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A highly refined form of jet fuel, RP-1 burned much more cleanly than conventional petroleum fuels and also posed less of a danger to ground personnel from explosive vapours. It became the propellant for most of the early American rockets and ballistic missiles such as the Atlas, Titan I, and Thor.
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
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.
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 ...
A NASA employee standing between two Raptor 2 Vacuum engines (background) and a Raptor 2 sea-level (foreground). The streamlined design is due to the reduced parts visible above the engine nozzles. Raptor 2 is a complete redesign of the Raptor 1 engine. [79] The turbomachinery, chamber, nozzle, and electronics were all redesigned.
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 ...
Raptor is a family of methane/liquid oxygen rocket engines under development by SpaceX since the late 2000s, [2] although LH2/LOX propellant mix was originally under study when the Raptor concept development work began in 2009. [15] When first mentioned by SpaceX in 2009, the term "Raptor" was applied exclusively to an upper stage engine ...