This page lists propellant formulation information not available in the “How To Make Amateur Rockets” book. 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.

Note: Curing agent ratio = (Wt. of curing agent)/(Wt. of binder) = (0.8) * (Equivalent weight of curing agent)/(Equivalent weight of binder)

This assumes 80% linkage for a flexible propellant. Other curing agents can be used, but an adjustment to the curing agent ratio will have to be made.

Ammonium nitrate, magnesium, HTPB binder

  • 20% R20LM HTPB (Low molecular weight HTPB)
  • 20% Magnesium powder(-650 mesh)
  • 60% Ammonium Nitrate powder
  • (Curing ratio = 0.19) Rubinate M (MDI Curing Agent)
  • Burn rate coefficient = 0.0061
  • Burn rate exponent = 0.507