H. Maus, and James B. Bramlet); and from the NASA Office of Spacecraft and Flight Missions (John H. Disher). (David M. Hammock of MSC was later added to the group.) The principal background material to be used by the group would consist of reports of the Large Launch Vehicle Planning Group (Golovin Committee), the Fleming Committee, the Lundin Committee, the Heaton Committee, and the Debus-Davis Committee. Some of the subjects the group would be considering were:
1961 November 16 - Second decision on launch vehicles Golovin Committe studies launch vehicles through summer, but found the issue to be completely entertwined with mode (earth-orbit, lunar-orbit, lunar-surface rendezvous or direct flight. Two factions: large solids for direct flight; all-chemical with 4 or 5 F-1's in first stage for rendezvous options. In the end Webb and McNamara ordered development of C-4 and as a backup, in case of failure of F-1 in development, build of 6.1 m+ solid rocket motors by USAF. 1961 November 20 - Rosen Group recommends direct ascent for the lunar landing mission mode Milton W. Rosen, Director of Launch Vehicles and Propulsion, NASA Office of Manned Space Flight (OMSF), submitted to D. Brainerd Holmes, Director, OMSF, the report of the working group which had been set up on November 6. Additional Details: Rosen Group recommends direct ascent for the lunar landing mission mode. 1961 November 29-30 - Emergency switchover from Saturn to Apollo guidance as backup discussed Spacecraft: Apollo CSM. On a visit to Marshall Space Flight Center by MIT Instrumentation Laboratory representatives, the possibility was discussed of emergency switchover from Saturn to Apollo guidance systems as backup for launch vehicle guidance. 1961 December 4 - Rosen working group on launch vehicles NASA Associate Administrator Robert C. Seamans, Jr., commented to D. Brainerd Holmes, Director, Office of Manned Space Flight, on the report of the Rosen working group on launch vehicles, which had been submitted on November 20. Seamans expressed himself as essentially in accord with the group's recommendations. 1961 December 15 - Boeing named contractor for Saturn C-5 first stage (S-IC) Spacecraft: Apollo Lunar Landing. NASA announced that The Boeing Company had been selected for negotiations as a possible prime contractor for the first stage (S-IC) of the advanced Saturn launch vehicle. The S-IC stage, powered by five F-1 engines, would be 35 feet in diameter and about 140 feet high. The $300-million contract, to run through 1966, called for the development, construction, and testing of 24 flight stages and one ground test stage. The booster would be assembled at the NASA Michoud Operations Plant near New Orleans, La., under the direction of the Marshall Space Flight Center. 1961 December 20 - Douglas named contractor for Saturn S-IVB stage Spacecraft: Apollo Lunar Landing. NASA announced that Douglas Aircraft had been selected for negotiation of a contract to modify the Saturn S-IV stage by installing a single 200,000-pound-thrust, Rocketdyne J-2 liquid-hydrogen/liquid-oxygen engine instead of six 15,000-pound-thrust P. & W. hydrogen/oxygen engines. Known as S-IVB, this modified stage will be used in advanced Saturn configurations for manned circumlunar Apollo missions. 1961 December 21 - Saturn C-5 launch vehicle configuration selected Spacecraft: Apollo Lunar Landing. Rosen Committee studies in November and December indicated that the most flexible choice for Apollo was the Saturn C-4, with two required for the earth orbit rendezvous approach or one for the lunar orbit rendezvous mission, with a smaller landed payload. The panel rejected solid motors again, but Rosen himself still pushed for Nova. An extra F-1 engine was 'slid in' for insurance, resulting in the Saturn C-5 configuration. The Manned Space Flight Management Council decided at its first meeting that the Saturn C-5 launch vehicle would have a first stage configuration of five F-1 engines and a second stage configuration of five J-2 engines. The third stage would be the S-IVB with one J-2 engine. It recommended that the contractor for stage integration of the Saturn C-1 be Chrysler Corporation and that the contractor for stage integration of the Saturn C-5 be The Boeing Company. Contractor work on the Saturn C-5 should proceed immediately to provide a complete design study and a detailed development plan before letting final contracts and assigning large numbers of contractor personnel to Marshall Space Flight Center or Michoud. 1962 January 5 - Three-man Apollo spacecraft, Saturn C-5 launch vehicle announced Spacecraft: Apollo Lunar Landing. NASA made public the drawings of the three-man Apollo spacecraft to be used in the lunar landing development program, On January 9, NASA announced its decision that the Saturn C-5 would be the lunar launch vehicle. 1962 February 13-15 - Technical aspects of earth orbit rendezvous meeting Spacecraft: Gemini. A meeting on the technical aspects of earth orbit rendezvous was held at NASA Headquarters. Representatives from various NASA offices attended: Arthur L. Rudolph, Paul J. DeFries, Fred L. Digesu, Ludie G. Richard, John W. Hardin, Jr., Ernst D. Geissler, and Wilson B. Schramm of Marshall Space Flight Center (MSFC); James T. Rose of MSC; Friedrich O. Vonbun, Joseph W. Siry, and James J. Donegan of Goddard Space Flight Center (GSFC); Douglas R. Lord, James E. O'Neill, Richard J. Hayes, Warren J. North, and Daniel D. McKee of the NASA Office of Manned Space Flight (OMSF). Joseph F. Shea, Deputy Director for Systems, OMSF, who had called the meeting, defined in general terms the goal of the meeting: to achieve agreement on the approach to be used in developing the earth orbit rendezvous technique. After two days of discussions and presentations, the Group approved conclusions and recommendations:
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