U.S. President Kennedy's proposal on May 25, 1961, of an In early June 1961, Bruce Lundin, deputy director of the Lewis Research Center, led a week-long study of six different rendezvous possibilities. These designs used two or three Rocketdyne The lack of a Saturn C-3 launch vehicle in 1965 created a large payload gap (LEO) between the The 3-stage version would use the S-IV stage, with a diameter of 5.5 meters and 12.2 meters in length. Soon, a totally new launch site on Merritt Island, just northwest of the Cape, was being designed to support C-3 salvo launches for Marshall's planned EOR Apollo missions. The booster consisted of a first stage containing two Saturn V After six months of further discussion at NASA, in the summer of 1962, Langley Research Center‘s Lunar orbit rendezvous (LOR) proposal was officially selected as the mission configuration for the Apollo program on November 7, 1962.Since 1961, a number of variants of the Saturn C-3 have been studied, proposed, and funded. Conclusion was that 43,000 kg stage (85% fuel) was needed for a lunar landing mission. The alternatives included Earth-orbital rendezvous (EOR), lunar-orbital rendezvous (LOR), Earth and lunar rendezvous, and rendezvous on the lunar surface, employing Saturn C-1s, C-3s, and Nova designs. I made the following changes: Robert C. Seamans, Jr., NASA Associate Administrator, notified the Directors of Launch Vehicle Program, Space Flight Programs, Advanced Research Programs, and Life Sciences Programs that Donald H. Heaton had been appointed Chairman of an Ad Hoc Task Group. Podcast: Play in new window | Download Subscribe: Android | Email | Google Podcasts | TuneIn | RSS Just as launch complex 34 dwarfed its predecessors, Saturn’s checkout represented a new magnitude in launch operations. On 7 October 1966, Boeing submitted a Final Report to the NASA Marshall Space Flight Center, "Studies of Improved Saturn V Vehicles and Intermediate Payload Vehicles". The design was for a four-stage launch vehicle that could launch 21,500 kg to low Earth orbit and send 6,800 kg to the Moon via Trans-Lunar Injection.
The design was for a three-stage launch vehicle that could launch 45,000 kilograms to low Earth orbit and send 18,000 kilograms to the Moon via trans-lunar injection.
Saturn C-3 would weigh about 1,023,700 kg at liftoff and would boost 36,280 kg into low earth orbit or 13,605 kg to escape velocity. Conclusion was that 43,000 kg stage (85% fuel) was needed for a lunar landing mission. Third rocket in the Saturn C series studied from 1959 to 1962Proposed Saturn C-3 and Apollo configuration (1962) If you have any questions, or need the bot to ignore the links, or the page altogether, please visit this simple FaQ for additional information. The Marshall Space Flight Center in Huntsville, Alabama developed an The Saturn C-3 was the primary launch vehicle for Earth orbit rendezvous. That report outlined the The need for a launch vehicle of Saturn C-3 capacity (45 tonnes to LEO) continued beyond the Apollo program. It would establish program plans and supporting resources necessary to accomplish the manned lunar landing mission by the use of rendezvous techniques, using the Saturn C-3 launch vehicle, with a target date of 1967. The common theme of these variants is the first stage with at least 3,044,000 lbf (13,540 kN) of sea-level thrust (SL).
The design was for a three-stage launch vehicle that could launch 45,000 kg (100,000 lb) to low Earth orbit and send 18,000 kg (39,000 lb) to the Moon via Trans-Lunar Injection. The Saturn C-1 stood three times higher, required six times more fuel, and produced ten times more thrust than the Jupiter. Launch vehicles studied were the Saturn C-2 and C-3. Please take a moment to review my edit. The Saturn C-3 was the third rocket in the Saturn C series studied from 1959 to 1962. Designed to lift 38 tons to LEO, it would utilize F-1 and J-2 rocket engines and tooling in storage from the Saturn V rocket program along with more recent Shuttle-era technologies to provide lower launch costs.Pyrios is an advanced booster concept proposed in 2012 by The Dynetics booster would attach at these points and apply thrust to an upper thrust beam in the SLS core, rather than at the bottom.