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Rocket Propellant Properties: solid pban ap al
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 |
|---|---|---|---|---|---|---|---|---|---|---|
| solid pban ap al | 907 | 6,210 | 3,450 | 4,954 | 1,510 | 7.72 | PBAN binder plus 16pct Al | 268 | AP integral | Space Shuttle SRB: 69.6% AP / 16% Al / 12.04% PBAN / 0.4% Fe2O3 by mass. Pc=906.8 psia nominal; epsilon=7.72:1 (exit area / throat area). Delivered Isp vac=268 s, Isp SL=242 s per NASA SP-2007-562. C*=1510 m/s estimated; Tc=3450 K per published SRM data. Each SRB produced ~14.7 MN (3.3 Mlbf) sea-level thrust at ignition. |
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