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5.70 3195 0.36 2417 RP-1: 3103 3.01 3665 1.09 1908 3697 3.30 3692 1.10 1889 F 2:O 2 70:30 RP-1: 3377 3.84 4361 1.20 2106 3955 3.84 4361 1.20 2104 F 2:O 2 87.8:12.2 MMH: 3525 2.82 4454 1.24 2191 4148 2.83 4453 1.23 2186 Oxidizer Fuel Comment V e r T c d C* V e r T c d C* N 2 F 4: CH 4: 3127 6.44 3705 1.15 1917 3692 6.51 3707 1.15 1915 C 2 H 4: ...
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.
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 ...
Dinitrogen tetroxide (N 2 O 4) and hydrazine (N 2 H 4), MMH, or UDMH. Used in military, orbital, and deep space rockets because both liquids are storable for long periods at reasonable temperatures and pressures. N 2 O 4 /UDMH is the main fuel for the Proton rocket, older Long March rockets (LM 1-4), PSLV, Fregat, and Briz-M upper stages.
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
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.
For example, LH 2 /LO 2 bipropellant produces higher I sp (due to higher chemical energy and lower exhaust molecular mass) but lower thrust than RP-1/LO 2 (due to higher density and propellant flow). In many cases, propulsion systems with very high specific impulse—some ion thrusters reach 25x-35x better I sp than chemical engines—produce ...
SpaceX’s Merlin 2 LOX/RP-1-fueled engine on a gas-generator cycle, capable of a projected 7,600 kN (1,700,000 lbf) of thrust at sea level and 8,500 kN (1,920,000 lbf) in a vacuum and would provide the power for conceptual super-heavy-lift launch vehicles from SpaceX, which Markusic dubbed Falcon X and Falcon XX.