The Aerojet M-1 was one of the largest and most powerful liquid-hydrogen -fueled liquid-fuel rocket engines to be designed and component-tested. It was originally developed during the 1950s by the US Air Force. The M-1 offered a baseline thrust of 1,500,000 pounds-force (6.67 meganewtons) and an immediate growth target of 1,800,000 lb f (8 MN).

Engine developed 1962-1966 for Uprated Saturn and Nova million-pound payload boosters to support manned Mars missions. Reached component test stage before cancellation. AKA: AJ23-146. Status: Study 1961. Thrust: 5,335.90 kN (1,199,558 lbf). Unfuelled mass: 9,068 kg (19,991 lb). Specific impulse: 428 s. Specific impulse sea level: 310 s.

Jan 3, 2023 · The M-1 engine consisted of a single regeneratively-cooled thrust chamber, separate turbopump assemblies driven by separate gas generators—as opposed to a single gas generator driving a common power shaft—and a turbine exhaust cooled nozzle extension.

This collection consists of design information, development program plans, quarterly technical progress reports, research and development proposals, and technical reviews concerning the development of the M-1 rocket engine. The majority of the material was prepared for NASA by Aerojet-General.

M-1 ROCKET ENGINE USING THE ANALOG COMPUTER by John R. Szuch, Leon M. Wenzel, and Robert J. Baumbick Lewis Research Center SUMMARY The purpose of this investigation was to study the starting characteristics of the M-1 engine system by using an analog computer simulation. It is further intended that this

Mechanical and physical properties of materials used in M-1 liquid hydrogen/liquid oxygen rocket engine

ENGINE DEVELOPMENT The M-1 rocket engine is a machine of impressive proportions. The ove_-1 all length is 521 inches or approximately 27 feet. A _-foot thrust-chambe_ diameter, coupled with a 17-foot-nozzle-exit diameter, are further evidence of the size of the engine. At design-point conditions, the M-1 fuel turbop_p

The M-1 was designed by the Aerojet as an advanced, high-performance first or upper stage powerplant for heavy-lift, deep space missions of the post-Saturn V (post-Apollo) era. The engine was conceived for use in the contemplated Nova super booster.

The M-1 Rocket Engine 630200 Considerable progress is being made by Aerojet-General Corp. to develop a large, high-performance rocket engine (designated M-1) using liquid oxygen and liquid hydrogen propellants and with a nominal thrust rating of 1.5 million pounds.

Jan 14, 2024 · Aerojet's M1 was the largest and most powerful liquid hydrogenfueled liquid fuel rocket engine to be designed and component tested. The M1 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.