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Engine Origin Designer Vehicle Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [e] Oxidiser: fuel ratio ...
The RD-180 (Russian: Ракетный Двигатель-180 (РД-180), romanized: Raketnyy Dvigatel-180, lit. 'Rocket Engine-180') is a rocket engine that was designed and built in Russia. It features a dual combustion chamber , dual- nozzle design and is fueled by a RP-1 / LOX mixture.
In April 2024, Musk shared the performance achieved by SpaceX with the Raptor 1 engine (sea level 185 t f, Rvac 200 t f) and Raptor 2 engine (sea level 230 t f, Rvac 258 t f) along with the target specifications for the upcoming Raptor 3 (sea level 280 t f, Rvac 306 t f) [50] [51] and said SpaceX would aim to ultimately achieve over 330 tonnes ...
RD-171 (and its RD-171M successor), -180 and -191 are derivatives of RD-170. RD-0124—a series of oxygen/kerosene engines used in the second stage of Soyuz-2.1b rocket as well as in upper stages of Angara series rockets. YF-100—Chinese engine developed in the 2000s; used on the Long March 5, Long March 6, and Long March 7. [12]
Notable examples are the RD-107/RD-108 engines used on the R-7, Molniya and Soyuz rocket families, and the RD-170, RD-171 and RD-180 engines used on the Energia, Zenit and Atlas V launch vehicles. As of July 2013 [update] , the company remained largely owned by the federal government of Russia , but RSC Energia owned approximately 14% of the ...
The maiden launch of the Atlas V rocket equipped with the RD-180 engine occurred in 2002. Energomash committed to delivering a total of 101 RD-180s for the fixed price of one billion dollars. [1] [2] [3] Under RD AMROSS, Pratt & Whitney is licensed to produce the RD-180 in the United States.
The RD-180 uses only two combustion chambers instead of the four of the RD-170. The RD-180 used on the Atlas V replaced the three engines used on early Atlas rockets with a single engine and achieved significant payload and performance gains.
In 2011, performance goals for the engine were a vacuum thrust of 690 kN (155,000 lbf), a vacuum specific impulse (I sp) of 310 s (3.0 km/s), an expansion ratio of 16 (as opposed to the previous 14.5 of the Merlin 1C) and chamber pressure in the "sweet spot" of 9.7 MPa (1,410 psi). Merlin 1D was originally designed to throttle between 100% and ...