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Rocket Propellant Properties: solid orbus6
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) | density g cm3 (g/cm3) | expansion ratio (dimensionless) | fuel | hazard class | isp vac s (s) | metal content pct (%) | mol mass exhaust kg mol (kg/mol) | oxidizer | propellant type | source method |
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| solid orbus6 | 3,672 | 47 | 5,200 | 1,585 | 1.77 | 611 | HTPB AP Al binder | 1.3 | 289.6 | 18 | 6,610 | AP integral | solid composite | Orbus-6 inertial upper stage motor (UTC). 68% AP / 18% Al / 14% HTPB binder. Pc avg=611 psia burn-time average (max 839 psia). Vacuum Isp=289.6 s. C*=5200 ft/s (1585 m/s). Tc=6150 F (3672 K) adiabatic flame. Burn time 101.0 s. Central perforation grain. Expansion ratio 47.3:1. |
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