Variable burn-rate propellant
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United States of America Patent
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Jan 7, 2003
Grant Date -
May 9, 2002
app pub date -
Nov 23, 1999
filing date -
Nov 23, 1999
priority date (Note) -
Expired
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Abstract
Disclosed are propellants such as may be used in solid rocket motors. In one preferred embodiment, the propellant comprises one high energy propellant composition comprising a homogeneous mixture of fuel and oxidizer having a predetermined fuel/oxidizer ratio, wherein individual fuel particles are generally uniformly distributed throughout a matrix of oxidizer, and a low energy propellant composition comprising a fuel and oxidizer. The amounts of the two propellants are present in amounts which achieve a preselected burn rate.
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