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Rocket Propellant Properties: mono afm315e
Rocket propellant performance data — specific impulse, characteristic velocity, chamber conditions for bipropellant, solid, and monopropellant combinations
| propellant id | chamber pressure psia (psia) | chamber temp deg r (deg R) | chamber temp k (K) | cstar ft s (ft/s) | cstar m s (m/s) | expansion ratio (dimensionless) | fuel | isp vac s (s) | oxidizer | source method |
|---|---|---|---|---|---|---|---|---|---|---|
| mono afm315e | 200 | 3,780 | 2,100 | 4,528 | 1,380 | 100 | AF-M315E | 257 | none monopropellant | AF-M315E (ASCENT) green monopropellant; catalytic decomposition. Pc=200 psia, epsilon=100:1 (GPIM 22-N thruster design point). Isp vac=257 s per NTRS 20140012587 (Spores et al., 2014) and NTRS 20170001286 (Burnside et al., 2017). Adiabatic flame temp ~2100 K (DTIC ADA623499). C*=1380 m/s estimated at 90-93% C* efficiency (Busek 0.5-N thruster data). Density 46% higher than hydrazine; density-Isp 50% better than hydrazine. Catalyst pre-heat to 370-400 C required; classified as mildly toxic (not REACH-SVHC). |
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