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Aerojet's M-1 was the largest and most powerful liquid hydrogen-fueled liquid fuel rocket engine to be designed and component tested. The M-1 offered a baseline thrust of 6.67 million N (1.5 million lbf) and 8 million N (1.8 million lbf) as its immediate growth target. If built, the M-1 would be larger and more efficient than the famed F-1 that powered the first stage of the Saturn V rocket to the moon. ==History== The M-1 traces its history to US Air Force studies from the late 1950s for its launch needs in the 1960s. By 1961 these had evolved into the Space Launcher System design. The SLS consisted of a series of four rocket designs, all built around a series of solid-fuel boosters and liquid hydrogen powered upper stages. The smallest model, intended to launch the Dynasoar, used two solids and an "A" liquid core. To power the "A" booster, Aerojet was contracted to convert an LR-87, used in the Titan II missile, to run on liquid hydrogen. A prototype was successfully tested between 1958 and 1960. Initial studies of the solid were also handed to Aerojet, starting in 1959. The SLS also envisioned a number of much larger designs intended to launch the Air Force's Lunex Project manned lunar landing. Lunex was a direct landing mission, in which a single very large spacecraft would fly to the Moon, land, and return. In order to launch such a design to low earth orbit (LEO), a very large booster with a payload would be required. These larger SLS designs followed the same basic outline as the smaller Dynasoar booster, but used much more powerful solids and the "B" and "C" liquid stages. To provide the required power, the liquid stages mounted a cluster of twelve J-2s. To reduce this complexity, the Air Force also had Aerojet start studies of a much larger hydrogen-fueled design that would replace the twelve J-2s with only two engines. These initial studies would eventually emerge as the M-1, with a thrust of 1.2 million pounds force. When NASA formed in 1958, they also started planning for a lunar landing. Like the Air Force, their Project Apollo initially favoured a direct landing profile, requiring a large booster to launch the spacecraft into LEO. Prior to NASA taking over Wernher von Braun's Saturn work for the US Army, they had no large rocket designs of their own, and started a study program known as Nova to study a range of options. Initially the payload requirements were fairly limited, and the favoured Nova designs used a first stage with four F-1 engines and a payload of about . These designs were presented to President Dwight D. Eisenhower on January 27, 1959. However, the Apollo spacecraft requirements quickly grew, settling on a spacecraft (the CSM) with a three-man crew. To launch a craft to the moon required a massive payload to LEO. Nova designs of this capability were quickly presented with up to eight F-1 engines, along with much more powerful upper stages that demanded the M-1 engine. Thus, for a brief period, the M-1 was used on the baseline designs for both NASA's and the Air Force's lunar programs. In 1961, President John F. Kennedy announced his intentions of landing a man on the moon before the decade was out. After a brief argument, NASA won the mission over the Air Force. However, Nova would require massive manufacturing capability that did not currently exist, and it was not clear that booster construction could be started in time for a landing before 1970. By 1962 they had decided to use von Braun's Saturn design, which went through a process of re-design to produce a usable booster that could be built in the existing facilities at Michoud, Louisiana. With the selection of Saturn for the lunar missions, work on Nova turned to the post-Apollo era. The designs were re-targeted for manned planetary expedition, namely a manned landing on Mars. Even utilizing a lightweight mission profile like that selected for Apollo, a Mars mission required a truly massive payload of about one million pounds to low earth orbit. This led to a second series of design studies, also known as Nova although they were essentially unrelated to the earlier designs. Many of the new designs used the M-1 as their second-stage engine, although demanding much higher payloads. In order to meet these goals, the M-1 project was uprated from 1.2 million pounds force to a nominal 1.5 million pounds force, and the designers deliberately added more turbopump capability to allow it to expand to at least 1.8 million pounds force, and potentially as high as 2.0 million pounds force. Additionally, the M-1 was even considered for a number of first stage designs, in place of the F-1 or the solids. For this role the specific impulse was dramatically reduced, and it appears some consideration was given to various expanding nozzle designs to address this. M-1 development continued through this period, although as the Apollo program expanded, NASA started cutting funding to the M-1 project in order to complete Saturn-related developments first. In 1965, another NASA project studied advanced versions of the Saturn, replacing the cluster of five J-2's on the S-II second stage with one M-1, five J-2T's, (an improved version of the J-2 with an aerospike nozzle), or a high pressure engine known as the HG-3, which would later become the direct predecessor of the Space Shuttle SSME. By 1966 it was clear that present funding levels for NASA would not be maintained in the post-Apollo era. The Nova design studies ended that year, and the M-1 along with it. The last M-1 contract expired on August 24, 1965, although testing continued on existing funds until August 1966. Studies on the J-2T ended at the same time. Although the HG-3 was never built, its design formed the basis for the Space Shuttle Main Engine. 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「M-1 (rocket engine)」の詳細全文を読む スポンサード リンク
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