Solid rocket motor propellants with reticulated structures embedded therein to provide variable burn rate characteristics
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United States of America Patent
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-
Jul 12, 1988
Grant Date -
N/A
app pub date -
Sep 18, 1986
filing date -
Sep 18, 1986
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A solid propellant grain which comprises an homogeneous mass of propellant material including an oxidant. A variable burn rate is provided by embedding a reticulated structure 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 selected to preferably provide improved bonding to the propellant mass.
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