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1.41 1844 MMH:N 2 H 4:N 2 H 5 NO 3 55:26:19 2989 2.46 3717 1.46 1864 3500 2.49 3722 1.46 1863 ClF 3: MMH:N 2 H 4:N 2 H 5 NO 3 55:26:19 Hypergolic 2789 2.97 3407 1.42 1739 3274 3.01 3413 1.42 1739 N 2 H 4: Hypergolic 2885 2.81 3650 1.49 1824 3356 2.89 3666 1.50 1822 N 2 O 4: MMH: Hypergolic, common 2827 2.17 3122 1.19 1745 3347 2.37 3125 1.20 ...
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 ...
RP-1 / H 2 O 2: Staged, decomposition and combustion 265 [72] ... 5.9: M-1 USA: Aerojet ... 302.3–313 8,580–20,470 17–41 196: 1.8:
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.
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.
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 ...
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 ...