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Rocket Propellant Properties: solid htpb 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 htpb ap al | 1,000 | 6,390 | 3,550 | 5,184 | 1,580 | 15 | HTPB binder plus 18pct Al | 285 | AP integral | Solid composite propellant: 68% AP / 18% Al / 14% HTPB by mass. Pc=1000 psia, epsilon=15:1. Theoretical Isp vac ~295-300 s; delivered Isp vac=285 s at ~93% efficiency (typical Ariane/Atlas class SRM). C*=1580 m/s, Tc=3550 K per MDPI Aerospace 9(11):677 (2022). Mixture ratio not defined for premixed solid propellant. Sea-level Isp typically 250-265 s depending on nozzle design. |
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