Variable burn-rate propellant Description

Here is the text of the patent for Variable burn-rate propellant, a kind of propellant 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.

US Patent Issued on January 7, 2003

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