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Rocket Propellant Properties: solid minuteman1 s1
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 minuteman1 s1 | 3,494 | 10 | 5,180 | 1,579 | 1.76 | 780 | HTPB type AP Al binder | 1.3 | 254 | 16 | 6,289 | AP integral | solid composite | Minuteman I first stage motor (Orbital ATK). 70% AP / 16% Al / 14% binder. Pc avg=780 psia burn-time average (max 850 psia). Altitude Isp=254 s. C*=5180 ft/s (1579 m/s) from Table 12-3. Tc=5790 F (3494 K) from propellant adiabatic flame temp. Burn time 52.6 s. Total thrust 201500 lbf max sea level. Six-point star grain. Expansion ratio 10:1. |
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