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1.12 2194 4143 3.35 4341 1.12 2193 b 5 h 9: 3502 5.14 5050 1.23 2147 4191 5.58 5083 1.25 2140 of 2: h 2: 4014 5.92 3311 0.39 2542 4679 7.37 3587 0.44 2499 ch 4: 3485 4.94 4157 1.06 2160 4131 5.58 4207 1.09 2139 c 2 h 6: 3511 3.87 4539 1.13 2176 4137 3.86 4538 1.13 2176 rp-1: 3424 3.87 4436 1.28 2132 4021 3.85 4432 1.28 2130 mmh: 3427 2.28 4075 ...
Russia is also working to switch the Soyuz-2 from RP-1 to "naftil" [10] or "naphthyl". [11] [12] After the RP-1 standard, RP-2 was developed. The primary difference is an even lower sulfur content. However, as most users accept RP-1, there was little incentive to produce and stock a second, even rarer and more expensive formulation.
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
The Aerojet Rocketdyne AR1 is a 2,200-kilonewton-class (500,000 lbf) thrust RP-1/LOX oxidizer-rich staged combustion cycle rocket engine project. [1]The engine was conceived in 2014, and received US government funding to build a prototype engine in 2016. [2]
One of the most efficient mixtures, oxygen and hydrogen, suffers from the extremely low temperatures required for storing liquid hydrogen (around 20 K or −253.2 °C or −423.7 °F) and very low fuel density (70 kg/m 3 or 4.4 lb/cu ft, compared to RP-1 at 820 kg/m 3 or 51 lb/cu ft), necessitating large tanks that must also be lightweight and ...
Rutherford is a liquid-propellant rocket engine designed by aerospace company Rocket Lab [8] and manufactured in Long Beach, California. [9] The engine is used on the company's own rocket, Electron. It uses LOX (liquid oxygen) and RP-1 (refined kerosene) as its propellants and is the first flight-ready engine to use the electric-pump-fed cycle.
Archimedes is presented as a highly reusable liquid-propellant engine using methane and liquid oxygen in an oxidizer-rich staged combustion cycle. [1] [2] There are both sea-level and vacuum variants. The engine is mostly 3D printed, [7] with some of the biggest 3D printers in the world. The rationale for the cycle change from the original gas ...
Merlin 1 is a family of LOX/RP-1 rocket engines developed 2003–2012. Merlin 1A and Merlin 1B utilized an ablatively-cooled carbon-fiber composite nozzle. Merlin 1A produced 340 kilonewtons (76,000 lb f ) of thrust and was used to power the first stage of the first two Falcon 1 flights in 2006 and 2007.