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2.37 4468 1.31 2122 nh 3: 3531 3.32 4337 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 ...
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.
RP-1 / H 2 O 2: Staged, decomposition and combustion 265 [73] 234,800: 47.40: 342: 70.01: 8: HM-7A ... 5.9: M-1 USA: Aerojet ...
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.
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 ...
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.