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Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio AJ-10-190 USA: Aerojet: Space Shuttle, Orion, Apollo CSM: Active Upper N 2 O 4 /MMH: Pressure-fed: 316 [1] 26,689 [1] 8.62 [1] 118 [1] 23.08: Archimedes New ...
The thrust-to-weight ratio is usually calculated from initial gross weight at sea level on earth [6] and is sometimes called thrust-to-Earth-weight ratio. [7] The thrust-to-Earth-weight ratio of a rocket or rocket-propelled vehicle is an indicator of its acceleration expressed in multiples of earth's gravitational acceleration, g 0. [5]
Jet or rocket engine Mass Thrust Thrust-to-weight ratio (kg) (lb) (kN) ... Merlin 1D rocket engine, full-thrust version 467 1,030 825 185,000 180.1 References
The NK-33 engine is renowned for its exceptional thrust-to-weight ratio, one of the highest among Earth-launchable rocket engines. It has been surpassed only in recent years by the RD-253 from NPO Energomash and the Merlin 1D and Raptor engines from SpaceX. The NK-43, a derivative optimized for upper-stage use, features a longer nozzle designed ...
The engine's 150:1 thrust-to-weight ratio is the highest ever achieved for a rocket engine. [ 8 ] [ 9 ] The first flight of the Merlin 1D engine was also the maiden Falcon 9 v1.1 flight. [ 10 ]
The common thrust-to-weight ratio of a launch vehicle is within the range of 1.3 to 2.0. [3] Another performance metric to keep in mind when designing each rocket stage in a mission is the burn time, which is the amount of time the rocket engine will last before it has exhausted all of its propellant.
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 stag
Measuring and making comparisons of rocket engine thrust is more complicated than it may first appear. Based on actual measurement the liftoff thrust of Apollo 15 was 7,823,000 lbf (34.80 MN), which equates to an average F-1 thrust of 1,565,000 lbf (6.96 MN) – slightly more than the specified value.