Solid rocket motor propellants with reticulated structures embedded therein to provide variable burn rate characteristics.

摘要

A solid propellant grain (10) which comprises an homogeneous mass (12) of propellant material including an oxidant. A variable burn rate is provided by embedding a reticulated structure (14) in a portion only of the propellant mass. The reticulated structure may be coated with a high thermal conductivity material to provide an increased burning rate. The coat of material is preferably selected to provide improved bonding to the propellant mass, and may for example comprise lead or copper.