Solid Rocket Propellant
Formulation Data
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This page is for amateurs wanting the last propellant characterization data on solid rocket propellants. The propellant parameters will be adjust from time to time to provide a more accurate characterization as more motor firing data on a particular formulation becomes available.
Initial weights are shown based on total propellant weight. The second set of weights shown in brackets are based on the weight of the propellant less the binder weight as discussed in the "How To Make Amateur Rockets" book. The curing agent ratio is shown for the second set of weights.
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- 19.27% (20%) R20LM HTPB
- 19.27% (20%) Magnesium (-650 to 1000 mesh)
- 57.8% (60%) PSAN-I Blend C Ammonium Nitrate
- 3.66% (Curing ratio = 0.19) Mondur MR MDI Curing Agent
- Burn rate coefficient = 0.0061
- Burn rate exponent = 0.507
- Propellant density = 0.0527 lbm/inch**3
- C-star range = 4100 to 3300 feet/second depending on motor size.
- Gamma = 1.23
Propellant 1 (Dec. 26, 2003)- 19.27% (20%) R45HT or R45M HTPB
- 19.27% (20%) Magnesium (-650 to 1000 mesh)
- 57.8% (60%) PSAN-I Blend C Ammonium Nitrate
- 3.66% (Curing ratio = 0.19) Mondur MR MDI Curing Agent
- Burn rate coefficient = 0.0032
- Burn rate exponent = 0.6
- Propellant density = 0.0527 lbm/inch**3
- C-star range = 4100 to 3300 feet/second depending on motor size.
- Gamma = 1.23
Propellant 2 (Dec. 26, 2003)Note: Curing agent ratio = (Wt. of curing agent)/(Wt. of binder)